NASA USLI Critical Design Review · 2020. 1. 22. · Mission Objectives Vehicle: The rocket will...

NASA USLI Critical Design Review University of Alabama in Huntsvil le

Charger Rocket Works

January 16 th, 2019

Agenda

Introductions and Team Overview

Mission Objectives

Changes since PDR

Vehicle Overview

Payload Overview

Program ManagementSafety

Outreach

Budget

Requirements Compliance

Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 2

IntroductionsZachary Ruta, Program Manager

Hope Cash, Safety Officer

Marcus Shelton, Chief Engineer

William Hankins, Vehicle Team Lead

Colton Connor, Payload Team Lead

Tanner Schmitt, Deputy Safety Officer

Jade Kirkwood, Vehicle Safety Lead

Connor Gisburne, Payload Safety Lead

Dr. David Lineberry, Faculty Advisor

Mr. Jason Winningham, NAR/TRA Team Mentor, Level III Certification

Bao Ha, UAH Graduate Student Teaching Assistant


Mission StatementThe objective of the Charger Rocket Works (CRW) team is to construct a safe and successful Level 2 high

powered rocket with deployable unmanned air vehicle as a payload through applying engineering

judgement and skills. Additionally, CRW will engage with the community in STEM education events and

promoting rocketry to diverse groups.


Mission ObjectivesVehicle: The rocket will deliver the payload to an altitude of approximately 4800 ft., descend safely and within the Mission Performance Requirements set by NASA, and be recovered in a reusable state.

Payload: The payload will deploy from the rocket, fly to a target location, and drop a beacon on target zone all while meeting the desired NASA requirements for the USLI competition.

Safety: Comprehensive safety methods will be implemented in all aspects of fabrication, testing, and launches of hardware using in-depth analysis and written procedures and checklists.

Outreach: The CRW team will meet a minimum of 200 students through hands-on activities as per the request of NASA and will promote STEM and rocketry to diverse groups.


Vehicle


Vehicle Overview


Parameter Value

Vehicle Length 124 in

Body Tube Diameter 6.17 in

Motor Selection L1420R

Major Vehicle Materials Fiberglass, Aluminum, ABS Plastic

Center of Gravity Location 76.13 in

Center of Pressure Location 91.14 in


Vehicle Overview

1

2 4

Pre-Launch

Launch

5

Drogue Deployment at Apogee

Main Deployment

3

Landing Rocket assembled Rocket placed on pad

Drogue deployment charge at apogee

Backup drogue deployment charge at apogee plus 1 sec

Motor ignited Vehicle accelerates

Main parachute deployment at 600 ft AGL

Backup main deployment at 550 ft AGL

Payload deploys Rocket recovered

Vehicle Changes since PDR

Upper airframe bulkhead redesigned to include payload hardware

The main and drogue parachutes positions have been swapped

Motor selection changed from 1520T to 1420R

Extended lower body tube to accommodate

Fin Can spars replaced with the fins

Boat Tail converted to motor retention ring


Full Scale Vehicle Status

Bulkheads and thrust plate CNC machined

Body tubes, nose cone, and fin material have arrived and are ready for alterations

Parachutes have been selected and prepared for launch.

One fin can has been printed but had failure point, will be reprinted

Second part order ready to be submitted


Upper Airframe OverviewThe upper airframe contains many important componentsThe drogue parachute

The payload bay

The nose cone

The tracker


Upper Airframe – Nose ConeThe selected nose cone is a 4:1 ogive nose cone from Madcow Rocketry

The exposed length is 26 inches with a 6 inch coupler

A blind hole will be tapped into the nose cone’s aluminum tipA threaded rod will be inserted into this hole

The threaded rod will be used to secure the nose cone bulkhead, where the tracker and the payload’s deployment sheath attaches


Upper Airframe - MainFEA was conducted to ensure upper airframe (UA) bulkhead could withstand loading

