Preliminary Design Reviewphsaerospace.weebly.com/uploads/1/3/0/5/13053226/pdr... · 2018. 9. 7. ·...

Preliminary Design Review

Joseph Vallone (NAR #83541 Level 2)

p. 754.322.1850 f. 754.322.1980

[email protected] Phsaerospace.weebly.com

Plantation High School Team 1 NASA Student Launch 2015-2016

Table of Contents 1 Summary ............................................................................................................. 2

2 Changes since Proposal ...................................................................................... 3

Vehicle Criteria Payload Criteria Project Plan

3 Vehicle Criteria ................................................................................................... 4

3.1 Selection, Design, and Verification of Launch Vehicle ............................................................................................................................................................ 4 3.2 Recovery Subsystem ........................................................................................................................ 35 3.3 Mission Performance Predictions ................................................................................................. 36 3.4 Interfaces & Integration ................................................................................................................. 44 3.5 Safety ................................................................................................................................................. 45

4 Payload Criteria ................................................................................................. 52

4.1 Selection, Design, and Verification of Payload ................................................................................. 52

4.2 Payload Concept Features and Definition ......................................................................................... 60

4.3 Science Value .......................................................................................................................................... 60

5 Project Plan ........................................................................................................ 62

5.1 Budget ............................................................................................................................................... 62 5.2 Timeline ............................................................................................................................................ 64 5.3 Funding Plan .................................................................................................................................... 68 5.4 Educational Engagement Plan ...................................................................................................... 69

6 Conclusion ......................................................................................................... 71

PRELIMINARY DESIGN REVIEW - NOVEMBER 2015 2

1 Summary

Team Summary

School Name

• Plantation High School

Team Name

• Plantation High School Team 1

Address

• 6901 Northwest 16th Street Plantation, FL 33313

Team Mentor

• Joseph Vallone (NAR #83541 Level 2)

Launch Vehicle Summary

Total Length (in.) 79

Mass (w/o payload & motor) (lbs.)

7.7

Diameter (in.) 4

Motor K695R

Recovery Dual Deployment

Main: 500 ft. AGL

Drogue: Apogee

Harness length: 30 ft.

Milestone Review Flysheet

Posted on website as a separate document.

Payload Summary

Title: Live Telemetry GPS Mapping

Experiment Summary

Hypothesizing that telemetric data can be recorded, transmitted, and displayed in real time from a rocket during flight, the experiment will utilize various sensors to collect data and send it to a computer AGL via a wireless transmitter.


2 Changes since Proposal

Vehicle Criteria

• Total length of vehicle has changed from 73 inches to 79 inches

o Length of tailcone increased to accommodate for the materials available in the market

• Target apogee is now 6,005 ft,

o To allow for the margin of error present from simulations

• Tail cone material has changed from aluminum to polystyrene

o To accommodate for the materials available in the market

• Nosecone shape changed from elliptical to ogive

o Aesthetics

• Fin design with larger root chord

o Withstand more impact; durability

Payload Criteria

Flight computer

• Changed from an Arduino Uno R3 to the Sparkfun RedBoard

o The Sparkfun RedBoard has a lower price and increased capability

Project Plan

Team

• Additional member was added to the team

Budget

• Has been updated according to the changes listed above

Funding

• No longer planning on holding videogame tournaments

o Low profit margin calculated

Outreach

• No longer working with middle schools for payload integration

o Plantation High Team 2 has decided to work with the middle school payloads in lieu of Team 1


3 Vehicle Criteria

3.1 Selection, Design, and Verification of Launch Vehicle

3.1.1 Mission Statement, Requirements, and Mission Success Criteria

Mission Statement

The mission of the Plantation High School Team 1 is to design, construct, and test-fly a solid propellant high-powered rocket, which conforms, to the requirements and regulations mandated by the Statement of Work (SOW) provided by NASA. The launch vehicle is to be launched at Clegg Sod Farm in Huntsville, Alabama. The rocket must achieve a maximum altitude of one-mile (5280-ft.), carry an operating scientific payload, and recover safely, thereby satisfying all requirements mandated by the SOW, The team must also educationally engage the community as a part of the NASA SL project by conducting local outreach events.

Mission Success Criteria

The mission success criteria of the Plantation High School Team 1 are as follows:

• All written documents are submitted to and approved by the NASA Review Panel.

• Design, construction, and test-flights of the launch vehicle are completed in compliance with the vehicle criteria and safety-requirements of the SOW, and are accomplished before launch week.

• The launch vehicle does not achieve an altitude greater than 5,280 ft. (1 mile) AGL.

• The launch vehicle successfully transports an operating scientific payload to apogee and during descent, while following payload and safety-requirements mentioned in the SOW.

• The launch vehicle safely recovers in compliance with the recovery and safety-requirements section of the SOW.

• The local community is engaged in educational activities relating to aerospace and engineering by the Plantation High School Team 1.

Requirements

Requirement Feature to Satisfy Requirement

Requirement Verification


1.1 The vehicle shall deliver the science or engineering payload to an apogee altitude of 5,280 ft.

AGL

An on-board, altitude triggered ejection charge, a fitted motor, and an appropriate drag coefficient to ensure the launch vehicle with payload reaches, but does not exceed, target altitude.

An on-board barometric altimeter will be used to record the altitude reached. Simulations will also be carried out to ensure altitude is reached.

1.2 The vehicle shall carry one commercially available,

barometric altimeter

Two Perfectflite Stratologger altimeters

The launch vehicle will include two Perfectflite Stratologger altimeters mounted onto an altimeter bay

1.3 The launch vehicle shall be designed to be reusable and

recoverable

A recovery system will be implemented using a main and a drogue parachute

Simulations will be carried out to ensure the kinetic energy of the rocket at landing will be below a safe threshold, enabling the rocket to be flown again without repairs or modifications

1.4 The launch vehicle shall have a maximum of four independent

sections

The rocket will be constructed into two sections.

Upon ejection, the vehicle will only separate into two sections tethered together using Kevlar.

1.5 The launch vehicle shall be limited to a single stage

The rocket will only use single stage motors.

The selection of the motors will satisfy the requirement and ensure only single stage motors will be utilized.

1.6 The launch vehicle shall be capable of being prepared for

flight at the launch site within two hours

A checklist w/ a scheduled, chronological set of events to keep the preparation of the launch vehicle in less than two hours.

A test run of the launch vehicle preparation will be performed prior to launch day to ensure launch vehicle preparations will take place within two hours.

1.7 The launch vehicle shall be capable of remaining in launch-

ready configuration at the pad for a minimum of 1 hour without losing the functionality f any

critical on-board component

All electrical components of the launch vehicle will be provided with a power supply that will sustain the hour during launch-ready configuration and for the duration of the flight.

A full-scale launch will take place along with battery testing to ensure all on-board components are working properly after an hour long (min.) launch-ready configuration at the pad.

1.8 The launch vehicle shall be capable of being launched by a

standard 12-volt direct current firing system

Igniters used will be capable of lighting with a 12-volt direct current firing system.

Test ignitions of the igniters and motors will be performed.


1.9 The launch vehicle shall require no external circuitry or

special ground support equipment to initiate launch

The launch vehicle will contain all components necessary, within the airframe, for a successful launch.

Test flights will be conducted where the launch vehicle will initiate launch using only internal equipment and those provided by Range Services.

1.10 The launch vehicle shall use a commercially available solid

motor propulsion system using APCP

An AeroTech K695 will be used for the test and final flight.

Research prior to use of motors determined the AeroTech K695 is a commercially available, APCP utilizing motors.

1.11 (includes all 1.11 sub requirements) Pressure vessels on the vehicle shall be approved by

the RSO

The launch vehicle design does not include pressure vessels.

N/A

1.12 The total impulse provided by a middle and/or high school

launch vehicle shall not exceed 2,560 Newton-seconds (K-class)

Use of AeroTech K695 motor

The AeroTech K695 has a total impulse of 1496.47 Newtons/second, which does not exceed the limit.

1.13 All teams shall successfully launch and recover a subscale

model of their rocket prior to CDR

A subscale model of the rocket will be designed, constructed, and flown subsequent to the submission and approval of the proposal.

The team’s Gantt chart will be followed accordingly. Simulations and measurements will be performed to ensure the subscale model is to scale and is capable of flying successfully.

1.14 All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight

configuration

The full-scale rocket will be constructed subsequent to the submission and approval of the CDR. The rocket will be flown on February 13th in Bunnell, FL. The same rocket will be used for the final flight in Huntsville, AL.

The rocket will remain unchanged from test launch to final launch.

1.14.1 The vehicle and recovery system shall have functioned as

designed

RockSim and test flights, subscale and full-scale.

Simulations and tests will be utilized to ensure the vehicle and recovery subsystem will/has function(ed) as designed.

1.14.2.1 If the payload is not flown, mass simulators shall be used to simulate the payload mass. The

mass simulators shall be located in the same approximate location

on the rocket as the missing payload mass.

The test flight will use the payload that will be used in the final flight. If the payload is not used in the test flight, a mass simulator identical to the mass of the payload will be substituted for the payloads.

Simulated payload weights will be recorded, so that in the event of the payloads not being completed, correct mass objects may be substituted.


1.14.2.2 If the payload changes the external surfaces of the rocket

or manages the total energy of the vehicle, those systems shall be

active during the full-scale demonstration flight.

The payload will not have external surfaces.

N/A

1.14.3 If the full-scale motor is not flown during the full-scale flight, it is desired that the motor simulate,

as closely as possible, the predicted maximum velocity and

maximum acceleration of the launch day flight.

The full-scale motor will be used for the full-scale test flight.

As the motor will not change, the test-flight data will produce accurate results in verifying the final flight in Huntsville, AL.

1.14.4 The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight.

RockSim, vehicle design Vehicle will be constructed as designed.

1.14.5 After successfully completing the full-scale

demonstration flight, the launch vehicle or any of its components shall not be modified without the concurrence of the NASA Range

Safety Officer (RSO).

No changes will be made Following the completion of the full-scale demonstration flight, the launch vehicle and all of its components will not be modified.

1.15 All vehicle prohibitions will be regarded concerning the design

of the launch vehicle

The prohibitions will not be included into the launch vehicle design in any aspect.

The vehicle prohibitions will be understood prior to the designing of the launch vehicle.

