University of Florida Rocket Team Flight Readiness Review Presentation

University of Florida Rocket TeamFlight Readiness Review

Presentation

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingProject PlanFuture Work

Design Overview

164 inches long Inner diameter: 6.0 inches

Outer diameter: 6.14 inches Total Mass: 74.2 lbs

Target Altitude: 10,000 ft

Outline


Changes From CDR

Structural Changes from CDR include: Nose cone Nose cone Extension Upper Airframe Upper Electronics Bay/Airframe Middle Airframe Ballast mass Fins

Nose Cone & Attachment

Problem Lack of precision with

nose cone plug Difficulty fiberglassing the

nose cone Did not attach to vehicle

as neededSolution

Purchased a fiberglass tangent ogive nose cone

11.5 inch nose cone extension airframe; length taken from upper airframe

Upper Electronic Bay/Airframe

Problem Vibrations to the hatch Electrical components

interfering on the bay Total length was

compromised Bay was not removable with

CDR designSolution

Eliminate the hatch Build a Faraday cage Shorten the airframe by 6

inches Only one end has a coupler

shoulder with nuts epoxied to it

Middle AirframeProblems

Limited removability of UEB

Solutions The middle airframe

was changed to 14 inches long

Phenolic coupler was extended throughout airframe to provide a shoulder on either end

Shoulder that slid into UEB airframe had nuts epoxied to inside

Ballast Mass

Problem No permanent solution for attachment mechanism No proper location for ballast mass No exact mass estimates

Solution Remove ballast mass concept

Fins

Problem Lighter mass estimates Expected apogee

higher than target altitude

Stability fluctuatingSolution

Induce drag by increasing the size of the fins and thickness

Move them forward

Key Design Features

Boattail

Tangent ogiveReduces base dragCenters motorHouses GSS payloadMotor retention

Motor Centering/ Thrust Capture

Two centering ringsOne thrust bulkheadThreaded rod

distributes load to LEB and centering mechanism

Tapped holes in bulkheads for securing in place

Fin Attachment and Fillets

G10 fins with 4 layers of fiberglass

Fiberglass filletTrapezoidalFlush with inside of

body tube

Payload Integration

Camera housed in boattailTriboelectric payload housed in noseconeStrain gages located on motor tube and easily

accessible

Outline


Cesaroni M1890

Max Thrust: 2239 NBurn Time: 5.28 seconds

Launch Mass: 19.5 lb. Empty Mass: 7.73 lb.

(N)

Cesaroni N2600-SK P

Max Thrust: 2972 NBurn Time: 4.26 secondsRail Exit Velocity: 67 ft/sThrust to weight ratio: 8.51Max Velocity: Mach .94

Launch Mass: 25.3 lb.Empty Mass: 10.4 lb.

Outline


Mission Performance

1. The vehicle achieves apogee between 9,500 and 10,500 feet.

2. At apogee, the vehicle separates beneath the upper electronics bay, and the drogue parachute is successfully ejected.

3. At 700 feet AGL, the nosecone and main parachute are successfully ejected.

4. No portion of the vehicle or payloads sustain any major damage during flight or landing.

Altitude vs. Time

Open Rocket Simulation

Flight Data

Mass Statement

Component Weight (lbs)Nose Cone 1.20

Triboelectric Board and Battery 1.50

Nose Cone Body Tube Section 0.82

Nose Cone Tube Coupler 0.58

Nose Cone Bulkhead 1.40

Main Parachute 6.20

Piston 1.60

Forward Airframe 1.81

Forward Airframe Shock Cord 0.60

Electronics Airframe Body Tube 1.99

Electronics Airframe Tube Coupler 1.40

Upper Electronics Bay 4.00

Middle Airframe Body Tube 0.96

Baffle 1 1.00

Baffle 2 1.00

Drogue 0.57

Drogue Shock Cord 0.32

Middle Coupler Tube 1.25

Lower Extension Body Tube 1.64

Lower Electronics Bay 2.60

Lower Coupler Tube 0.65

Bulkhead 1.00

Wires/Harnesses 0.50

Lower Airframe 2.19

Trapezoidal Fins (Quantity 3) 1.88

Centering Ring Lower 0.60

Centering Ring Upper 0.40

Boattail 2.80

Motor Mount 1.00

N2600-SK Motor (6 Grains) 25.31

Total Weight 68.76

Velocity vs. Time

Stability Margin

Static Stability: 1.88 calibersCG: 108 in.CP: 120 in.