FEA results indicate a generally good design, will require some hang testing

UA bulkhead attached to upper body tube with six #4-40 bolts

Eye bolt mounts through face of UA bulkhead

Shock cord is attached to the eye bolt

Payload deployment mechanism attaches to UA bulkhead


Avionics Coupler - Overview 2x G10 fiberglass bulkheads per end G12 fiberglass tube (not shown) G12 fiberglass switch band Twin threaded rod load bearing path Forged 1/4-20 eye bolts Redundant main and drogue ejection charges


Coupler V4 Mk II

Avionics Coupler - Electronics Twin redundant Stratologger CF Altimeters 2x SPST key switches control avionics Redundant main and drogue deployment charges Power supplied by 2x 9v lithium batteries


http://www.perfectflite.com/SLCF.html

https://www.digikey.com/product-detail/en/c-k/Y101132C203NQ/CKN11517-ND/484276

Avionics Coupler - Structural Load transferred from 1/4-20 eye

bolts to bulkheads Upper and lower bulkheads are

epoxied together From the bulkheads load is

transferred through (2x) 1/4-20 304 SS threaded rods

Washers and lock nuts used to secure all eye bolts and threaded rods


Avionics Coupler - Mounting

Avionics mounted to fiberglass bulkhead suspended on threaded rods

Altimeter mounted on standoffs with nylon screws

Battery holders mounted with stainless steel screws

Quick connectors allow easy removal and assembly of avionics


GPS Tracking

Xbee-Pro S3B Radio Transmitter with Antenova GPS

Located in nose cone

Powered by CR123 lithium ion battery

Used with success on previous CRW flights

Transmitting frequency: 902 to 928 MHz

Transmits to distances up to six miles away


Lower Airframe OverviewThe lower airframe contains:The main parachute

The motor

The fin can assembly


Fins and Fin CanFins:

Adjusts CP for stability

G10 fiberglass sheet

Fabricated in-house

Through-wall mounting

Fin Can:

Removed full spars since PDR

3D printed in-house

Fixed to airframe with 8 #4-40 bolts


Previous Current

Thrust Plate

Changes since PDR:Increased thickness

Added cutouts

Transfers force from motor

Supported by FEA


Previous Current

Retention Ring

Fabricated in-house

Retains the motor during the coast phase of the flight


Load Path:Boost Phase

Motor case

Thrust Plate

Body Tube

Coast Phase

Retention Ring retains motor

Aft BulkheadFunctions as recovery retention system

Main parachute attached via eyebolt

Diameter: 6 in

Aluminum thickness: 0.25 in

Fixed to body tube with 6 #4-40 screws


Motor Trade Study25 motors simulated using OpenRocket

Velocity off the rail, apogee, and stability off the rail were the three FOM


Motor Manufacturer # of GrainsVelocity off

the rail(ft/s)

Apogee(ft)

MaxVelocity

(ft/s)

Max Acceleration

(g's)

Stability off the rail

(cal)

L1520T-P Aerotech 3 65.2 3719 509 7.3 2.82

L1390G-P Aerotech 3 60.2 3915 517 7.0 2.72

L1350-CS CTI 3 61.2 4500 564 6.6 2.80

L1420R-P Aerotech 4 63.4 4817 592 6.9 2.50

L1365M-P Aerotech 4 61.3 4965 594 6.4 2.55

L1395-BS CTI 4 63.3 5302 629 7.3 2.66

L2375-WT CTI 4 80.8 5463 687 11.6 2.73

L1115 CTI 4 62.6 5406 593 7.0 2.63

Selected Motor

75mm case

Total Impulse: 4603 N∙s

Average Thrust: 1420 N

Peak Thrust: 1814 N

Burn Time: 3.2 s

Propellant Mass: 2560 g / 5.6 lbm


Aerotech L1420R

Flight Profile

Projected apogee: 4806 ft

Maximum velocity: 592 ft/s

Maximum acceleration: 222 ft/s2

Thrust to weight: 7.01

Rail exit velocity: 55.5 ft/s

Total flight time: 98.8 s


Trajectory Verification

Custom-made, two dimensional code showed less than 1% error compared to OpenRocket