3.1.2 System Design and Functional Requirements

Structural System: Airframe & Guidance

Functional Requirements

• To provide the launch vehicle with a robust structural frame

• Effectively stabilize and guide the launch vehicle throughout its entire flight

Market Availability/Ease of Construction

The intended concept may be achieved by being purchased or constructed - within the budget and skillset(s) possessed by the Plantation High School Team 1 - from a vendor or within the facilities available to the team.

System Selected Concept Characteristics Subsystems

Airframe • Blue Tube

• Upper Airframe

• Lower Airframe

• Upper length: 32 in.

• Lower length: 26 in.

• Diameter: 4 in.

• Nosecone

• Upper

• Lower

• Bulkheads

• Coupler/Altimeter


Selection Rationale

Airframe

• Size is adequate enough to provide room for other systems of the launch vehicle - including payload, recovery, and propulsion - as well as each subsystem of the systems

• Does not interfere with the mission objective of achieving a minimum apogee of one mile AGL as of the PDR

• BlueTube material used is capable of withstanding impact upon landing and works synergistically with the nose cone, coupler, and tailcone in providing the rest of the launch vehicle with a robust frame.

Guidance

• Allows the launch vehicle to achieve stability while exiting the launch rail, and maintain its stability throughout the duration of its flight

• All structural components of the guidance system are properly integrated with the launch vehicle, and are capable of remaining intact after impact upon landing

Payload System: Frame & Electronics


To record and transmit real-time telemetric data (altitude, air pressure, acceleration in all directions, and precise location (GPS)) to a receiver at ground level and the Plantation High School Aerospace Program’s website.


The intended concept may be achieved by being purchased or constructed - within the budget and skillset(s) possessed by the Plantation High School SL New Team - from a vendor or within the facilities available to the team.

Bay

• Tailcone

Guidance • Fins

• Launch Rails

(2x)

• Dual Trapezoidal Fin set

• Carbon Fiber Fin set

• Fins

• Launch Rails

System Selected Concept Subsystems/Components


Selection Rationale

Frame

• Design provides the payload electronics with durable and sturdy bases, which the electronics will be tethered to

• Sufficient space is provided for each electronic component with wiring throughout

• Capable of remaining intact after being subject to the amount of thrust generated by the K695R motor (695 N) and upon landing

Electronics

• Capable of successfully recording and transmitting real-time telemetric data (altitude, air pressure, acceleration in all directions, and precise location (GPS)) to a receiver at ground level and to the Plantation High School Aerospace Program’s website.

• Easily integrated with the payload frame design

• Capable of functioning properly to achieve its objective

Recovery System: Altimeter Bay, Black Powder Ejection Charges, Chutes/Harness/Eyebolt


To guarantee that the launch vehicle recovers safely after the initial drogue chute is deployed at apogee and the main chute at 500 ft. AGL and to prevent any components of the launch vehicle from being damaged from impact upon landing.


The intended concept may be achieved by being purchased or constructed - within the budget and skillset(s) possessed by the Plantation High School Team 1 - from a vendor or within the facilities available to the team.

Frame • Universal Payload Frame • Balsa Baseplates

• Threaded Rods

• Silicon Compression

Tubes

Electronics • Real-Time Telemetric Data

Acquisition

• Barometric Pressure

Sensor (BMP 180)

• XBee Pro 900

• GPS Module

• Triple-Axis

Accelerometer

• Sparkfun RedBoard

System Subsystems


Selection Rationale

Altimeter Bay

• Robust altimeter sled

o Provides a base for two Perfectflite Stratologger altimeters to remain tethered to as they perform their subsystem functions throughout flight

The subsystem functions are as follows:

o One altimeter sends impulses to two separate black powder ejection charges at different periods of flight; one at apogee and one at 500 ft. AGL during descent

o A second altimeter sends impulses to two separate black powder ejection charges three seconds after each blast from the first altimeter

o This is performed as a method to guarantee the deployment of both drogue and main chutes.

Black Powder Ejection

• Located in both upper and lower airframes • Capable of separating the airframe component from the coupler as well as deploying each

airframe’s respective chute after being fired Parachutes, Harnesses, and Eyebolts

• Drogue and main chutes o Must be capable of being tethered to a recovery harness within the launch vehicle o Must be properly deployable by black powder ejection charges at apogee and at

500 ft. AGL during descent • Recovery harnesses

o Attached to eyebolts and d-links on bulkheads located within both airframes and on each end of the coupler

o Capable of withstanding the tension created by each black powder ejection charge

Sketches

Altimeter Bay • Altimeter Sled

• Altimeters

• 9v Batteries

• Threaded Rods/Nuts & Washers

• Bulkheads

Black Powder Ejection • Black Powder Charges

• E-matches

Chutes/Harnesses/Eyebolts • Main Chute

• Drogue Chute

• Recovery Harness (Upper)

• Recovery Harness (Lower)

• Eyebolts and D-Links


Figure 1 Sketch of recovery system in an exploded format.

Both main and drogue chutes are tethered to recovery harnesses of equal length and thickness. The main chute and its recovery harness are attached to a bulkhead in the upper airframe, while the drogue chute and its recovery harness are attached to a bulkhead in the lower airframe.

Figure 2 The recovery schematics

Within the altimeter bay are two Perfectflite SL100 altimeters. Both altimeters fire ejection charges at apogee and at 500 ft. AGL during descent to deploy the drogue and main chute. One altimeter fires three seconds after each charge as redundancy in order to guarantee the deployment of the drogue and main chutes.


Propulsion Systems: Frame & Motor


To provide the launch vehicle with sufficient thrust enabling it to exit the launch rails and to carry out a stable flight to the target apogee of 6,005 ft. AGL.


The intended concept may be achieved by being purchased or constructed - within the budget and skillset(s) possessed by the Plantation High School Team 1- from a vendor or within the facilities available to the team.

System Subsystems

Frame • Centering Rings

• Motor Mount

• Tail Cone

Motor • AeroTech K695R

• Motor Casing

• Retention Cap

Section Rationale

Frame

• Motor mount

o Firmly secures the selected motor within the lower airframe of the launch vehicle

o Capable of withstanding heat generated by the motor as it expels propellant

• Centering rings

o Robust

o Can bolster the motor mount within the airframe without sustaining any damage

• Tail cone

o Surrounds and protects the motor mount and motor

o Decreases drag of the launch vehicle

3.1.3 Subsystems

Structural Subsystems: Airframe

Nosecone

• Ogive

• Fiberglass

• Length: 12 in.


• Diameter: 4 in.

• Shoulder Length: 2 in.

• Shoulder Diameter: 3.9 in.

• Decreases the amount of drag the launch vehicle faces during flight; improves stability of launch vehicle during flight.

Sketch:

Upper Airframe

• Blue Tube

• Length: 32 in.

• OD: 4 in.

• ID: 3.9 in.

• Houses

o Payload system and subsystems

o Recovery system; Main chute

Sketch:


Lower Airframe

• Blue Tube

• Length: 26 in.

• OD: 4 in.

• ID: 3.9 in.

• Houses

o Propulsion system and subsystems

o Recovery subsystem; Main Chute

o Guidance subsystem; Fins

Sketch:


Bulkheads (3x)

• G10 Fiberglass

• Diameter: 3.9 in.

• Thickness: 0.125 in.

• Designates:

o Payload system

o Recovery system

o Recovery subsystem; Altimeter Bay

Coupler

• BlueTube

• Length: 11 in.

• OD: 3.9 in.

• ID: 3.8 in.

• Houses:

o Recovery subsystem; Altimeter Bay

• Serves as a conduit for the upper and lower airframes

Sketch:


Tailcone

• Polystyrene

• Ogive

• Length: 8 in.

• Front Diameter: 4 in.

• Rear Diameter: 2.2 in.

• Surrounds and protects the motor mount and motor while decreasing the drag of the launch vehicle.

Sketch:


Structural Subsystems: Guidance

Fins

• Carbon Fiber

• Trapezoidal; Dual Set

• Fin Count: 3

• Total Root Chord: 11.5 in.

• Height: 4.2 in.


• Adequately provides the launch vehicle with stability during flight.

Sketch:


Launch Buttons (2x)

• Steel Screws

• Guide the launch vehicle up the launch rail in order to provide a stable, vertical trajectory

Payload Subsystems: Frame

Balsa Baseplates

• Provide the payload electronics with attachment surfaces.

• Supported by two threaded rods.

Threaded Rods

• ¼ in. diameter

• Support the balsa baseplates within the payload bay.

• Fastened to a bulkhead separating the payload bay from the upper airframe recovery system with screws and washers.

Silicon Compression Tubes

• Located between each balsa baseplate to prevent them from oscillating during flight

Structural Subsystems: Electronics

Barometric Pressure Sensor

• Barometric Pressure Sensor – BMP180 Breakout

• Used to measure the air pressure surrounding the launch vehicle at any given altitude


• Wired to the Sparkfun Redboard Flight Computer.

GPS Module

• Adafruit Ultimate GPS Breakout

• Used to determine the position of the launch vehicle at any given time during flight.

• Wired to the Sparkfun Redboard Flight Computer

Triple Axis Accelerometer

• ADXL335 – 5V ready triple-axis accelerometer

• Used to measure the oscillation of the launch vehicle at different altitudes of flight.


Wireless Communication Device

• XBee Pro 900 RPSMA

• Transmits data retrieved by the Sparkfun RedBoard from the GPS module, triple-axis accelerometer, and barometric pressure sensor to an XBee AGL that will send the data to a computer, also AGL, and the Plantation High School Aerospace Program Website.


Flight Computer

• Sparkfun Redboard

• Retrieves the data collected from the GPS module, triple-axis accelerometer, and barometric pressure sensor and relays the data to the XBee Pro 900

• Wired to the barometric pressure sensor, GPS module, triple-axis accelerometer, and XBee Pro 900

Recovery Subsystems: Altimeter Bay

Altimeter Sled

• 3D Printed/ABS plastic

o Provides an attachment surface for the altimeters and 9v batteries

Altimeters (2x)

• Perfectflite Stratologger 100

• Tethered to the altimeter sled

• Measures the altitude of the launch vehicle at any given time;

• Sends an impulse to black powder ejection charges at apogee and at 500 ft. AGL to deploy drogue and main chutes

• Sends an impulse to black powder ejection charges after each initial blast at apogee and at 500 ft. AGL in order to guarantee the deployment of the drogue and main chutes

9v Batters (2x)

• Powers both altimeters

Bulkheads (2x)

• G10 Fiberglass




• Separates the altimeter bay from the upper and lower airframes.

