1. Illinois Space Society Tech Team USLI FRR Presentation

2. Contents Vehicle Specifications Performance Characteristics Recovery System Flight Predictions and Testing Payload

3. Vehicle Design Modified Ultimate Darkstar kit with dual deploy UAV deployment at apogee Three split fins AeroTech L2200 motor 24" Von Karman nosecone

4. Vehicle Dimensions Length: 126 in Diameter: 6 in Component dimensions shown:

5. Final Motor Choice Aerotech L2200 75 mm motor, Aeropack retainer and adapter

6. Motor Characteristics Max Thrust 3101.8 N Average Thrust 2246.6 N Total Impulse 5104 Ns Mass pre Burn10.55 lbs Post Burn 5.55 lbs

7. Stability Analysis CG 14.4 inches above CP Static stability margin of 2.34 Marginally overstable, but well within acceptable bounds

8. 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

9. 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

10. Recovery System Overview

11. 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

12. Kinetic Energy at Key Phases Kinetic Energy During Descent (ft-lb) Under drogue: Nosecone:172.5 Upper airframe/ coupler:913.4 Booster airframe:1822.5 UAV:431.3 Under main: Nosecone:6.57 Upper airframe/ coupler:34.77 Booster airframe:69.38 UAV descends separately from rocket.

13. 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) 55064600 1050421250 1550091900 2049602600

14. Predicted Performance Final launch vehicle predicted performance

15. 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.

16. 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.

17. Full Scale Flight Test Stability During first flight test: CG: 107 in CP: 122 in Stability: 15 in Margin: 2.5

18. Simulated Full Scale Flight Test The rocket was flown with a four foot upper airframe and the original nosecone, weighing 54 lbs.

19. 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.

20. 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.

21. Payload Design Changes 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

22. 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.

23. Testing UAV 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

24. 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

25. 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 fly autonomously.

26. 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)

27. Questions?