RASAero II predicted apogee at 500 feet above other codes


Trajectory Verification

10,000 iterations using the custom-made code

Altered vehicle mass, body drag coefficient, and motor impulse

Average value: 4831 feet

Deviation: 211 feet

Of the 10,000 runs, 23% fall 250 feet or more outside apogee target

Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS

0

200

400

600

800

1000

1200

43

04

43

57

44

10

44

62

45

15

45

68

46

20

46

73

47

26

47

78

48

31

48

84

49

36

49

89

50

42

50

95

51

47

52

00

52

53

53

05

53

58

54

11

Mo

re

# o

f R

un

s (o

f 1

0,0

00

)

Apogee (ft)

28

Stability Margin

Stability of 2.43 off the rail

Center of Pressure: 91.14 inches from leading edge

Center of Gravity: 76.13 inches from nose


Mass Statement and Margin


System Component Mass (lbm) Mass Value Origin System Component Mass (lbm) Mass Value Origin

Wing Nuts 0.005 SPEC 1/4"-20 Washer 0.004 SPEC

0.25" Button Head Torx Screw 0.001 SPEC 1/4"-20 Lock Nut 0.011 SPEC

0.50" Button Head Torx Screw 0.001 SPEC 1/4"-20 Shouldered Eyebolt 0.064 SPEC

1.25" Button Head Torx Screw 0.003 SPEC 1/4"-20 x 13" Threaded Rod 0.185 SPEC

Drogue Parachute and Cord 0.955 MEASURED Battery Holder 0.120 CAD

Nosecone Bulkhead 0.301 MEASURED Coupler Outer Bulkhead 0.227 CAD

NoseCone 4.188 SPEC Coupler Inner Bulkhead 0.210 CAD

Threaded Rod 0.089 SPEC Charge Well 0.009 CAD

Tracker 0.031 MEASURED Coupler Body Tube 1.604 CAD

Upper Body Tube 4.647 CAD Epoxy Plugs 0.001 CAD

TOTAL 10.228 Terminal Block 2x2 0.005 MEASURED

Aft Bulkhead 0.339 MEASURED Stratologger CF Altimeter 0.027 MEASURED

Retention Ring 0.207 CAD #2-56 Locknut 0.002 SPEC

Lower Body Tube 5.433 CAD #2-56 Longnut 0.5" 0.001 SPEC

RMS-75/3840 Case with 1420R 10.057 SPEC #4-40 Locknut 0.002 SPEC

#4-40 Locknut 0.002 SPEC #4-40 Locknut 0.75" 0.002 SPEC

#4-40 Brass Heat Set Insert 0.001 SPEC #4-40 Standoff 0.001 SPEC

#4-40 1-3/8" Socket Head Screw 0.004 SPEC #4-40 Pan Head Screw 0.000 SPEC

Centering Rings 0.805 CAD Coupler Switch Band 0.101 CAD

Fins 0.519 CAD TOTAL 4.653

#4-40 0.375" Socket Head Screw 0.001 SPEC Payload TOTAL 9.225

#4-40 1.00" Socket Head Screw 0.003 SPEC

Thrust Plate 0.294 CAD

Main Parachute and Cord 2.970 MEASURED

TOTAL 23.022 47.129

Lower Airframe

Total Mass:

Upper Airframe

Avionics Coupler

Recovery System Drogue Parachute

FruityChutes CFC-18 Classic Elliptical (CD =1.5)

Terminal Velocity: 119 ft/s

30 feet tubular nylon (1”)

Deploys at apogee, apogee + 1s

Main Parachute

FruityChutes IFC-144 Iris Ultra w/ Spectra Lines (CD 2.2)

Terminal Velocity: 12.92 ft/s

50 feet tubular nylon (1”)