Threaded Rods/Nuts + Washers

• ¼ in.

• Length: 11 in.

• Steel

• Fastened to each bulkhead of the altimeter bay

• Supports the altimeter sled and secures it in place

Recovery Subsystems: Black Powder Ejection

Black Powder Charges (4x) • Main (2x):

o 2.5g • Drogue (2x):

o 2g • Used to deploy both drogue and main chutes at apogee and 500 ft. AGL respectively • Fired from e-matches

E-Matches (4x) • Used to fire ejection charges to deploy drogue and main chutes at apogee and 500 ft. AGL

respectively

Recovery Subsystems: Chutes/Harnesses/Eyebolts

Drogue Chute

• Giant Leap TAC-24

• Diameter: 24 in.

• Shroud Lines (x6):

• Location: Lower Airframe

• Deployment: Apogee

• Deployed to slow the launch vehicle before the main chute deploys at 500 ft. AGL

Main Chute

• Giant Leap TAC-60

• Diameter: 60 in.

• Shroud Lines (x6):

• Location: Upper Airframe

• Deployment: 500 ft. AGL during descent

• Deployed to slow the launch vehicle to an optimal descent velocity before landing

Recovery Harness (Upper + Lower)

• Tubular Kevlar

• Length: 30 ft.


• Thickness: 3/8 in.

• Main

o Tethered to a bulkhead in the upper airframe and a bulkhead on one end of the coupler

• Drogue

o Tethered to a bulkhead in the lower airframe and a bulkhead on one end of the coupler

• Used to connect the upper and lower airframes with the coupler

• Serves as harnesses for the drogue and main chutes

Eyebolts and D-Links (4x)

• Zinc-coated steel

• ¼ in. Eyebolts

• ¼ in. D-Links

• Three eyebolts are mounted on a bulkhead and one to the motor mount

o Each eyebolt is accompanied by a d-link

• Serves to tether the recovery harnesses to the airframes

Propulsion Subsystems: Frame

Centering Rings (2x)

• G10 Fiberglass

• OD: 3.9 in.

• ID: 2.25 in.


• Bolster the motor mount within the airframe

Motor Mount

• Blue Tube

• Length: 17 in.

• OD: 2.25 in.

• ID: 2.2 in.

• Retains and secures the motor inside the lower airframe

Tailcone

• Polystyrene

• Ogive

• Length: 8 in.

• Front Diameter: 4 in.

• Rear Diameter: 2.2 in.

• Surrounds and protects the motor mount and motor while decreasing the drag of the


launch vehicle

Propulsion Subsystems: Motor

Aerotech K695

• Reloadable

• Propellant Weight: 903 grams

• Average Thrust: 695 N

• Total Impulse: 1514 Ns

• Burn Time: 22 s

• Allows the launch vehicle to achieve a simulated apogee of 6062 ft.

Motor Casing

• Length: 16.8 in.


• Provides the frame for the motor.

• Tethered to the recovery harness in the lower airframe of the launch vehicle

Retention Cap

• Used to fasten the motor to its motor casing

3.1.4 Characteristics, Evaluation, & Verification Metrics

Vehicle System or Subsystem

Evaluation of Performance by Component

Verification

Fins The fins' performance will be judged on whether or not they provide the stability and drag simulated in the design of the rocket, can withstand the forces of high-powered flight and recovery of the rocket, and can deliver the rocket to the target altitude.

The verify that the fins have accomplished these goals, data about the drag coefficient and stability of the rocket after the test and subscale flights will be collected. Post-launch inspection of the fins will take place.

Nose Cone The nose cone's performance will be judged on if the drag coefficient matches the drag simulated in the design and by whether or not it can withstand the forces of high powered flight and recovery.

Stress test of the nosecone will be carried out to determine it's strength and data collected from the subscale and test flight will determine its drag coefficient.

Body Tubes The body tubes' performance will be evaluated by their strength and by the drag coefficient they achieve.

Stress tests will determine the strength of the tubes and data collected from the test and subscale flights will determine if it achieved the desired drag coefficient.

Coupler The performance of the coupler is evaluated by its strength and by whether or not it achieves the desired drag coefficient that the team simulated.

Stress tests will determine the strength of the coupler and data collected from the test and subscale flights will determine if it achieved the desired drag coefficient.


Payload Frame The performance of the payload frame will be evaluated by its ability to withstand the forces of high-powered flight and recovery and by its ability to provide a suitable housing for the payload of the rocket.

Stress test of the materials used for the frame will be conducted. Test fitting of the payload on the frame will be conducted.

Payload Electronics

The performance of the payload electronics will be evaluated by the accuracy and precision of the telemetric data it transmits.

Ground tests of the payload and the test flight will verify that the payload can function and provide precise, accurate data about the telemetry of the rocket.

Altimeter Bay The bay's performance will be dependent on its ability to safely house the altimeters and their wiring during high-powered flight.

Stress test of the materials used in the bay will verify that it is robust enough for high-powered flight.

Altimeters The performance of the rocket's altimeters will be dependent on their ability to accurately record the altitude of the rocket.

Ground tests of the altimeter will verify that they function correctly and precisely.

Black Powder Charges

The performance of the black powder charges will be judged upon their ability to successfully break the shear pins holding the rocket together and allow the body tubes to separate and allow the chute to deploy.

Ground tests of the recovery system will include a black powder charge test to ensure that the size of the charges selected can successfully separate the body tubes of the rocket.

Drogue Chute The performance of the drogue chute will be evaluated by if it can slow the descent of the rocket by the amount simulated by the design team.

Information from the subscale and full-scale test flights will verify that the drogue is of adequate size and can slow the rocket by the desired speed.

Main Chute The performance of the rocket will be judged by its ability to slow the descent of the rocket enough to allow all components of the rocket and payload to be recovered safely.

Information gathered from simulations and the subscale flight will verify the necessary size of the Main chute to ensure the rocket can be recovered safely.

Recovery Harness and Eyebolts

The performance of the recovery harness ad eyebolts that attach the harness to the rocket is dependent on their tensile strength and whether they are robust enough to withstand the separation of the body tubes upon ejection.

Stress tests of both components and research into their max loads along with comparison of this information to the forces they will experience during ejection will allow the team to verify that they are strong enough to withstand the separation of the rocket.

Motor mount/Engine Cap/Centering Rings

The performance of these components is evaluated by whether or not they can withstand the heat and force generated by the motor during the ignition and burn phase

Stress test and research about the physical limitations of the materials used for these components will allow the team to verify that the motor mount, engine cap and centering rings are all robust enough to withstand the heat and force created by the motor as it burns.

Engine The performance of the engine will be evaluated by its ability to deliver the rocket to the desired/simulated altitude.

The full-scale test flight will allow the team to verify if the engine provides the correct thrust to deliver the rocket to the desired/simulated altitude.

3.1.5 Verification Plan & Status

Requirement Feature to satisfy requirement Verification

1.1. The vehicle shall deliver the science or engineering payload to an apogee altitude of 5,280

A combination of the design of the rocket and appropriate rocket motor, as designed in

The rocket will be test flown to ensure all components of the rocket will work in conjunction to


feet above ground level (AGL).

RockSim will provide the appropriate thrust, weight, and drag relationship to allow the rocket to attain but not exceed 5,280 ft.

attain, but not exceed, the altitude of 5,280 ft.

1.2. The vehicle shall carry one commercially available, barometric altimeter for recording the official altitude used in determining the altitude award winner. Teams will receive the maximum number of altitude points (5,280) if the official scoring altimeter reads a value of exactly 5,280 feet AGL. The team will lose two points for every foot above the required altitude, and one point for every foot below the required altitude. Any team is eligible for the award as long as their rocket remains below an altitude of 5,600 feet AGL.

One Perfectflite Stratologger 100 altimeter, along with a redundant Perfectflite Stratologger 100 altimeter.

Within the payload bay of the rocket, a section will be provided to contain the barometric pressure altimeter. The rocket will be test flown to ensure it does not exceed 5,600 feet.

During the design phase of the payload project, a separate section of the bay will be designed specifically carry a barometric pressure altimeter. The rocket will be designed to reach but not exceed 5,280 feet. Two Perfectflight SL100 altimeters will be used.

1.3. The launch vehicle shall be designed to be recoverable and reusable. Reusable is defined as being able to launch again on the same day without repairs or modifications.

The rocket will utilize a parachute recovery. The team will be able to quickly "re-build" the rocket and prep it for another immediate flight.

Ground tests and utilization of a post-launch checklist will ensure that the parachute can safely recover the rocket and that the team can quickly re-prep the rocket for flight.

1.4. The launch vehicle shall have a maximum of four (4) independent sections. An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute.

The rocket is made of three independent sections: an upper body tube, a coupler, and a lower body tube, all tethered together.

The launch vehicle design consists of only three independent sections.

1.5. The launch vehicle shall be limited to a single stage.

The rocket will use an AeroTech K695R motor for propulsion, a single stage motor.

Research on the AeroTech K695R motor has been conducted to ensure it is a single stage.

1.6. The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours, from the time the Federal Aviation Administration flight waiver opens.

The team will be able to prepare the rocket for launch within two hours and will be ready for launch.

Practice drills of the preparation of the rocket before flight will be held until the team can complete the preparation of the rocket in less than two hours.

1.7.The launch vehicle shall be capable of remaining in launch-

All critical on-board components will have a power source, which

Ground tests will ensure that the electrical systems on board can


ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component.

will last at least double the required inert time on the pad and time in the air

function after two hours of waiting on the pad.

1.8.The launch vehicle shall be capable of being launched by a standard 12-volt direct current firing system. The firing system will be provided by the NASA-designated Range Services Provider.

The rocket will utilize an igniter that can be lit with a 12-volt direct current firing system.

Ground tests will ensure that the igniter is capable of being lit with a 12-volt direct current firing system.

1.9. The launch vehicle shall require no external circuitry or special ground support equipment to initiate launch (other than what is provided by Range Services).

The launch of the rocket and ignition of the igniter will only require the equipment provided by the NASA range services.

Ground tests of the ignition system will ensure that the rocket can be launched with no external circuitry or support aside from that provided by the range services.

