USLI Flight Readiness Review

1. USLI Flight Readiness Review Harding University Flying Bison 2010 USLI Rocket Team

2. Harding Flying Bison Team Team made up of 16 members with diverse educational backgrounds: Greg Libby Elizabeth Hunter Matt G. April Josh Lisa Darah Chi Patrick Matt I. Meredith Cortney Shailer Ed

3. Organization Seven Divisions Airframe Greg, Mgr. Motor Matt G., Mgr. Science Payload Darah, Mgr. Avionics Chi, Mgr. Launch Operations Matt I., Mgr Recovery Patrick, Mgr. Outreach Elizabeth, Mgr. Team Official & Safety Officer Ed Project Progress Cortney

4. Mission Statement • Design, build, test and fly a hybrid rocket • Achieve an altitude of exactly 1.00 mile • Measure gamma radiation as a function of altitude • Measure temperature and pressure • Measure x-, y-, z- acceleration during flight • Done safely with no injuries, no damage to property • Rocket recovered without damage

5. Airframe Length 93.55 inches 7.5 feet Diameter 4.09 inches Span Diameter 14.09 inches Estimated Mass 241.39 ounces15.03 pounds

6. Airframe Center of Pressure 72.22 in Center of Gravity 55.0 1in Margin of Stability4.30 body calibers over stable

7. Scale Model Test & Competition Rocket Test We were not able to do a scale model test as planned because some key supplies were missing. We found out in the process that our ignition system has become defective. We are purchasing a new unit. We plan our full scale test on 21 March 2010.

8. Thrust to weight motor selection in flight simulation Average Thrust = 896 N Mass 241.39 g + 4173 g = 4.414 kg Weight = 43.31 kg Thrust to weight ratio = 20.7

9. Rail Exit Velocity Launch guide length: 94.0000 In. Velocity at launch guide departure: 77.2523 ft/s The launch guide was cleared at : 0.203 Seconds User specified minimum velocity for stable flight: 43.9993 ft/s Minimum velocity for stable flight reached at: 31.0498 In.

10. Parachute sizes and descent rates • Drogue is a 24” Classic II Sky Angle Parachute • P: Drogue Parachute Deployed at : 18.384 Seconds • Velocity at deployment: 7.3339 ft/s • Altitude at deployment: 5678.14961 Ft. • Main is a SkyAngle CERT-3 Large. • P: Main Parachute Deployed at : 119.385 Seconds • Velocity at deployment: 47.5640 ft/s • Altitude at deployment: 799.99344 Ft.

11. SkyAngle Cert-3 Parachute

12. Test plans and procedures Tensile strength tests run for: Shock cord – 3/8 in. Kevlar U-Bolts – ¼ in diameter Knots – Bowline Bulk plates/coupler

13. Test Configuration

14. U-Bolts, Shock Cord, Bulk Plates

16. Failure at 1000 lbf Tests stopped after Kevlar cord began to fray at 961 lbf at the knot The Kevlar shock cord would not have separated until more force applied

17. Further Required Testing Full scale flight test - planned for 21 March 2010 Dual deployment avionics test test - planned for 21 March 2010 Ejection charge amount test test - planned for 21 March 2010 Payload integration feasibility – Payload is fully integrated into the rocket

18. Payload • Science payload consists of: • Flight computer number 1 • Flight computer number 2 • Embedded microcomputer system • Radiation counter • Temperature sensor • Pressure sensor • x-, y-, z- accelerometers • Battery power supply

19. Payload • Science instruments, flight computers, recovery transmitter and batteries fit inside 3.78 in diameter by 12.0 inch long phenolic coupler tube • Switches ,status LEDs, computer connectors mounted on ring in the middle of the coupler

20. Payload • Science Payload Objectives. • Test and calibrate a Geiger-Mueller radiation counter • Interface Geiger counter to embedded controller to operate the instrument and collect and store the data. • Test the complete instrument mounted in the airframe using laboratory alpha, beta and gamma radiation sources. • Test and calibrate pressure sensor • Test and calibrate a temperature sensor • Test and calibrate a low sensitivity and a high sensitivity 3-axis accelerometer

21. Payload • State the payload success criteria Payload success will be achieved if all the sensors perform satisfactorily and data from each is collected and stored in the on-board computer memory.

22. Science Payload

23. Payload Side profile of science payload with circuit boards and batteries mounted

24. Motor Contrail Rockets Certified K-888-BM Hybrid Motor Diameter of motor 75 mm Length of Motor 40.0 inches Nozzle medium Fuel Grain Used Black Smokey

25. Motor Exit end of nitrous tank showing fill and overfill lines

26. Motor Ignition -- Pyrodex Pellets Ignited with Resistors

27. Motor Tripoli Rocketry Association, Inc., Certification

28. Motor

29. Avionics The recovery subsystem is composed of the following components: • PerfectFlite MiniAlt/WD to measure and store altitude and deploy drogue and main parachutes. • DT2x Data Transfer Kit for connecting MiniAlt/WD to computer • G-Wiz MC-2.0 Flight Computer to provide redundant backup of the PerfectFlite • Nine pin female to female cable with subminiature D connectors to connect G-Wiz MC-2.0 to computer

30. Avionics • Software to download data from G-Wiz • Ejection charges with electric matches to deploy parachutes • SkyAngle Main Parachute with 57 square feet • SkyAngle Drogue Parachute with 6.3 square feet • Shock cord – to be determined • Walston Retrieval System with Rocket Transmitter, 3-Channel Receiver, and 3-element Antenna

31. AvionicsDual Deployment Avionics Test • Test planned for 21 March 2010 PerfectFlite MiniAlt/WD Official USLI Altimeter and Flight Computer

32. Avionics G-WIZ MC-2 Backup Altimeter and Flight Computer

34. Launch Operations • We plan to assemble the motor ahead of time, so that all we have to do is load the nitrous • Draft Launch Plan in Appendix A in CDR, Page 29

35. RecoveryEjection Charge Amount Test • Test planned for middle of 21 March 2010 • Walston Retrieval System for Rocket Locating • SkyAngle 24 in for Drogue • SkyAngle Large Cert-3 for Main

36. Acknowledgement We gratefully acknowledge support from NASA/Arkansas Space Grant Consortium A part of the National Space Grant Program