Deploys at 600 ft, 550 ft


Main Parachute Kinetic Energy

Part Mass KE

Upper Airframe 19.80 lbm 46.21 lbf-ft

Avionics Coupler 4.26 lbm 11.04 lbf-ft

Aft Airframe 15.74 lbm 40.82 lbf-ft

Drift Analysis

Maximum drift: 2387 ft from launch pad

Assumes constant, one-directional wind shear from apogee to touch down

Does not account for parachute deployment time and effects


Vehicle FabricationCurrent Capabilities

3D printed parts

Fin Can

Retention Ring

Machine Shop Access

Bulkheads

Thrust Plate

Limited Finishing at JRC

Readying components for Assembly


Machine Shop access will be restricted after January 30th

Machined part production has been prioritized to manufacture all parts which require the machine shop before January 30th

Alternative options for part manufacturing are being considered

Vehicle Testing Plan


Subscale Flight Launch

Launched from Birmingham, AL on November 17

Launched at 11:30 a.m. Winds below 7 MPH

Temperature averaged 640F

1010 Rail canted 40 N


Subscale Flight Data

Flight RecorderMaximum Altitude

Recorded (ft)

Primary Stratologger 2047

Secondary Stratologger 2098

Raven3 2151

Average 2099

Standard Deviation 52


0

500

1000

1500

2000

2500

0 10 20 30 40 50 60 70

Alt

itu

de

(ft)

Time (sec)

Primary

Secondary

Apogee approximately 400 feet lower than OpenRocketprediction

Total flight time ≈ 45 sec

Apogee

Main Parachute Deployment



Successful deployment of drogue recovery charge

Decent velocity ≈ 85 ft/s

y = -84.609x + 3215.8R² = 0.9908

y = -85.727x + 3297.9R² = 0.9863

0

500

1000

1500

2000

2500

10 12 14 16 18 20 22 24 26

Drogue

Successful deployment of main recovery charge

Decent velocity ≈ 38 ft/s

Expected decent velocity was approximately 32 ft/s

y = -38.124x + 1699.9R² = 0.9641

y = -37.253x + 1743.7R² = 0.9058

-100

0

100

200

300

400

500

600

700

800

900

25 30 35 40 45 50

Main


Max axial acceleration of 28 G’s

Max lateral acceleration of 40 G’s


Burnout Drogue Main Landing

Subscale Flight Results

Stratologger data matched against one-dimensional trajectory code.

Drag coefficient could not be approximated from results.

Possible re-flight in coming month, otherwise results will be calculated from Full Scale tests.

Assessed accuracy of descent velocity predictions.


Subscale Lessons Learned Expected loads and decent rate in recovery

far higher than anticipated. Apogee lower than anticipated Refined simulations based on data

Flaws when 3D printing parts Redesign of 3D printing parts to minimize

effects of flaws

Flexing and errors when manufacturing parts Refined jig design and manufacturing

methods

Lost lock on GPS tracker in flight Developed methods to ensure power to

GPS tracker in flight

Improved rocket recovery methods if GPS tracker lock is lost


Payload


Beacon Release

Use video feed to confirm location

Send command to release beacon

Payload Concepts of Operation


UAV Flight

Vehicle Landing

Pre-Flight

Wait for affirmation to deploy

Check for GPS lock Check for Ground

station connection Check video

feedback

Autonomous flight to the FEA (100 ft Ascent, flight to the GPS location of FEA)

Piloted landing on to the FEA Fail safe return to last way point when

communication loss

Payload Deployment2 Send command to fire black

powder charges

Piston: Pushes the deployment sheath and the nose cone out of the body tube

Deployment sheath: Houses the UAV and unfolds to allow UAV to fly when pushed out of the body tube by piston

1

3

4

5

6 Piloted flight away

front the FEA

Fly away

Changes Since PDRSpring mechanism for UAV arm unfolding: now supplemented by limit pins