1.10. The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR), Tripoli Rocketry Association (TRA), and/or the Canadian Association of Rocketry (CAR).

An AeroTech K695R motor; an APCP, NAR certified motor.

The team has completed research on the motor to ensure that it is APCP and NAR certified.

1.10.1. Final motor choices must be made by the Critical Design Review (CDR).

1.10.2. Any motor changes after CDR must be approved by the NASA Range Safety Officer (RSO), and will only be approved if the change is for the sole purpose of increasing the safety margin.

The SLI team will decide on the final motor choice before the CDR, and if needed, any new motor selections will be sent to NASA for review with related safety information regarding the team's change in motor.

The team will use simulations and the subscale flight to determine which motor will be best suited for the full-scale flight.

1.11. Pressure vessels on the vehicle shall be approved by the RSO and shall meet the following criteria:

1.11.1. The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating Pressure) shall be 4:1 with supporting design documentation included in all

The SLI team will not be utilizing pressure vessels of any kind aboard any portion of the rocket.

N/A


milestone reviews.

1.11.2.The low-cycle fatigue life shall be a minimum of 4:1.

1.11.3. Each pressure vessel shall include a solenoid pressure relief valve that sees the full

1.11.4. Full pedigree of the tank shall be described, including the application for which the tank was designed, and the history of the tank, including the number of pressure cycles put on the tank, by whom, and when.

1.12. The total impulse provided by a Middle and/or High School launch vehicle shall not exceed 2,560 Newton-seconds (K-class).

The AeroTech K695R motor's impulse will not exceed 2,560 Newtons of thrust.

Research has been conducted to ensure that the rocket has a total impulse below 2,560 Newtons.

1.13. All teams shall successfully launch and recover a subscale model of their rocket prior to CDR. The subscale model should resemble and perform as similarly as possible to the full-scale model; however, the full-scale shall not be used as the subscale model.

A subscale will be designed that to be proportionally identical to the full scale. This rocket will be completed prior to the CDR.

Team GANTT charts, checklists and references to the full-scale design will ensure that the subscale rocket will function as similarly to the full scale as possible.

1.14.All teams shall successfully launch and recover their full-scale rocket prior to FRR in its final flight configuration. The rocket flown at FRR must be the same rocket to be flown on launch day. The purpose of the full-scale demonstration flight is to demonstrate the launch vehicle’s stability, structural integrity, recovery systems, and the team’s ability to prepare the launch vehicle for flight. A successful flight is defined as a launch in which all hardware is functioning properly (i.e. drogue chute at apogee, main chute at a lower altitude, functioning tracking devices, etc.). The following criteria must be met during the full scale demonstration flight:

Prior to the FRR the final rocket design will be selected and flown to ensure all subsystems work properly. This rocket will be the same rocket flown on launch day of the competition.

To ensure the rocket is not changed in its design from the test flight to launch day, the team will use the team checklist. The checklist will ensure that the rocket is ready for the competition flight in Huntsville, AL. The design team and construction team will work in conjunction to complete the project on time.

1.14.1. The vehicle and recovery system shall have functioned as

To attain a successful flight the bottom section of the rocket will

Ground tests of the separation of the rocket will be conducted to


designed. separate at the coupler upon reaching apogee and release the drogue chute. At 500 feet, the main chute will deploy from the upper half, allowing for safe recovery of the rocket.

ensure that the recovery system can properly eject from the rocket and open to allow for a safe recovery.

1.14.2.The payload does not have to be flown during the full-scale test flight. The following requirements still apply:

1.14.2.1. If the payload is not flown, mass simulators shall be used to simulate the payload mass. 1.14.2.1.1.The mass simulators shall be located in the same approximate location on the rocket as the missing payload mass.

After the rocket payload section has been constructed, the design team will create a dummy payload with equivalent mass and roughly equivalent mass distribution to be placed within the rocket if a scenario in which the real payload cannot be flown arises.

The actual and dummy payloads will be constructed in parts. At every step of the construction process, the two versions of each section will be weighed to ensure they maintain equivalent mass.

1.14.2.2. If the payload changes the external surfaces of the rocket (such as with camera housings or external probes) or manages the total energy of the vehicle, those systems shall be active during the full-scale demonstration flight.

The payload will not change the external surface of the rocket.

N/A

1.14.3.The full-scale motor does not have to be flown during the full-scale test flight. However, it is recommended that the full-scale motor be used to demonstrate full flight readiness and altitude verification. If the full-scale motor is not flown during the full-scale flight, it is desired that the motor simulate, as closely as possible, the predicted maximum velocity and maximum acceleration of the launch day flight.

The motor used during the full-scale test flight will be the AeroTech. K695R, the same motor the rocket will utilize during the final flight in Huntsville, AL.

The team, compiling data from the subscale and simulations, will be able to decide on a final motor before the FRR.

1.14.4.The vehicle shall be flown in its fully ballasted configuration during the full-scale test flight. Fully ballasted refers to the same amount of ballast that will be flown during the launch day flight.

Based on simulations and designs of the rocket, the final ballast of the rocket will be decided before the FRR and flown on the test launch day as well as the final launch day.

Simulation information and information from the subscale launch will allow the team to ascertain a final launch ballast that will remain constant through testing and competition flight.

1.14.5. After successfully completing the full-scale demonstration flight, the launch vehicle or any of its components

Any necessary changes to the rocket after the full-scale test flight shall be reported for approval by the NASA RSO.

Before any proposed changes can be applied to the rocket, the team manager will ensure the request is sent to the NASA RSO


shall not be modified without the concurrence of the NASA Range Safety Officer (RSO).

for review.

1.15.1. The launch vehicle shall not utilize forward canards.

The rocket lacks the application of forward canards.

The rocket is designed to reach altitude using only the single AeroTech K695R motor.

1.15.2. The launch vehicle shall not utilize forward firing motors.

The rocket does not utilize forward firing motors.

The rocket is designed to reach altitude using only the single AeroTech K695R motor.

1.15.3. The launch vehicle shall not utilize motors that expel titanium sponges (Sparky, Skidmark, MetalStorm, etc.)

AeroTech K695R; a motor that does not expel titanium sponges.

Research on the components of the AeroTech K695R motor has been conducted to ensure it does not expel titanium sponges.

1.15.4. The launch vehicle shall not utilize hybrid motors.

A single, APCP based AeroTech K695R motor. No hybrid motor of any kind will be used.

The rocket has been designed to exclusively house the AeroTech K695R.

1.15.5. The launch vehicle shall not utilize a cluster of motors.

A single AeroTech K695R motor will be utilized for launch.

The rocket is designed to exclusively house a single AeroTech K695R.

1.15.6. The launch vehicle shall not use motor ejection as a primary or secondary means of deployment.

The ejection system will consist of two black powder charges (and two redundant back-up charges) hooked up to an altimeter in the coupler. The top and bottom sections of the rocket will each contain a charge and back-up charge. These altitude-triggered charges will induce the separation of the rocket.

Ground tests will be performed to ensure that the ejection system can successfully break the shear pins holding the rocket components together and separate the rocket.

3.1.6 Severity, Likelihood, & Mitigation of Risks

Risk Likelihood Impact Value

Mitigation

The rocket and/or payload is not constructed on time and thus, cannot fly in the competition.

Low High The team will carefully follow GANTT charts, use checklists and be aware of deadlines to complete the project on time.

The final construction of the rocket fins cannot withstand the forces of flight and break off. The flight is rendered invalid.

Low High The team will gather information from the subscale flight and simulations to determine the best material, shape, size, and thickness of fin to ensure the fins function correctly during flight.

The rocket body sections fail to separate during flight. Flight is rendered invalid.

Moderate High Ground tests will allow the team to select the most ideal combination of shear pin and black powder charge size to ensure the body tubes separate during flight.

During ejection the parachutes fail to unfurl from their Kevlar heat shields and properly open.

Low High The heat shields and parachutes will be folded with the "burrito" style. Ground tests of the folding style will ensure the parachute can unfurl from the heat shields and catch air.

Upon separation of the body tubes, the recovery harness snaps from the force of ejection.

Low High The recovery harness will be made of Kevlar cording and steel D-links to ensure it can withstand the force of ejection.


Ground tests will investigate the strength of these materials.

During construction, as the fin slots are being cut in the body tubes, the slots are not cut correctly increasing the likelihood of the fins wobbling or breaking off in flight.

Moderate Low Any imperfect cuts in the body tubes made to house the fins can be partially filled with epoxy or expanding foam to allow for a smooth finish and tight seal on the fin slots.

The rocket does not achieve the target altitude.

Moderate Moderate Information from the subscale flight will help the team create a rocket with the correct thrust, drag, and weight to achieve the target altitude simulated.

The payload malfunctions in flight and does not perform the task it was designed to do.

Low Moderate Ground tests of the electrical systems will be performed to ensure all electrical components of the payload bay function.

3.1.7 Components & Risks/Impact

Any and all possible delays or risks that could affect the project have been included in the timeline of the GANTT charts. Ample time has been allotted to allow team members to fix potential delays or risks in the timeline of the project. The payload, rocket construction and design teams will work in conjunction to prevent as many delays from happening as possible. Strong communication will prevent lapses in information between teams. A steady stream of input and multiple perspectives on problems faced by any team will allow for the most efficient and safe solution to a problem possible.

3.1.8 Manufacturing, Verification, Integration, & Operations

The vehicle will be designed and constructed according to a GANTT chart created by the team project manager. Time will be allotted to account for delays in the product completion. The vehicle has been designed in RockSim and simulated to ensure it has a proper drag coefficient, weight and other vehicle components. The design team will send the design to the construction team for the manufacturing of the rocket. All materials used in the vehicle will be tested to ensure they are strong enough to withstand the forces of high-powered flight. Once the rocket has been constructed, ground test of all in flight procedures will begin. Ejection tests will be completed to ensure the rocket can separate during flight. After the rocket has been deemed viable for high-powered flight, the team will practice and memorize the pre-launch procedure to prepare the rocket for flight. This includes all safety procedures and post-launch operations.

