Jordan High School Rocketry Team. A Roll Stabilized Video Platform and Inflatable Location Device

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1 Jordan High School Rocketry Team A Roll Stabilized Video Platform and Inflatable Location Device

2 Mission Success Criteria No damage done to any person or property. The recovery system deploys as expected. The rocket is retrievable with the help of the balloon payload. The flywheel is able to diminish roll. The position transmitter takes valid measurements. Rocket Alignment Device allows for no-roll video.

3 Last Year s Project We ended the year with no one harmed and no property damaged. Our rocket continuously reached an apogee close to the goal. Our rotational device worked for 10s on the last flight. We hope to improve it this year.

4 Last Year s Project Flight in AL

5 Last Year s Project Flight in AL Data

6 Vehicle Dimensions / Design Payload Bay #1 houses the ILD (Inflatable Location Device) Payload Bay #1 Payload Bay #2 houses the RAD (Roll Alignment Device) Parachute Camera Housing Drogue Chute Transmitter Bay Motor Altimeter Bay Payload Bay #2 Ballast

7 Vehicle Dimensions / Design Length: 89 in Max. diameter: 4 in Mass w/ motors: 23.6 lbs Stability: 2.41 cal CG: 60.6 in CP: 70.5 in Apogee: 5,367.5 ft Max. velocity: ft/s (mach 0.62) Max. acceleration: ft/s^2 2 lb increase since PDR 273 ft. decrease in apogee prediction 65.1 ft. decrease in max. velocity 51.9 ft. decrease in max. acceleration

8 Vehicle Materials 48 long 4 diameter airframe tube 48 long 4 diameter airframe coupler tube 4 ogive nose cone (4:1) Ring/Bulkhead: Baltic Birch Fin end-grain balsa wood and half-round hardwood for edges Fin Carbon Fiber Altimeter Phenolic motor mount tube 3 motor retainer Nylon Shock Cord Raven3 Altimeters Raven Perches Altimeter Batteries Ejection Charge Canisters Rail buttons main parachute 2 drogue parachute Nomex protection JB weld Z-poxy 30 minute 8 oz glue Motor Case (75 mm) K1000T motor Bolts, quick links, all-thread, nuts, and i nuts Spray paint

9 Justifications for Design Fins: Aren't swept to prevent breakage Four fins for easy alignment Shape for aerodynamics, stability, and looking cool Rounded edges for simplicity to reduce construction errors Size: Larger diameters created too much drag to reach one mile with a K motor Shorter to decrease mass 4 because our current RAD was designed for this size Mass: Heavier than PDR

10 Motor Selection and Justification K1000T by AeroTech It is within parameters and allows us to hit the right altitude

11 Flight Stability Stability: 2.4 Calibers CG (center of gravity): 60.6 inches CP (center of pressure):70.5 inches

12 Thrust-to-Weight Ratio and Rail Exit Velocity Thrust-to-Weight Ratio: 8.9 (average thrust) Rail Exit Velocity: 70 ft/s

13 Mass Statement The mass has increased from 21.7 lbs in the PDR to 23.6 lbs. The major contributors to this change are: A new brass flywheel design (about 170% heavier). Added about 2.78 lbs. A error in the mass of the motor/fin airframe tube saved us about 1.76 lbs. A glue and paint allotment of 0.9 lbs was added. The ILD design added about 0.26 lbs to the nose cone payload bay. Other small corrections to the mass of various components as we obtained/built them.

14 Recovery System 2 foot parasheet drogue chute; descent rate of 65 ft/s (subscale) 7 foot ripstop nylon main chute, including small pilot chute; descent rate of 15 ft/s 30 foot nylon shock cords, ½ inch in width Descent rate is calculated using the velocity of last year s rocket (which was flown using the same parachute) D= ½ pcdav2

15 Recovery System Testing Recovery system is the same as the one used in previous years with no negative results; empirical evidence that the system is functioning properly We have tested the elasticity of the shock cords multiple times (left) Ideal Gas law and Hooke s law to determine the tension on the shock cords during parachute ejection

16 Kinetic Energy Ke = ½mv2 Component Mass (lb) Descent Rate (ft/s) Kinetic Energy (ft-lbf) Nose Cone Parachute Bay Motor Section Main Chute and 1.67 Cord Drogue Chute and Cord

17 Drift Calculations Values taken from OpenRocket simulations Simulation Apogee (ft) Max. Velocity Lateral (ft/s) Distance (ft) Ground Hit Vertical Velocity (ft/s) 0 mph wind mph wind mph wind mph wind mph wind

18 Drift Calculations

19 Vehicle Safety and Testing Full-scale launches will take place beginning in March All full-scale flights will be full power with running RAD. Previous flights have proven rocket stability with this payload. Verification tests on vehicle Airframe strength, black powder charges for full scale, etc. ILD will eventually be integrated and verified during BP tests All vehicle-related failures listed have been considered and accounted for Rocket over/underpowered, parachute tangles, etc.

20 Subscale Flight Rocket completed 1/7/16, flown 1/11/16 with a G80-13T motor Drogue deployment one second after apogee, and main deployment at 288 ft. Predicted apogee at 1036 ft, observed apogee at 968 ft. Possible explanation for disparity Vectored thrust, evident from nozzle wear Difference in simulated/actual temperature Lower calculated drag coefficient Slight asymmetry in camera bay mounting

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22 Payload Design Our payload this year consists of two parts: Roll Alignment Device (RAD) Located in the payload bay (between altimeter and motor sections) Designed to eliminate roll through the use of a spinning flywheel Inflatable Location Device (ILD) Located in the nose cone Designed to aid in rocket retrieval after landing

23 Vehicle Materials: Payload ILD RAD Flywheel Balloons VESC motor controller Fishing line Bulkhead Motor and Electronic Batteries Auxiliary Board UDB5 Microprocessor 3DR Radio All thread Support

24 Last Year s RAD

25 New RAD Design

26 New RAD Design

27 RAD Verification and Testing Testing of motion sensors Testing the flywheel motor Testing the system as a whole

28 Inflatable Location Device

29 Inflatable Location Device

30 ILD Verification and Testing Visibility Testing Ability to Float Survivability of the Balloons Inflation with Changes in Pressure

31 Outreach Activities planned for local middle school; initiation of a middle school TARC team Participation in Astronomy Days RAD used as an entry in JHS Science Fair; first place in engineering category