Added additional safety features to deployment controller

Buzzer and LED added to relay arm/disarm status

Added visible indicators to UAV design

Switch to higher-capacity battery

4000mAh to 5000mAh battery

Simplified piston latching mechanism

COTS option adopted


Custom retention mechanism COTS latch solenoid

Previous Design

New Design

Payload Progress Since PDR

Acquired parts

Radio Range testing

GPS testing

FPV imaging testing

Motor and speed controller compatibility with flight computer confirmation

Q-Ground Control operation

Performed material testing for orientation sheath



UAV CAD

Updated CAD allows for better visualization of electrical component placement

Isometric View Bottom View

45


UAV Manufactured Components

Upper mounting plate

Manufactured from aluminum

Main frame of UAV to which all components and brackets are fastened

46



Under Carriage

Supports the majority of the UAV electrical components

Aluminum

47



Battery Brackets

Functions as an encasement for the battery and protects the battery from impact with the ground

Sheet Metal

48



Telemetry Transceiver Bracket

Supports and retains the telemetry transceiver

Sheet Metal

49



Beacon Holder Bracket

Secures the beacon holder to the upper mounting plate

Sheet metal

50



UAV Arms

Provide distance from the UAV body for the motors to have a larger combined surface area of thrust

Carbon Fiber

51


Unfolding the UAV Arms

A tension coil

spring pulls the

cable across arc

limiting pins which

act as the sheaves

of a block pulley

UAV arm

UAV arm

Limiting pin

Limiting pinSpring

52

UAV Power Budget


Component Voltage

(V)

Current

(A)

Power

(W)

Duty

Cycle

Supply

Efficiency

Power

Draw (W)

Flight computer 5.0 0.045 0.23 100% 90% 0.25

Camera 7.0 0.38 2.66 100% 90% 2.96

GPS 5.0 0.033 0.17 100% 90% 0.18

LED 5.0 .35 1.75 100% 90% 1.94

Transceiver 5.0 0.1 0.50 100% 90% 0.56

Video transmitter 7.0 0.56 3.94 100% 90% 4.37

Solenoid 11.1 0.25 2.78 1% 100% 0.03

Motors 11.1 50.9 564.99 100% 100% 564.99

Total weighted power draw (W) 575.28

Total battery capacity (WHr) 111

Run time (min) 11.58


UAV Block Diagram

Gro

un

d statio

n

Vid

eo R

ecei

ver

2 X Battery (LiPo 3s)

Electric Speed Controllers (ESC)

Motor + Propeller

Flight Computer

Camera

GPS + Compass

Power Module

Video Transmitter

Tele

met

ry/C

on

tro

ller

Tran

scei

ver

Transceiver1

1.1

V

Solenoid

5V

Pow

er li

ne

Dat

a lin

e

Lege

nd

Switch

54

UAV Schematic


Includes 6 major subsystems: Power System FPV System Communication System Beacon Release System Flight Control System Propulsion System

Also includes: Indicators Switches

UAV Power System


Schematic Major Components

ZOP Power 11.1V 4000MAH 3S 30C LiPo Battery

AUAV power module ACSP5

56

Purpose: Powers all the components

of the UAV There are two voltage rails

11.1 V of the battery 5V of the power

module

UAV Flight Controls System


Sch

em

atic

Maj

or

Co

mp

on

en

ts

mRo Pixracer R15 mRo GPS u-Blox Neo-M8N

57

Receives commands from the ground station through the communications system

Sends signals to the propulsion system to change the direction/speed of the drone

Sends signal to Pull the solenoid and release the payload

UAV Propulsion System


Maj

or

Co

mp

on

en

tsSc

he

mat

ic

58

Change horizontal and vertical position of the payload by changing the speed of different motors

Change the orientation of payload by varying motor speed and direction across the UAV