Airframe

• Pre-manufactured 4-inch BlueTube body tubes

• A piece of BlueTube will be cut for component strength tests

• Tubing will be cut to length with a hand saw

• Slots in the bottom of the lower airframe will be cut

• Shear pin holes will be drilled

Motor Mount


• Tubing will be cut to length with a hand saw

• Pre-manufactured BlueTube

• Strength tests as well as research on its heat resistance capabilities will be conducted on the motor mount tube

• Centering rings that attach to the motor mount will be cut from G10 fiberglass with a drill press

o Rings will undergo strength tests to ensure they can withstand the forces of high-powered flight

o Epoxied to the motor mount and to the lower body tube

*The altimeter bay will be made of the Blue Tube coupler compliment to the 4-inch body tubes.

Fins

• Cut from 0.05-inch thick pre-manufactured carbon fiber

• Carbon fiber sheets will undergo strength tests

• Inserted into fins slots on the lower body tube and epoxied to the motor mount and lower body tube

Nosecone

• Pre-manufactured, plastic ogive nosecone

• Tested to ensure it can withstand the forces of high-powered flight

• Four holes will be drilled into the bottom of the nosecone

• Screwed onto the upper airframe

Payload Frame

• Will be designed and 3-D modeled using Autodesk Inventor

• Will be exported to the lab's 3-D printers and printed with ABS plastic

• Components of the payload will be dry fitted on the sled and the plastic will be tested for robustness

• Will be constructed and fit into the top section of the rocket

* A similar design and construction process will occur with the altimeter bay within the coupler. Once within the rocket, all electrical systems will undergo a systems test to ensure all electronics function.

Recovery Harness

• Two 30-foot sections of 3/8 inch tubular Kevlar

o Kevlar has more tensile strength than what is necessary to withstand the ejection of parachutes from the body tubes

• Attached to rocket with 1/4 inch steel eyebolts and D-links

o Eyebolts and D-links each have a tensile strength far exceeding the forces they will experience during the separation of the rocket

To ensure all components of the rocket can function after two hours of sitting on the launch stand and that all components of the rocket can handle the forces of ejection and separation, a ground test of the


full launch procedure including a full electrical system run and ejection test will occur.

3.1.9 Confidence & Maturity of Design

Multiple changes and augmentations have been made to the final design. All changes are based off of measurements and calculations made within the facilities of the Plantation High School Aerospace Program of store-bought materials and previously constructed SLI rockets. Based on the changes made to the launch vehicle regarding size, mass, and simulations, the design in within 85% - 90% accuracy.

3.1.10 Dimensional Drawings∗

Figure 4 Recovery system dimensional sketch

∗ All dimensions are in inches

Figure 3 Launch vehicle dimensional sketch


Figure 5 Propulsion system dimensional sketch

3.1.11 Electrical Schematics for Recovery System

3.1.12 Mass Statement

Launch Vehicle (no motor): 4.4 kg

Launch Vehicle (with motor): 5.9 kg

The launch vehicle weighs 4.4 kg without its motor, and 5.9 kg with it. Separate mass values for each system and subsystem of the launch vehicle are listed below:


Structural System

Total Mass: 1842.5 g/1.8 kg

Airframe

Component Mass (grams) Basis

Nosecone 514.7 Simulated in RockSim.

Upper Airframe 406.7 Simulated in RockSim.

Lower Airframe 330.4 Simulated in RockSim.

Bulkhead (2x) 46.6 Simulated in RockSim.

Coupler 161.4 Simulated in RockSim.

Tailcone 272.1 Simulated in RockSim.

Total: 1778.5

Guidance


Fins 60.0 Simulated in RockSim.

Launch Buttons (2x) 2.0 Measured within facility.

Total: 64.0

Payload System

Total Mass: TBD

Frame

TBD – The mass of the frame will be calculated upon finalization of the payload frame design using 3D design software and later by hand.

Electronics

TBD – The mass of the electrical components will be calculated by hand upon obtaining each component.

Recovery System

Total Mass: 1350g/1.4kg

Altimeter Bay



Altimeter Sled 50.4 Measured within facility.

Altimeter (2x) 20.0 Measured within facility.

9v Batteries (2x) 60.0 Measured within facility.

¼ in. Threaded Rod (2x) 70.0 Measured within facility.

¼ in. Lock Nuts and Washers (20x)

5.0 Measured within facility.

Bulkhead (2x) 46.6 Simulated in RockSim.

Total: 252.0

Black Powder


Black Powder Charge (Main; 2x)

2.5 Calculated using online black powder calculator.

Black Powder Charge (Drogue; 2x)

2 Calculated using online black powder calculator.

E-match (4x) 1.5 Measured within facility.

Total: 15.0

Chutes/Harnesses


Main Chute 396.9 Giant-Leap Online Store

Drogue Chute 153.1 Giant-Leap Online Store

Recovery Harness (Upper) 134.0 Measured within facility.

Recovery Harness (Lower) 134.0 Measured within facility.

Eyebolt (3x) 35.0 Measured within facility.

D-Link (4x) 40.0 Measured within facility.

Total: 1083.0

Propulsion System

Total Mass: 1988.4g/2kg

Frame


Centering Ring (2x) 46.6 Simulated in RockSim.

Motor Mount 146.2 Simulated in RockSim.

Tailcone 272.1 Simulated in RockSim.

Total: 464.9


3.2 Recovery Subsystem

Analysis

The parachute subsystem will be constructed in the following manner:

One end of the first 30 ft. 3/8ths inch tubular Kevlar harness will be d-linked to the motor casing and the opposite end to the coupler/altimeter bay. The second 30 ft. 3/8ths inch tubular Kevlar harness will be d-linked to a fiberglass bulkhead in the upper half of the launch vehicle and to the coupler/altimeter bay, respectively. The Giant-Leap TAC-60 main parachute will be attached to the upper portion of the recovery harness in the upper body tube, and vice versa for the Giant-Leap TAC-24 drogue parachute. Upon reaching apogee, the dual Perfectflight Stratologger altimeters ignite the 2-gram ejection charge in the aft end of the launch vehicle to break the 1/16 in. shear pins that keep the aft end of the vehicle attached to the coupler/altimeter bay. Upon reaching an altitude of 500 feet, the altimeters fire the main parachute ejection charges, which again break the shear pins on the upper half of the vehicle to deploy the main parachute. The second altimeter and charges act as a redundancy system to ensure parachute deployment.

Major Components

The recovery subsystem is composed of one Giant-Leap TAC-60 main parachute, one Giant-Leap TAC-24 drogue parachute, two 30 ft. 3/8ths in. tubular Kevlar, 2 Perferflight Stratologger altimeters, and 4 black powder ejection charges. In order to ensure the robustness of the system, the team will perform a ground ejection charge test. Multiple trials will be undergone to ensure the success of the vehicle once actually in flight, and if the grounded ejection test were to fail, proper adjustment to the design will be implemented.

Motor


Aerotech K695R 903.0 Simulated in RockSim.

Motor Casing 603.0 Simulated in RockSim.

Retention Cap 17.5 Measured within facility.

Total: 1523.5

Mass Statement Discussion

Mass Margin

Based off of simulation conducted with RockSim, there is an 8 kg margin before the thrust-to-weight ratio of the launch vehicle becomes equivalent to 5:1, and becomes too heavy to achieve a stable flight off of the launch pad.

Reserved Mass

Current simulations demonstrate an overshot apogee due to planned mass. A minimum of 1.02 kg is held in reserve in order to decrease the apogee of the launch vehicle to its target of 6,005 ft. Vehicle components, which are expected to fill the reserved mass, include epoxy, silicone caulking, and other adhesive substances. The mass is also reserved for the intended payload frame and electronics, which have not been weighed by hand or simulated through software.


3.3 Mission Performance Predictions

3.3.1 Mission Performance Criteria

Below are all the mission performance criteria of the launch vehicle:

! The launch vehicle can achieve its target apogee of 6005 ft. with a stable flight path.

! The launch vehicle can achieve its target apogee of 6005 ft. and its payload may successfully operate.

o The payload is capable of recording and transmitting as many telemetric data samples per second as it can.

! The AeroTech K695R motor allows the launch vehicle to achieve its target apogee of 6005 ft. and provide the launch vehicle with an average upward thrust of 156 lbs. and total impulse of 340.4 lbf-s.

! The recovery system of the launch vehicle performs as intended:

o Drogue chute deployment at apogee of 6005 ft.

o Main chute deployment at 500 ft. AGL during descent

! The launch vehicle is capable of landing with both drogue and main chutes deployed, and all sections land with a kinetic energy of less than 75 ft-lbs individually.

3.3.2 Simulations


Figure 6 Flight profile: At launch stand


Figure 7 Flight profile: At 500 ft. AGL/Main deployment


Figure 8 Flight profile: At apogee/Drogue deployment


Figure 9 Flight profile: At landing

Altitude Predictions/Simulated Vehicle Data

Altitude: 6000 ft.


Figure 10 Data values from RockSim

Simulated Velocity, Acceleration, and Altitude at Different Flight Events

Drogue Main Landing Maximum

Velocity (ft./s.) 6 70.8 -28 755.6

Acceleration (ft./s2) -32 -32 -32 465.4

Altitude (ft.) 6005 500 0 6005


Motor Thrust Curve

3.3.3 Stability Margin/Center of Pressure (CP)/Center of Gravity (CG)

Figure 11 Launch vehicle w/ CP & CG, without motor (from RockSim)


Figure 12 Launch vehicle w/ CP & CG, with K695R motor (from RockSim)

Center of Gravity

(In. from nosecone)

Center of Pressure

(In. from nosecone)

Stability

(Calibers)

Without Motor 37.3 53 3.7

With Motor 45.7 52.1 1.9

3.3.4 Kinetic Energy Calculations

Section Kinetic Energy (ft-lbs)

Upper Airframe + Nosecone 23.3

Coupler 8.6

Lower Airframe 19.0

3.3.5 Drift Calculations

Wind Speed in MPH Drift from launch stand in feet

0 0 5 392

10 786

15 1507

20 1870


3.4 Interfaces & Integration

• The payload will easily integrate into the vehicle by being placed within its own compartment exactly 14" of the entire length.

• The payload will use a wireless interface to communicate with the ground through the XBee Pro 900 RPSMA. This component will send data collected in flight by the sensors on the payload to a corresponding XBee Pro 900 RPSMA on the ground, which receives this data, then inputs it into an application for display and organization.

