Illinois Space Society Tech Team USLI FRR Presentation

Illinois Space Society Tech TeamUSLI FRR Presentation

Contents

• Vehicle Specifications • Performance Characteristics• Recovery System• Flight Predictions and Testing• Payload

Vehicle Design

Modified Ultimate Darkstar kit with dual deployUAV deployment at apogeeThree split finsAeroTech L2200 motor24" Von Karman nosecone

Vehicle Dimensions

• Length: 126 in• Diameter: 6 in

Component dimensions shown:

Final Motor Choice

• Aerotech L2200 75 mm motor, Aeropack retainer and adapter

Motor Characteristics

• Max Thrust 3101.8 N• Average Thrust 2246.6 N

• Total Impulse 5104 Ns

• Mass pre Burn 10.55 lbs

• Post Burn 5.55 lbs

Stability Analysis

• CG 14.4 inches above CP• Static stability margin of 2.34• Marginally overstable, but well within acceptable bounds

Takeoff Characteristics

Using an 8ft high, 1.5 in standard launch rail, the predicted takeoff characteristics are:

Thrust to weight ratio: 13.5

Rail exit velocity: 73.7 ft/s

These are well within acceptable ranges for normal launch conditions

Vehicle Mass

For detailed vehicle mass, view section 3.1 G. All weights in pounds.

• Nosecone: 2.04• Upper Airframe and Coupler: 10.801• UAV and Piston: 6.73• Booster Airframe and Motor: 27.297• Parachutes and associated hardware: 6.163• Total, on the pad: 53.031

Recovery System Overview

Recovery System Characteristics

Dual deployment system, with• Two redundant Stratologger altimeters for charge control• Telemetrum for GPS and tracking• Independant switches and batteries for all altimeters• SkyAngle 36 in Classic 2 Drogue, ~74 ft/s terminal velocity• Rocketman 18 ft Main, ~ 17.4 ft/s terminal velocity

Kinetic Energy at Key Phases

Kinetic Energy During Descent (ft-lb)

Under drogue:Nosecone: 172.5

Upper airframe/ coupler: 913.4Booster airframe: 1822.5UAV: 431.3

Under main:Nosecone: 6.57Upper airframe/ coupler: 34.77Booster airframe: 69.38

UAV descends separately from rocket.

Predicted Performance

For the final launch vehicle:

Drift during test flight was 772 ft with 8 mph winds; this is with the expected range for this speed. Drift calculations have been altered from CDR to reflect changes to stability margin.

Wind Speed (mph) Altitude (ft) Maximum Drift (ft)

5 5064 600

10 5042 1250

15 5009 1900

20 4960 2600

Predicted Performance

Final launch vehicle predicted performance

Test Plans

The only remaining testing to be done on the launch vehicle are tests involving the UAV, including a second full scale test flight.

• Final charge testing of piston, UAV, and drogue• Second full scale test flight

All other tests have been completed.

Recovery System Testing

Charge testing and one full scale flight test have been successfully completed. All charges successfully deployed at proper times during flight, and there was no unexpected separation.

Future charge testing will occur after the new design components are completed and the UAV is prepared for charge testing, to ensure continued successful deployment. Only one charge test remains to be done.

Full Scale Flight Test Stability During first flight test:

CG: 107 inCP: 122 inStability: 15 inMargin: 2.5

Simulated Full Scale Flight Test

The rocket was flown with a four foot upper airframe and the original nosecone, weighing 54 lbs.

Full Scale Flight Test Results

The final apogee is observed as 5007 ft, which a 315 ft (~6%) overshoot. Overshoot correlates to that found from subscale flight test.

Summary of Verifications

Full summary in section 3.4

All requirements for the launch vehicle are currently met, and no changes are expected to occur.

Payload DesignChanges since CDR:• No longer mounting a camera onboard the UAV; will instead attempt to add

Raspberry Pi 5 megapixel sensor• Controls and other systems are retained

Payload Integration

The payload needs to be carefully loaded into the rocket to ensure successful deployment; full instructions for loading payload into rocket found in section 5.1 of FRR.

Rocket is contained completely separately from all other avionics, and thus cannot interfere in any way with parachute deployment or other launch vehicle functions.

TestingUAV will undergo a battery of tests to ensure flight readiness, including:• Static test article for controls testing• Ground, charge, flight, deployment, and full scale flights testing

Interfaces

Physical interface on the vehicle are quick links and eye bolts connecting different sections through shock cord, and the Defy Gravity tether, holding the UAV to the shock cord before deployment.

Communication with the ground happens through two channels:• An X-Bee transceiver on the UAV allows communication with the ground

station• A Telemetrum Altimeter allows tracking of the vehicle during flight

Tether

The Defy Gravity tether will be used to secure the UAV to the launch vehicle, via the recovery harness, until the RSO gives permission to release.

The vehicle will be released and will descend under parachute until stable,

then unfold and flyautonomously.

Status of Requirements

A full summary of the status of requirements is given in section 4.4 of the FRR for the payload.

- UAV performs well mechanically- Structurally capable of withstanding large forces

- Unfolds successfully during separation from rocket- X-Bee modules communicate effectively with the quadrotor

- Ground station command confirmation from the UAV- Range tests of up to 2 miles

- Flight tests guarantee the stability of the system- Reliable data being read from the on-board sensors

- Successful deployment of both parachutes (main and emergency)

Questions?