UAV FPV System


Caddx Turtle Micro Mini FPV Cam

Airy Mini 5848 5.8Ghz VTX

Schematic

Major Components

59

Provides video feedback to the

UAV operator

Confirm position above FEA

Avoid obstacles

FPV system is transmits

independently and is not

controlled by flight computer

Only shares the power supply

UAV Communications System


Holybro 915MHz Telemetry radio

Schematic

Major Components

60

Sends Telemetry from the flight

computer on flight condition

Receives commands on

maneuvers through a joystick on

the ground station

UAV Beacon Release System


Adafruit Push/Pull Solenoid

Schematic Major Components

61

Retains the beacon in board until a

command is received in the pull

position

On receiving the command,

releases the beacon on to the

Future Excursion Area by

transitioning to pull position


Indicators and Switches

62

Schematic

Major Components

Switch: To avoid the necessity to use a heavy switch which is rated to above 100 A

pulled by the motors, it is placed parallel to the motors LED is placed parallel to the flight computer as the flight computer being

powered is the best indication of UAV being armed

UAV Power Budget


Component Voltage

(V)

Current

(A)

Power

(W)

Duty

Cycle

Supply

Efficiency

Power

Draw (W)

Flight computer 5.0 0.045 0.23 100% 90% 0.25

Camera 7.0 0.38 2.66 100% 90% 2.96

GPS 5.0 0.033 0.17 100% 90% 0.18

LED 5.0 .35 1.75 100% 90% 1.94

Transceiver 5.0 0.1 0.50 100% 90% 0.56

Video transmitter 7.0 0.56 3.94 100% 90% 4.37

Solenoid 11.1 0.25 2.78 1% 100% 0.03

Motors 11.1 50.9 564.99 100% 100% 564.99

Total weighted power draw (W) 575.28

Total battery capacity (WHr) 111

Run time (min) 11.58

63

Assumptions: Power consumed by motor

at nominal thrust is used All the components are

assumed to have a duty cycle of 100% except the solenoid which is estimated to be powered 1% of the total time

The power supplies are assumed to be at 90% supply efficiency


Ground Station Block Diagram

64

Video Link Diversity Receiver Biquad and Dipole for both

high gain and isotropic radiation pattern

Video Converter to convert from NTSC to RTSP

Ethernet crossover connection to computer

Telemetry/Command Dipole Antenna Transceiver for

communication both ways USB connection to

computer Joystick to send commands

UAV Link Budget


Dipole Antenna Dipole Antenna

Signal

RX

sensitivity

(dB)

Transmit

power

(dBm)

Rx

Antenna

Gain (dB)

TX

Antenna

Gain (dB)

Link

Margin

(dB)

Rx

Antenna

Loss (dB)

Tx

Antenna

Loss (dB)

Maximum

free space

loss (dB)

Frequency (GHz)

Range (km)

Telemetry -117 20 2.15 2.15 12 2 2 125.3 0.915 48

Video -95 20 9.5 2.15 12 2 2 108.5 5.8 1.4

48 km

65

Biquad Antenna

1.4 kmVideo Link

Telemetry


Ground Station Software

QGroundControl Open source Popular among Amateur Drone

Operators Ability to stream FPV video Ability to use Joystick over the

telemetry radio instead of an RC transmitter/ receiver pair

66

Payload Propulsion System


Parameter Value

Maximum thrust 7.49 lbf

Weight 3.73 lbf

Thrust-to-weight ratio 2.0

Nominal throttle point 4.19 lbf

Airspeed 30.1 mph

Range in 20 mph headwind 1.44 mi

Flight time 9.29 min

67

Payload Integration


Payload contained within upper airframe after landingUpon command from the ground station, the payload is ejected by a black powder charge

The semi-rigid sheath surrounding the payload unrolls, reorients the payload right-side-up

The payload lifts off of the sheath upon command from the ground station

Deployment Piston


Redundant black powder charges

Piston deploys complex assemblyPayload

Orientation sheath

Nosecone

69

Deployment Controller


Door latch solenoid

Attachment to piston bulkhead

Deployment signal controller

Black powder deploys payload

Latch secures payload until deployment

No transmission from radio

70

Arming switch access

Deployment Electrical System


Microcontroller

6V power supply(batteries)