3.5 Safety

Preliminary Checklist

1. Unload rocket and completely disassemble

2. Go through, on a system level and ensure no components were damaged since the last flight or during travel.

3. Detach the D-links holding the Recovery harness and parachutes and remove the harness from the rocket.

4. Z-fold the parachutes and their Kevlar heat shields.

5. Place the Z-folded heat shields and parachutes within a protective blanket and "burrito"-wrap the blanket.

6. Unscrew the altimeter bay and inspect the internal components of the bay. Check if new batteries are necessary.

7. Install new batteries if necessary and test the manual switches of the altimeter bay.

8. Reassemble the bay.

9. Wire black powder charges to their respective sides of the coupler.

10. Wire redundant back-up charges to their respective sides of the coupler.

11. Reattach the D-links of the recovery harness to the coupler of the rocket.

12. Close the rocket, sliding the body tubes onto the coupler.

13. Insert shear pins into the holes in the coupler and body tubes.

14. Remove nose cone and insert payload.

15. Screw nose cone onto the rocket.

16. Mentor constructs the rocket's motor and ejection charge.

17. Attach the bottom D-link of the recovery harness to the eyebolt on the top of the engine casing.

18. Insert motor in motor casing and screw on engine cap

19. Clear any dry brush or other flammable material from under the rocket.

20. Place the rocket onto launch stand.

21. Turn on electrical systems of the rocket using a manual switch located on the side of the body of the rocket.

22. Unsheathe igniter and insert within the engine ensuring it is fully threaded inside the rocket and is in contact with the top section of the hollow core of the rocket.

23. Tape down igniter to the side of the rocket.

24. Attach igniter to electrical launch ignition system.

25. Retreat to safe distance as listed by the minimum safe distance table provided by the NAR.

26. Arm ignition system.

27. The NAR level 2 mentor will announce with a 5 second countdown when the launch will begin.

28. Launch.

Safety Officer

The Plantation High School Team 1 Safety Officer is Ian, who is responsible for ensuring all team members are cognizant of the safety guidelines, requirements, and the proper usage of the tools and facilities.

Preliminary Hazard Analysis

Hazard Likelihood Severity Mitigation/Verification


Improper use of the band saw results in a user cutting his/her hand.

Low Moderate Educate all team members on the correct usage of the band saw and have them use proper PPE's while using the band saw.

When cutting a material with the band saw, shards or particles of the cut object enter the user's eye or are inhaled.

Low Moderate Educate all team members on proper PPE use while working with the band saw.

When cutting with a razor, slippage results in the user cutting themselves or others.

Low Low/Moderate Ensure all team members are using sharp razors, cut away from themselves and never cut while another person is within a circle around them with a radius of the user's arm.

When using the 3-D printer to make a print, the user burns themselves.

Low Low Ensure the team members know to never touch the bed of the 3-D printer while it is heating up, printing or immediately after a print.

While drilling a hole with a power drill, the user accidently cuts themselves or others,

Low Moderate Educate the team members on the proper use of the power drill to ensure appropriate action is taken when using the drill.

While sanding a material with the power sander, the user loses grip and abrades their

Low Low Ensure all team members are focused on the task at hand while sanding and are wearing gloves.


hand on the sander.

While sanding a material, dust or particles of the material gets kicked into the eye of the user.

Moderate Low Ensure while sanding the user is always wearing safety glasses and has a vacuum running next to the sander to pick up a loose particulate.

While mixing or applying epoxy, some drips onto the users skin or is accidently rubbed into the user's eye, causing irritation.

Low Low All team members will wear gloves when working with epoxy and will rinse skin or eyes thoroughly if epoxy comes into contact with them.

When handling soft carbon fiber fabric, it comes into contact with the user's skin causing irritation.

Moderate Low All team members will handle carbon fiber fabric, only after putting gloves on.

While cutting a hole with the drill press, improper use results in a user cutting themselves or others.

Low Moderate Team members will always stay a safe distance from the drill press and will never place their hands or other parts of their body underneath the drill while it is running.

Failure Mode Analysis

Failure Mode Likelihood Severity Mitigation

Faulty wiring or a dud igniter results in a failure of the black powder charges, necessary to

Low High In preparation for a failure such as this, the altimeter bay will house a


eject the parachutes, to fire.

back-up set of altimeters and black powder charges, with a separate power supply.

Due to incorrectly sized shear pins, the body tubes of the rocket fail to separate and the rocket cannot safely recover.

Low High Using checklists, the team will verify that the correct shear pins have been selected for use in flight

Miscommunication between team members or misallocation of work results in the project not finishing on time.

Moderate High The team will host weekly meetings to discuss project completion and work allocation to ensure everything I finished on time. GANTT charts and checklists will help team members stay on track when working.

Moisture from the air (or precipitation) gets within the altimeter or payload bays and shorts the electrical systems before launch.

Low Moderate The team will never fly in the rain and will keep the altimeter and payload bays sealed from the outside environment to keep any moisture out of the rocket.

While the black powder charges are being made, moisture is absorbed by the charge, which keeps the charge from igniting at the planned separation time.

Low High The NAR mentor will not create the black powder ejection charges if the humidity in the air is too great and never if there is a water source very near by.


Jagged cuts on any portion of the rocket due to errors in cutting (sloppiness, lack of focus, etc.), prevent the rocket from attaining the necessary drag coefficient to achieve the target altitude.

Moderate Low All team members will show the utmost focus when cutting; however if an error should occur, any grooves or spaces on the surface of the rocket will be filled with wood filler, sanded level and smooth, and painted over.

The altimeters fail to receive power from their power sources because the batteries are shaken loose during flight.

Moderate High The batteries in the altimeter bay (and payload bay) will be contained within their own housing and will be zip-tied down very firmly to the sled to prevent any movement during flight.

The recovery harness fails to unfurl fully, because it knots or cannot uncoil, keeping the parachutes from ejecting and recovering the rocket.

Low High The recovery harness will be z-folded to prevent any knots or catches from forming. The z-folded recovery harness will then be wrapped with only one layer of thin masking tape to. This tape will keep it folded during flight, but will easily break under the force of the ejection charges.

As the parachute ejects from the rocket, the shroud lines become tangled. The tangled lines prevent the parachute from fully

Low Moderate The shroud lines will be attached to the recovery harness with a swivel barrel and will be z-folded to


opening and result in the rocket coming down faster than planned. This speed may damage the rocket itself or the payload it carries.

prevent any tangling.

Material Hazards

Risk Mitigation Verification When mixing epoxy for the use of attaching portions of the rocket or hardening soft carbon fiber, users can inhale dangerous fumes.

Epoxy will only be mixed under the classroom fume hood and with the use of facial masks.

A safety briefing will be held, with all team members, to explain the proper use of epoxy and other materials and facilities.

Mixed epoxy can drip onto user’s hand, causing skin damage.

When mixing and applying epoxy, gloves will be worn

A safety briefing will be held, with all team members, to explain the proper use of epoxy and other materials and facilities.

Microfibers of carbon can irritate the skin of users when handling soft carbon fiber fabric.

Gloves will be used at all times when handling carbon fiber

A safety briefing will be held, with all team members, to explain the proper handling of carbon fiber.

When handling hardened carbon fiber, sharp edges can cut user’s hand.

Gloves will be used at all times when handling carbon fiber

A safety briefing will be held, with all team members, to explain the proper handling of carbon fiber.

When painting the launch vehicle, users may inhale dangerous fumes.

All painting will be performed outside and with the use of facemasks.

A safety briefing will be held with all team members explaining the proper use of spray paint.

When handling cut fiberglass, sharp edges may cut users.

Glove will be worn at all times when handling fiberglass.

A safety briefing will be held, with all team members, to explain the proper handling of fiberglass.

Facility Hazards

Risk Mitigation Verification Improper use of the DaVinci milling machine can result in user injury

Users will never place any body parts inside the machine during milling.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the DaVinci.

Touching the bed of the 3-D printer while it is heating up or in use can cause burns.

Users will never touch the bed of the 3-D printer while it is printing or heating up

Team members will be administered a safety test to ensure all members are aware of the correct


handling of the3-D printer.

Improper use of a razor can lead to a user cutting oneself or nearby team members.

Users will only cut away from themselves and at a safe distance from other team members.

Team members will be administered a safety test to ensure all members are aware of the correct handling of razors.

Improper use of the handsaw can result in a user cutting oneself.

Users will wear gloves and carefully use the handsaw.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the handsaw.

When using the band saw, slippage or a lapse in attention can result in serious bodily harm to a user.

Users will never wear headphones or engage in other distracting activities while using the band saw.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the band saw.

When cutting with the band saw, fragments of the material being cut can fly into a user's eye.

Users will always wear safety goggles or full facial masks when cutting with the band saw.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the band saw.

When grinding or cutting with the dremel tool, a user may cut oneself or a team member nearby.

Users will only use the dremel on the appropriate speed setting and will always be aware of those around them.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the dremel tool.

When grinding or cutting with the dremel tool, fragments of the material being grinded or cut can fly into a user's eye.

Users will always wear goggles or full facial masks when cutting or grinding with the dremel tool.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the dremel tool.

When drilling with the power drill, slippage can result in a user cutting oneself.

Users will be undistracted and drill steadily while using only appropriate speed and pressure.

Team members will be administered a safety test to ensure all members are aware of the correct handling of the power drill.

Safety Code Compliance (NAR high power rocketry safety code)

1. The Plantation high School SL Team (1) will only handle/possess rocket motors size _____ and lower, as licensed by the team's mentor, Mr.Vallone.

2. The PHS SL Team will only use lightweight materials such as blue tube, fiberglass, carbon fiber, etc. in the construction of the team's rocket.

3. The PHS SL Team will only use commercially manufactured rocket motors from _______ in the way intended by the manufacturer and will leave them unhampered. Absolutely no flames, smoking, sparks or heat sources will be will be allowed within 25 feet of the motors in the possession of the PHS SL Team.

4. The launch vehicle shall be launched using an electrical launch system. Electric igniters will be used to ignite the motors and will be installed within the motor after the launch vehicle is on the launch stand. The electric launch system will apply a safety interlock in series with the launch switch that will not be installed until the rocket is ready for launch. The launch switch will return to the "off" position when released. All onboard energetics and firing circuits will be inhibited until the launch vehicle is in the launch position.

5. If the rocket fails to ignite after the launch switch is activated, the launch switch will be turned


off. A 60 second countdown will begin, before anyone can approach the rocket.

