1. High Powered Rocket Team Fall 2015

2. Project Manager Wesley M. Harpster Team Members James Lawrence Ryan Horton Karna Shah James “Trey” Simmons Irfan Shaukat Project Advisor Dr. Thomas Alberts Multi-Disciplinary Members Cindique Simmonds (EET) Derek Hampton (IT) Alexandre Misenheimer (Junior MAE) Amanda Nolan (Soph. MAE)

3. Overview  Project Scope  Rocket Breakdown  Avionics Bay  Flight Simulation  Commercial Motor Flights  Fuel Preparation  Research Motor Flight 1  Research Motor Flight 2  Research Motor Results  Gantt Chart  Budget

4. Project Scope  Objective Statement: To design and build a custom engine to successfully launch a rocket to an altitude of 10,000 feet with a payload of 5 pounds by the end of the fall 2015 semester with a budget of $2,500.  Acceptable Criteria  Attain a 10,000 foot flight using a purchased commercial motor with proper parachute deployment.  Successfully test and gather data for one custom motor prepared by the ODU Rocket Team

5. Rocket Breakdown  Nose Cone  Forward Body Tube  Avionics Bay  Aft Body Tube  Motor Housing  Main Parachute  Drogue Parachute

6. Avionics Bay Design Progression  Original Design  Single Altimeter Board mounted on an aluminum sled.  New Design  Two boards implemented for redundancy.  GPS system was added to locate rocket.  Back to Back arrangement to allow arming after rocket assembly.  Rail mounted for weight reduction.

7. Flight Simulation  Each flight was simulated using RASAero 2 and Open Rocket.  This produced 2 altitude levels from which an average could be taken.  The final research launch  Open Rocket = 8,104 ft.  RASAero = 8,254 ft.  Average = 8,179 ft.  Actual Altitude = 8,111 ft.  Error = 0.8314%

8. Commercial Motor Flights Commercial Flight I  Apogee: 4,029 feet  Maximum velocity: 538 m/s  Time to apogee: 15.5 sec  Flight time: 93.15 sec Commercial Flight II  Apogee: 11,960 feet  Maximum velocity: 352 m/s  Time to apogee: 25.15 sec  Flight time: 206 sec

9. Fuel Preparation  Necessary Components of a Research Motor  Propellant Base, Mixing Agent, Plasticizer, Curing Agent, Catalyst  Mixing phases for fuel 1. Liquid components (binding agent, catalyst, plasticizer) 2. Metal oxide catalyst 3. Oxidizer  Allow the mixer to run for 3-4 hours  Apply mold release to all surfaces that are not propellant tubes  Shape and press propellant into tubes and allow to cure

10. Research Motor I  Propellant Composition  Propellant Base: Ammonium Perchlorate – 76.90%  Mixing Agent: Aluminum – 5.0%  Plasticizer: Dioctyl Adipate – 3.0%  Curing Agent: R45HT-LO – 13.0%  Curing Agent: E744 – 2.0%  Catalyst: Iron Oxide – 0.1%  Comparisons to a commercial motor  This motor would be similar to a white propellant.  Such as Aerotech’s White Thunder

11. Research Motor II  Propellant Composition  Propellant Base: 74.75% Ammonium Perchlorate  Mixing Agent: 2.54% Aluminum Powder  Plasticizer: 3.5% Dioctyl Adipate  Curing Agent: 11.74% R45HT-LO  Catalyst: 0.75% Black Copper Oxide  Stabilizer: 4.5% Strontium Carbonate  Increase Strength: 0.3% Tepanol

12. Research Motor Results Research Flight I  Apogee: 3,156 feet  Maximum Velocity: 157 m/s  Time to apogee: 13.6 sec  Flight Time: 84.9 sec Research Flight II  Apogee: 8,111 feet  Maximum Velocity: 803 m/s  Time to apogee: 21.65 sec  Flight Time: 114.7 sec

13. Gantt Chart

14. Funding SourceMAE Dept. NASA ODU Grant Dr. Bawab LoanTestingMiscellaneousLaunch PrepShippingTotal Received$354.00$1,232.45$500.00$1,000.00 $3,086.45 Spent $1,500.00$971.56$250.08$696.51$50.00$3,468.15 Total -$381.70

15. Questions?