3.3V power supply(buck regulator)

XB

eerad

ioLatch actuator

(solenoid)Dual E-match firing

circuitsA

rmin

g in

dicato

r

Gro

un

d statio

n

Co

ntro

ller Tran

sceiver

Power line

Data line

Legend

12V power supply(boost convertor)

71

PCB for Deployment Electronics

Payload Testing Plan


Integrated Payload Tests

UAV System Tests Deployment System Tests

Cube Retention

Test

Integrated Deployment Test

Radio Range Test

FPV Imaging Test

Deployment Material Testing

Flight Range Test

Ejection Test

Flight Endurance Test

Deployment Software

Qualification

Safety

Safety Committee Focus for CDR

Update Risk and Hazard AssessmentEmphasis on Personnel and

Environment

Further analysis into Failure Modes and EffectsDetailed Component Description

Sheets

Evaluating lessons learned from sub-scale launch


Subscale Flight Operating Procedure

Safety Training


Training Topic Date

CPR/AED/First Aid 10/4/18 – 10/19/18

Basic Emergency Procedures 10/18/18

Black Powder Testing and Motor Safety 10/30/18

Outreach Safety 11/1/18

Sub-Scale Launch Safety 11/15/18

Test and Demonstration Safety 1/17/19

Full-Scale Launch Safety 1/31/19

75

Hazard and Risk Assessment

The Safety Committee continues to use the team’s previously established Risk Assessment Criteria (RAC)

Testing and fabrication has resulted in updated

hazard and risk assessments with emphasis on:

Machine shop use during fabrication

Personnel and Environmental Hazards after the sub-scale launch

Full reviews of current Hazard and Risk Assessment tables have been conducted by team leadership


Environmental Hazards

Local launch field conditions for sub-scale were identified

as hazardous to personnel during recovery operation

Additional hazard analysis resulted from this in order to

mitigate future risk to personnel

Major hazards analyzed include:

Injury resulting from vegetation (scratches, rash, etc.)

Injury resulting from insects (stings, bites)

Heat Exhaustion, Heat Stroke, Dehydration


Poison Ivy (Google Images)

Component Description SheetsEach component of the rocket and payload has a detailed description sheet

This sheet includes the basic information of the component: size, weight, material, etc.

Each sheet has a specific, detailed FMEA attached for the indicated component

Any finite element analysis for a component is also included on the sheet


Failure Modes and Effect AnalysisAnalysis of possible failure modes for each component of the rocket and payload to establish mitigations and prevent failures as part of the Component Description Sheets

FMEA is done using a table of severity and likelihood to identify the criticality of each mode

The list of FMEA is comprehensive and has been updated as components have changed


Checklists and SOPs


Approved Pending Review (Vehicle) Pending Review (UAV)

Black Powder Demonstration Full-Scale Launch UAV Deployment Demonstration

Sub-Scale Launch Shock Cord Tensile Test Integrated Propulsion Testing

Drop Test Integrated Deployment Testing

Ejection Demonstration

Flight Endurance Testing

Flight Range Demonstration

Full Scale SOP Pre-Launch


Launch Preparation

Upper Airframe Assembly

Coupler Preparation

Lower Airframe Assembly

Main Parachute Installation

Drogue Parachute Installation

UAV Installation

Ejection Charge Installation

Motor Installation

UAV Preparation

Full Scale SOP Post-Recovery


UAV Sheath Deployment

UAV LaunchedAutonomous

FlightPiloted Flight

Beacon Deployment

UAV Systems Check at Ground

Station

Program Management

Changes Since PDR

Awarded 5,000 dollars from ASGC

Sub-Scale Vehicle Launch Date (11/17/2018)