6. Prior to ignition, the range safety officer will begin a 5 second countdown, with ignition occurring at 1. All spectators and team members will be a safe distance from the rocket (as dictated by the minimum safe distance table from the NAR). The rocket will only be flown when determined stable. All team members will be clear of the launch pad before ignition can occur.

7. The launch vehicle will be launched from a rigid guide rail that is within 20 degrees of vertical, that can guide the rocket until it can reach a safe speed that will ensure a stable flight. All combustible material and dried grass will be cleared from beneath the rocket prior to flight.

8. The total impulse of the motor(s) in the launch vehicle will be ______ , below the maximum total impulse of 40,960 required by the NAR. At liftoff the launch vehicle will not weigh more than one-third of the certified average thrust of the motors being launched.

9. The launch vehicle will not be launched at clouds, airplanes or over spectators. The launch vehicle will not be launched in wind speeds exceeding 20 mph. No flammable or explosive payloads will be on-board the launch vehicle.

10. The rocket will be launched on an open field void of any trees, power lines, buildings or persons that would be hazardous for launch. The launch site will be at least half as wide in it's smallest dimension as the expected maximum altitude of the flight, approximately: ______ ft.

11. The launch pad will be at least 1500 feet from any occupied building or public highway with traffic speed exceeding 10 mph.

12. The launch vehicle will implement the use of a parachute to safely return all portions of the rocket during recovery. Flame retardant Kevlar heat shields or non-flammable wadding will be used to protect the parachute upon ejection.

13. The PHS SL Team will not attempt to recover the rocket should it land in a power line, tree, building or other hazardous area. The rocket will not be flown under conditions where it will likely land in spectator areas or in areas outside the launch site.

Environmental Concerns

Effects of Environment on Launch Vehicle

While on the launch stand, just before flight, rain or moisture in the air could enter the rocket and short the electrical systems. To prevent this, the rocket will never be flown if cloud cover is overhead or if it is raining. All electrical systems will be kept in a bay that is sealed from the open air to ensure no moisture can enter the rocket. While in flight, high winds could weather cock the rocket and result in a flight below altitude. The rocket will be constructed with a stability margin that allows for a stable flight, even through wind, based off data collected from the subscale flight and simulations. While the rocket is recovering, it may collide with a tree, rocket, and body of water or other obstacle and damage the rocket or payload. To avoid this, the launch area will be large enough to ensure no tall obstacles or bodies of water are within the range of the rocket. The rocket will also utilize a parachute to safely recover the rocket.

Effects of Launch Vehicle on Environment

To prevent a fire when the rocket motor ignites and expels hot exhaust behind it, all dry brush or other flammable material will be cleared from beneath the rocket. If an engine or black powder charge malfunctions, bits of propellant or rocket may fall to earth resulting in litter or endangering wildlife. All pieces of the rocket will be collected after every flight.


4 Payload Criteria

4.1 Selection, Design, and Verification

4.1.1 Design at System Level

Selection Rationale

• Sparkfun Redboard

o Improved functionality and lower price from the Arduino Uno R3

• XBee Pro 900

o Optimal choice for wireless communication on the Arduino platform due to immense documentation and technical capability

• Barometric Pressure Sensor Breakout – BMP180

o Performance

! BMP180’s superior range is optimal for the payload experiment

o Price & Ease of Sourcing

! By sourcing many of our parts from the same supplier, small discrepancies in price are made up for through shipping

• ADXL335 – 5V ready triple-axis accelerometer

o Chosen to meet the internal requirement of having separate outputs for the x, y, and z coordinates

o Meets instrument margin of error requirements for the experiment

• Adafruit Ultimate GPS Breakout

o Has a range and accuracy optimal for the experiment, which allows for its use anywhere and the expectation of optimal performance

Custom made payload bay

• Custom manufacture of the payload frame was chosen to fix several technical issues experienced in the past with former designs.

• Tapered rail design

o To avoid structural problems in the past which were due to wobbling caused by the oscillations of the rocket in flight. By tapering up to the top of the rails this design feature should allow for much greater structural stability during flight.

• Single vertical sled design

o Improves modularity as well as to fix aforementioned structural problems (wobble). This design feature allows us to change component sleds easily, which gives the option to easily change experiments, which contributes to reusability.

• Cap design feature

o Included to minimize wobble and to ensure that the main components sled is properly secured in between our rails. This helps minimize the risk of disconnection between


components on the main components sled

• Separate power supply bay

o Attached to the main components bay separately to improve modularity and reusability. By being able to interchange power supply modules it theoretically gives the ability to extend battery life infinitely.

These changes have several benefits apart from fixing previous structural problems.

These include:

o Lower weight in part because of the fully 3d-printed design.

o Increased modularity and reusability.

4.1.2 Payload Subsystems

Electrical Components

Arduino Flight Computer∗

Sparkfun RedBoad

• Used to process the data transmitted from the sensors

• Technical specs

o 14 Digital I/O Pins (6 PWM outputs)

o 6 Analog Inputs

o 32k Flash Memory

o 16MHz Clock Speed

Barometric Pressure Sensor∗

Barometric Pressure Sensor Breakout – BMP180

• Sensor to collect and send pressure data to the flight computer

• Technical Specs

o Range of 300 to 1100 hPa

o Accuracy down to 0.02 hPa in advanced resolution mode

∗ Image courtesy of Sparkfun ∗ Image courtesy of Sparkfun


Wireless Communication Device∗

XBee Pro 900 RPSMA

• Used to transmit data from flight computer to a corresponding XBee Pro 900 AGL at a minimum latency of 500 ms (milliseconds)

• Data received from flight computer is transmitted to a website which dynamically represents the data in real-time

• Connected to the flight computer through an XBee

Shield

• Technical specs

o Fast 156 Kbps RF data rate

o Up to 6 miles (10 km) RF LOS with high gain antennas

GPS Module∗

Adafruit Ultimate GPS Breakout

• Used to give exact position of rocket at any given point

• Technical Specs

o Satellites: 22 tracking, 66 searching

o Position Accuracy: < 3 meters (all GPS technology has about 3m accuracy)

o Velocity Accuracy: 0.1 meters/s

o Warm/cold start: 34 seconds

o Maximum Velocity: 515m/s

o Jammer detection and reduction

Triple Axis Accelerometer

ADXL335 - 5V ready triple-axis accelerometer

• Used to measure the G’s of the rocket in the x, y, and z planes

• Technical Specs

o +/- 3Gs margin of error on measurements

∗ Images courtesy of Sparkfun ∗ Image courtesy of Adafruit


4.1.3 Performance Characteristics, Evaluation, and Verification Metrics

Performance Characteristics & Evaluation

The payload is calibrated on the launch pad in its initial start-up period. This process takes roughly 1 minute to complete. After this is complete the payload is ready to launch. During flight all the data, which the payload records are real-time and low latency. This data is processed by the central flight computer (Sparkfun Redboard) and then sent through an Xbee Pro 900 RPSMA on the payload in-flight to a corresponding Xbee on the ground, at a very low latency. The telemetry data which Xbee on the ground receives is then input into a computer application and displayed on the ground, as well as, streamed to a pre-made website. The team then analyzes all the telemetry data provided by the payload to determine the rockets precise flight characteristics.

Verification Metrics

The accuracy and range tests will be the metric to measure probability of success. If the tests meet their stated margins of error and range, then the probability of success will be high, as defined by the success criteria.

4.1.4 Verification Plan

Verification Matrix

Payload Requirements Design Feature/Solution Means of Verification

The launch vehicle shall carry a science or engineering payload.

Live Telemetry GPS Mapping engineering payload

A Live Telemetry/GPS Mapping payload will be constructed according to design and will be capable of being integrated into the launch vehicle.

Data from the science or engineering payload shall be collected, analyzed, and reported by the team following the scientific method.

XBee Pro 900 data transmitter; data streamed from the payload to the ground will be logged and saved as a hard copy.

The log saved to the computer via XBee Pro 900 will be read and analyzed.

Unmanned aerial vehicle (UAV) payloads of any type shall be tethered to the vehicle with a remotely controlled release mechanism until the RSO has given the authority to release the UAV.

The vehicle will not contain any UAV payloads of any type

N/A

Any payload element that is jettisoned during the recovery phase, or after the launch vehicle lands, shall receive real-time RSO permission prior to initiating the jettison event.

The payload system will not contain any elements to be jettisoned during the recovery phase.

N/A

The payload shall be designed to be recoverable

The payload system’s start values data can be calibrated to launch

Prior to and following each flight, the payload will be


and reusable. pad conditions at the beginning of each launch.

ensured that it is calibrated to launch pad conditions and is ready for another flight.

Verification Plan

o To verify the payload’s measurement and long range transmitting capabilities, a variety of tests will be conducted. These include:

! A range test in which the payload module is taken a specific distance away from the transmitter to test latency and accuracy as distance increases.

! An accuracy test in which the payload is used to measure values for each sensor when the values are already known; thus, the deviation from the correct values will be the calibration error.


4.1.5 Preliminary Integration Plan

Payload Bay

• All the equipment will be mounted on a sled, between two 3D printed rails

o Used to keep the sled in place and upright

• 1” clearance on the top and bottom of the payload bay to separate it from the rest of the rocket

• Rails will have a 3.5” x 1.5” x 1.5” cap screwed on top to keep the sled from moving during flight

• The main components area of the payload bay will be 9” x 3” x 0.5”

• The rails will be 1.5” x 0.5” x 9”, with a 0.25” indentation on the side at 0.5” from each side

• The power supply bay is placed beneath the main electrical area in its own section

• The power supply bay will be 2.5” x 4”


4.1.6 Precision of Instrumentation, Repeatability of Measurement, & Recovery System

Precision of Instrumentation & Repeatability

Instrument Range Precision of Measurement

Sparkfun Redboard N/A N/A

Barometric Pressure Sensor (BMP180)

300 to 1100 hPa 0.02 hPa

Adafruit Ultimate GPS Breakout (746)

Range of satellites

(22 tracking, 66 searching)

Less than 3m


N/A +/- 3 G

XBee Pro 900 RPSMA (WRL-09099)

Up to 6 mi N/A

4.1.7 Drawings & Electrical Schematics

Figure 13 Electrical schematics of payload system (PCB)∗

∗ XBee Pro 900 is connected to the flight computer through the XBee Shield, which will be placed directly onto the flight computer


Figure 14 Electrical schematics of payload system

Figure 15 2D Drawing of payload frame


4.1.8 Payload Operation

• Use Barometric Pressure Sensor to collect pressure data, the data is then sent to the flight computer

• Use GPS module to give exact position of rocket at any given point. This data is sent to the flight computer

• Use Triple Axis Accelerometer to measure the G’s of the rocket in the x, y, and z planes

• Use Sparkfun RedBoard to receive and process all the data, which the sensors acquire

• Use XBee Pro 900 to transmit data coming from flight computer to a corresponding XBee pro 900 on ground at a minimum latency of 500 ms.