Kinetic Energy

Crosswind Drift/Altitude

Outline


Attachment Scheme

Recovery System

DrogueDeployment at apogee48 inches in diameterSemi-ellipsoid canopy

shapeCharge baffle ejection

systemDescent velocity: 63.3 ft/s

MainDeployment at 700ft168 inches in

diameterSemi-ellipsoid canopy

shapePiston ejection

systemParachute

deployment bag with 12in pilot chute

Descent velocity: 12.6ft/s

Recovery

Changes since CDRUse of a deployment bag for main parachuteDrogue parachute reduced from 60in to 48inNumber of shear pins increasedNylon upholstery thread size reducedPiston orientation changed

Main Parachute

Drogue Parachute

Deployment Bag

Full Scale Test

Outline


Ground Scanning System Payload

Ground Scanning System to detect hazards in the landing area

Take an image of landing areaScan for potential hazards in real-timeSend scanned image to Ground Station in

real-time

Design Overview

Picture is taken and sent to Lower Computer Image is saved, then sent to Upper Computer

via onboard wifiImage is run through custom color-mapping

hazard detection software Hazard is defined as the edge, corner or cliff of any

surface or area. Scanned image is sent to ground station via

RF signal

Camera Module

Camera Integration

Payload Verification

Camera module test successfulCeramic heat shield material protects camera

from exhaustSaved control image analyzed for hazards

and quantified by teamSuccess criteria requires 75% of analyzed

hazards to be detected by software

Boost System Analysis Payload

Utilizes vehicle weight information and strain gage readings on the motor tube to determine the drag force seen on the rocket.

Assumes that force of thrust is imparted directly onto the phenolic motor tube.

Successful if the calculations of acceleration constructed from the strain gage readings coincide with the rate gyro acceleration readings.

Boost System Procedure

Data acquisition of the strain gages will be triggered by the start of motor burn.

The voltage across the Wheatstone bridges will be read by the data acquisition device until apogee.

Post recovery, the data will be processed by relating the acquired voltages to strains.

The strains are converted to stresses to ultimately arrive at the force of drag.

Centering Rings Bulk Head

Motor Tube Strain GagesTemperature Compensation

Strain Gages

Boost System Integration

Triboelectric Effects Analysis Payload

Determine charge build up on the exterior of the rocket

Calculate surface charge density at each region

Compare surface map of surface charge to the map of friction on the surface of the rocket

Generate table relating acquired triboelectric charge to air friction

Design Overview

Design Integration

Payload Testing

Payload Verification

Outline


Electronics

Recovery Communications and data processing Boost systems analysis Image processing

Electronics

Outline


Testing

Recovery Testing Parachute Testing and Full Scale Launch Complete

Structural Testing Compression and Shear Stress Testing Complete Subscale Testing and Full Scale Testing Complete

Electronics TestingMotor Testing

Backup Motor Tested by Full Scale LaunchPayload Testing

Full-scale Results

Design Length: 13’ 8” Max. Diameter: 6.14 in. Weight: 68.75 lbs. Stability Margin: 1.88 Predicted Apogee: 9469

ft. Results

Actual Apogee: 9043 ft. Drogue Deployment:

Successful Main Deployment:

Premature

Status of Requirements Verification

Completed 34 Requirements

Vehicle Inspection Project Plan Safety Requirements

In Progress 10 Requirements

Vehicle Modifications After Full-ScaleNot Started

9 Requirements Payload Integration Pending

Outline


Project Plan

Education Engagement Over 200 students reached throughout three events

Budget Total Budget: $17,190.07

Projections show a $363.63 surplusSchedule

All Major Milestones Complete Preparing For Travel

Outline


Future Work

Payload IntegrationElectronics/Software IntegrationRocket PaintingUSA Science & Engineering Festival, April

26th & 27th Competition Preparation

University of Florida Rocket Team Flight Readiness Review Presentation

Documents

Transcript of University of Florida Rocket Team Flight Readiness Review Presentation