Arrival of all Full-Scale Vehicle Parts

New Team GTA


Past Outreach EventsNov. 3 – Girls Science and Engineering Day

Activities: Stomp Rockets & CD Hovercrafts

Individuals Reached: 166

Nov. 10 – UAH Society of Women Engineers

Activity: Team Interaction with Students


Nov. 28 – Interactive Rocketry at Lexington High School

Activity: Rocketry Basics Presentation


Dec. 11 – Elkhorn Crossing School Presentation




Upcoming Outreach EventsFeb. 16 – Science OlympiadCRW team members

Activity: Battery Buggy, Boomilever & Mousetrap Vehicle

Mar. 2019 – Ramsay High SchoolCRW team members


TBA: Davis Hill Elementary SchoolActivity: Propulsion and Vehicle Design

TBA: Challenger Middle SchoolProjectile Motion and Forces

TBA: Jemison High SchoolHeat Shields & Payload Design


Students participating in UAH Science Olympiadnsstc.uah.edu

Project Funding

Funding Overview Funding Status


Projected vs. Actual Expenditures

Projected Expenditures Actual Expenditures



Requirement

NumberRequirement Description Compliance Verification Plan Verification Status

NASA-5.5 Teams will abide by all rules set forth by the

FAA.

All applicable FAA regulations are accessible to the

team. The Safety Officer and Team Leadership are

responsible for ensuring CRW is in compliance with all

applicable FAA regulations.

Lists of the applicable FAA regulations are available to the team on the

CRW online sharing site. Team Leadership ensures all applicable FAA

regulations have been considered when in the design phase of the

project.

Inspection complete

UAH-V-01 The vehicle shall reach an apogee of 4800

feet within ± 250 feet

Simulations were used to predict an achieved altitude of

4806 feet. The subcale test flight was used to refine the

simulations.

Analysis

The team will use simulations and hand calculations to confirm that

vehicle will reach the required height.

Complete

The simulations predict the launch vehicle will

reach 4806 feet.

UAH-V-02 There shall be redundant, increasing black

powder charges in the event of initial

recovery system deployment failure.

Multiple increasingly powerful black powder charges

will be installed in the recovery system.

Analysis

The launch vehicle will incorporate redundant black powder charges.

Incomplete

The subscale rocket incorporated redundant black

powder charges. The full-scale rocket is awaiting

assemblly.

Requirement Verification & Compliance

Verified using the method below Validated through testing, demonstration, analysis, or inspection


Jan Feb Mar April

Vehicle

Payload

FRR

Competition

PLAR

2/9

2/2

1/25

NASA Q&A

4/6

4/26

Fab. And Assy.

Fab. And Assy.

2/9

3/2

Backup

LaunchLaunch

2/2

2/9

Launch Backup Launch

Document Development

Document Development

Overview Schedule

Competition

Launch

March

1/21 - 1/27 1/28 - 2/1 2/4 - 2/10 2/11 - 2/17 2/18 - 2/24 2/25- 3/3 3/4 - 3/10

Vehicle Fab. and Assy.

Final Cad

Materials Order

Final Drawings

Part Machining

Assembly

Deployment Testing

Piston Testing

Flight Readiness Review

Payload Fab. and Assembly

Final Cad

Materials Order

Final Drawings

Part Machining

Assembly

Payload Ejection Testing

Rocket Flight Test

UAV Testing

FL Launch Opportunities

Jan Feb


Detail Schedule

2/9 2/16 3/93/22/2

HARA/SoARHARA/

SoARMC2 SEARSSEARS

1/14

1/18

1/19

1/21-1/26

1/26-1/30

1/311/29-2/01

2/01

1/14

1/18

1/19

1/21-1/26

1/26-1/30

1/30-2/05

2/06

2/07-2/21

Questions

NASA USLI Critical Design Review · 2020. 1. 22. · Mission Objectives Vehicle: The rocket will...

Documents

Transcript of NASA USLI Critical Design Review · 2020. 1. 22. · Mission Objectives Vehicle: The rocket will...