• The data received from flight computer is transmitted to a website which dynamically represents the data in real-time

Payload Concept Features and Definition

Science Value

Hypothesis

• Telemetric data can be recorded, transmitted, and displayed in real time from a rocket during flight Payload Objectives

• To record and transmit real-time telemetric data (altitude, air pressure, acceleration in all directions, and precise location (GPS))

• To send the data collected to a website which displays it also in real-time

Flight Computer (Sparkfun Redboard)

XBee Pro 900

Computer AGL & website

Barometric Pressure Sensor

GPS Module

Triple-Axis Accelerometer


Payload Success Criteria • Record and transmit real-time telemetric data (altitude, air pressure, acceleration in all directions, and

precise location (GPS)) • Website displays data acquired from payload in real-time

Test and Measurement, Variables, and Controls

• Tests o Atmospheric pressure tests with a barometric pressure sensor o Location tests with a GPS module o Altitude and rocket motion tests with a triple-axis accelerometer

• Controls o Atmospheric pressure at launch site (Barometric pressure sensor) o Original position of rocket as recorded by the accelerometer and GPS modules

• Variables o Atmospheric pressure as rocket ascends o Position in space relative to original recorded position

Relevance of data

• Atmospheric pressure data o Record and analyze the changes in atmospheric pressure as the rocket ascends

• GPS data o Record the location of the rocket at any given time

• Accelerometer data o Record the orientation of the rocket at any given time

• Accuracy/Error Analysis o Accuracy/error tests will be performed upon obtaining the electrical components of the

payload o The analysis will be completed following the accuracy/error tests

Experiment

• Logic o As the rocket ascends, the data recorded from the instruments should change accordingly.

The changes should follow a predictable curve • Approach

o The position of the rocket as well as the atmospheric pressure changes during flight will be recorded by on-board sensors such as a GPS module, a barometric pressure sensor (BMP 180) and a triple-axis accelerometer (ADXL335)

o The live data collected will be analyzed by the team upon transmission

• Method of Investigation o On the launch pad all the instruments are calibrated and zeroed to launch pad conditions. o As the rocket ascends data from the barometric pressure sensor (BMP180), triple axis

accelerometer (ADXL335), and GPS module is sent to the central flight computer. o The flight computer takes this data and sends it through an XBee Pro 900 RPSMA to a

corresponding XBee on the ground. o The data received from the flight computer is then streamed in real-time to a pre-made

website which displays the telemetry data. Preliminary Process Procedures

• At the launch pad all the instruments are turned on for calibration and for recording the control measurements

• As the rocket ascends, the instruments will collect data and send it to the flight computer, which then uses the XBee Pro 900 to wirelessly transmit the data to a corresponding XBee Pro 900 AGL

• This data is inputted into an application on the receiving computer, which then transmits it in real-time to a pre-made website

• The measurements are the conditions that exist on the launch pad to allow for an accurate measurement each time.


5 Project Plan

5.1 Budget

5.1.1 Launch Vehicle Expenses

Item Quantity Place of Purchase Total Price

Fiberglass Nosecone 1 Rocketry Warehouse $36.00

Polysteyrene Nosecone (Tailcone)

1 Madcow Rocketry $21.95

Carbon Fiber Fins 1 Sollar Composites $44.50

Eyebolts 6 Lowes/Home Depot $13.62

Centering Rings 2 ARR $4.98

Lock Nuts 20 Lowes/Home Depot $2.40

Washer 20 Lowes/Home Depot $2.20

BlueTube Airframe 2 ARR $77.90

BlueTube Coupler 2 ARR $21.90

Carbon Fiber Plate 1 Rockwest Companies $78.99

Fiberglass Sheet (138 in.2) 3 Grainger $40.41

9v Batteries (4 pack) 1 Amazon $8.00

Threaded Rod 2 Lowes/Home Depot $1.96

TOTAL EXPENSE $354.81

5.1.2 Recovery Expenses


Tubular Kevlar (3/8 in.) 80 ft. Rocketry Warehouse $63.20

Perfectiflite Altimeter 2 Perfectflite $98.92

Nylon Parachute 24” 1 Giant Leap Rocketry $30.68

Nylon Parachute 70” 1 Giant Leap Rocketry $126.78


5.1.3 Payload Expenses


XBee Pro 900 RPSMA (WRL-09099)

2 Sparkfun $109.90

Sparkfun Redboard 1 Sparkfun $19.95

Adafruit Ultimate GPS Breakout (746)

1 Adafruit $35.95


1 Sparkfun $14.95


Barometric Pressure Sensor (BMP180)

1 Sparkfun $9.95

XBee Explorer Dongle 1 Sparkfun $24.95

Sparkfun XBee Shield 1 Sparkfun $14.95

Break Away Headers 2 Sparkfun $3.00

Breadboard Self-adhesive (white)

1 Sparkfun $4.95

Jumper Wires Standard 7” M/M Pack of 30

1 Sparkfun $4.95

CR122 12mm Diameter – 3v Lithium coin cell battery

1 Adafruit $0.95


5.1.4 Motor Expenses


AeroTeach K695R 3 Sirius Rocketry $96.04

AeroTech G77R 2 Apogee Rockets $42.78


5.1.5 Trip Expenses

Item Quantity Price per Unit Time Spent Total Price

Rental Vans 2 $76.02 per day 7 days $1,064.38

Gas (Vans) N/A $237.13 per van 7 days $474.26

Gas (Pick-Up Truck) N/A $279.65 7 days $279.65

Hotel Rooms 3 $126.00 6 nights $2,268.00

TOTAL EXPENSE $4,087.89

5.1.6 Combined Total Expenses

Item Quantity

Launch Vehicle Expenses $354.81

Recovery Expenses $319.58

Payload Expenses $244.45

Motor Expenses $138.82

Trip Expenses $4,087.89

Grand Total $5145.55


5.2 Timeline


5.3 Funding Plan

Junk Food Sales

• Throughout the SLI 2015-2016 Season, the Plantation High SLI Teams will be selling junk food and beverages to students after school, through the aerospace program

• Sales have begun and are very successful in producing an income to help fundraise for the project

• All profit is being divided between the two Plantation High SLI teams

School Fair

• The aerospace program will participate in the Plantation High Annual School Fair. This event allows everyone who wishes to attend to visit the school and partake in activities set up by student organizations and outside sponsors

• At the event, both SLI teams from Plantation High School will cooperate to set up an activity booth

• Activities planned for the event include, but are not limited to: UFO rocket construction, spin art, customizable dog-tags, and junk food sales

Additional fundraising ideas are currently being researched.


5.4 Educational Engagement Plan

With proper planning and communication with our partners, several events have been planned out which will easily engage at least 200 students. These outreach opportunities will enlighten the students on allowing them to comprehend what engineers do and how they think. The following events will take course over the eight months leading up to the launch week in Huntsville, Alabama.

5.4.1 Open Lab Nights at Plantation High

Time: Every Thursday the month of February, starting February 4th at 5pm

Location: Plantation High School cafeteria

Audience: Elementary students

o Activity: Building small Estes rockets with the guidance of the Plantation High SL team members

Audience: 5th Grade students

o Activity: Building TARC style rockets and working with computer programs such as OpenRocket to design rockets.

Once the sessions have been completed, a launch day will be set up at our local PAL field where the students get to come out and fly their rockets. The students will be provided kits and all supplies necessary.

On the 14th of November, the team will be visiting Plantation Middle School to set up a booth and activities for the students

5.4.2 Women in Engineering Empowerment Seminar

Time: Span of 4 months, once per month from 3PM-5PM

Location: Plantation High School Aerospace classroom

Audience: Girls who are interested in the Engineering/STEM fields

Activity:

o A representative from the Women in Engineering Society will speak to the students on what makes a female engineer, how to get involved in the STEM fields, and the pros & cons associated with being a woman in engineering

o The girls will also participate in a project with the team and the society member

This event is currently in the planning process; therefore, details will be disclosed upon finalization.


5.4.3 Boy Scout Rocket Construction Night

A local boy scout group will be constructing Estes rockets. The PHS SLI Teams and mentor will supply the scouts with all supplies and kits necessary along with out guidance during construction. During construction, the team mentor will give a step-by-step demonstration on how to properly build an Estes rocket, along with helpful tips and hints.

o Time: After December

o Location: American Heritage School

o Audience: Boy Scouts

5.4.4 Parkway Launch Day and Seminar

A presentation will be given in which the PHS SLI Team 1 will introduce the students to our Aerospace Program and perform a model rocket safety review.

o Time: Friday, December 4th

o Location: Parkway Middle School

o Audience: 8th grade STEM space science class

Joint Rocket Launch

o Time: Saturday, December 5th

o Location: Vista View Park


6 Conclusion

The Plantation High School SL Team #1 is comprised of nine students, and is mentored by Ken Green and Joe Vallone. Currently, the team has developed and simulated a launch-vehicle design using RockSim software. Ian is the designated safety officer, who will ensure and guarantee the safety of the team and civilians throughout the life cycle of the launch vehicle (construction, static/ground-testing, launching, etc.). The team is prepared to engage in further development and construction of the proposed launch vehicle once approval from NASA has been obtained to proceed with the design of the launch vehicle and the GPS Mapping Live Telemetry payload. The team is a part of a program that has participated in the NASA SL project for the past ten years. Therefore, the team is aware of all requirements and actions needed to carry out the project as planned. The team will continue selling junk food after school in order to raise funds for the project. Leading up to the SLI trip, outreach events, such as those involving the Women in Engineering Society, will be continuously planned to engage as many students as possible. By doing so, the team will not only be teaching young children about our program, but also spreading the word of it as well. Plantation High School’s Aerospace program has grown vastly over the course of the years and has become something to be proud taking part of.

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