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Flight Readiness Review

The Efficiency of Flexible Solar Panels and Changes in the Earth’s Magnetic Field at Altitude. Flight Readiness Review. Vehicle Summary. Top Nosecone Payload Flip-Out Rotor Blades. Middle Drogue Parachute Altimeters Housing for Rotor Blades. Bottom Main Parachute Motor (Plugged)

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Flight Readiness Review

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  1. The Efficiency of Flexible Solar Panels and Changes in the Earth’s Magnetic Field at Altitude Flight Readiness Review

  2. Vehicle Summary Top Nosecone Payload Flip-Out Rotor Blades Middle Drogue Parachute Altimeters Housing for Rotor Blades Bottom Main Parachute Motor (Plugged) Fins • Total length of 116.5 inches • 4.0” Airframe (3.9” Inside diameter) • BlueTube 2.0 • Separates into three sections • 22.3 pounds with motor • 17.0 pounds without motor

  3. Payload Summary • Studying the efficiency of flexible solar panels, and changes in power output • Also investigating changes in the earth’s magnetic field • Housed in the Modular Payload System (explained later)

  4. Vehicle Changes • Piston added to the main parachute compartment to deploy the main parachute • Hinges on flip out rotor blades have been upgraded from mouse traps to small door hinges with rat trap springs • Dry weight is now 17.0 pounds

  5. Payload Changes • Slots in the Modular Payload System have been enlarged to slide over solar panel wires • Reduces the risk of shearing wires inside airframe • Because of the solar panel, a hole cannot be drilled through the airframe to verify payload on pad • Payload will have to be activated and verified before installing

  6. Motor Selection • Aerotech K828 FJ • 54/2560 mm casing • Proven to take rocket to projected altitude

  7. Estimated Rocket Performance • Estimating a coefficient of drag of around 0.55 • Dry weight of 17.0 pounds Note: Simulations calculated with 5 mph winds

  8. Motor Thrust Curve

  9. Rocket Flight Stability Margin CG Position: about 74 inches from nose CP Position: 87.5 inches from nose • Center of gravity 73.4 inches from nose • Center of pressure 87.5 inches from nose • Stability margin of 3.50 calipers • Stability of 4.86 calipers after burnout Stability Margin: about 3.38

  10. Thrust to Weight Ratio • Thrust to weight ratio is 8.35 to 1 • High acceleration of approx. 459 m/s2 (14 g’s) Acceleration (ft/s2) vs. Time (s)

  11. Rail exit velocity • 8 ft Rail = 75.0 ft/s • 10 ft Rail = 83.3 ft/s • 12 ft Rail = 90.8 ft/s • Planned to launch using a 10 ft rail • 12 ft rail was used for test flight • Lugs compatible with Standard 1” Black Sky Rails

  12. Parachute Sizes and Descent Rates • Drogue parachute: 24 inch diameter TAC-1 • Four flat strap nylon suspension lines • Deploys at Apogee (backup charge 2 seconds later) • Drogue descends at approx. 71 ft/s • Swivels are attached to each parachute • Additional swivel attached to drogue mount

  13. Parachute Sizes and Descent Rates • Main parachute: 84 inch diameter TAC-1 • Four flat strap nylon suspension lines • Deploys at 700 feet (backup charge at 500 feet) • Estimated descent rate of 19 – 20 ft/s • Drift in 5 mph= 500 feet • Drift in 10 mph= 900 feet • Drift in 15 mph= 1800 feet Large Margin of Error

  14. Test Plans and Procedures • BlueTube airframe was able to withstand 300 pounds of force of compression without signs of failure • 350 degrees for 30 minutes = ⅛” increase in circumference • Freezer for 30 minutes = No notable change • Underwater for 30 minutes = Tube began to wrinkle • 5 hours in sun = No warping found

  15. Test Plans and Procedures • Decal radiant heat test • A precaution for BlueTube warping from uneven heating

  16. Test Plans and Procedures • Exposed to light for 10 minutes (temp leveled off) • Four trials in 2 different positions to limit bias • Replacing black with white in color scheme

  17. Test Plans and Procedures- Assembly • Before loading ejection canisters with black powder on launch day continuity will be verified in all electric matches with altimeters • No cell phones or unnecessary electronics in work area • Parachutes and piston are to be coated in talcum powder before installing • All six quick-links must be verified at least once by two or more people • At launch pad igniter is to be installed AFTER activating altimeters

  18. Test Plans and Procedures • All sensors for payload have been verified and function as planned • Sensors must be zeroed before use for best results • Accelerometer • Held up for 5 seconds, down for 5, shook, then hit against palm

  19. Test Plans and Procedures • The magnetic field sensor was rotated clockwise to check functionality • Peak readings when pointed to magnetic south (geo graphic north) as expected • Does not appear to be affected by other sensors

  20. Test Plans and Procedures • The ground station has been completed and tested • Solar panel, current probe, voltage probes, and resistors are set up like in rocket • In full sun 1.184 V around 10 ohm resistor and .2491 A • Total voltage difference = 9.12 V, Total power = 2.27 Watts

  21. Full Scale Flight Test • Feb 26th Launch cancelled to lack of FAA waiver • One full scale flight was completed on Sunday, March 6th • Notable turn into wind off of launch rail

  22. Full Scale Flight Test • NO main parachute deployment • Rocket landed under drogue in soft field • Only damage to rotor blade hinges • Altimeters read 5219 feet and 5267 feet

  23. Full Scale Problems • Main parachute was stuck in airframe • All flights suspended until problem resolved • Next launch cancelled because of problem, high winds, and closing of field in Waco Full Scale Conclusion • Rocket structure can handle forces of flight • Main parachute system now resolved • Rotor blades repaired and upgraded • Ready for flight

  24. Dual Deployment Avionics Test • Completed on Monday, December 13th • Altimeters placed in a vacuum chamber • Both altimeters showed a drogue and main deployment • All ejection charges were detonated during launch

  25. Ejection Charge Amount Test • Drogue parachute tests completed February 19th and February 21st • 2.3 grams of FFFF black powder • Successful separation, deployment of drogue, and deployment of rotor blades

  26. Ejection Charge Amount Test • Main parachute tests on February 21st, March 12th, 18th, and 19th • On Feb. 21st parachute pulled roughly halfway out of tube • Minimal force required to release parachute • Parachute was believed to deploy on the 21st, because drogue parachute would act as a pilot chute

  27. Ejection Charge Amount Test • Parachute failed to separate from airframe on first test launch • Tests were redone with parachute packed tighter and talcum powder • Test failed to pull out parachute • Lack of moving mass, lack of force

  28. Parachute only halfway out of airframe

  29. Main Parachute Ejection Options • Add more black powder • Add mass to electronics bay • Wrap shock cord around parachute • Use a piston recovery system • Use a parachute bag • Move separation joint closer to parachute • Attach a ball below parachute to pull out parachute

  30. Main Parachute Ejection • On 7th main parachute test (10th overall) main parachute ejects with a piston system

  31. Payload Integration Feasibility • All sensors and data logger are made by Vernier Software and Technology • Data logger is also power source for all sensors • LabQuest has been modified by Vernier to fit into the payload airframe • To retrieve data the data logger unit must be retrieved

  32. Payload Integration Feasibility • All units contained in the Modular Payload System (MPS) • Constructed out of birch plywood • Two ¼” threaded steel rods for structural integrity • Excess wiring will be coiled and stored in bottom section of MPS • Slots cut in bulkplates to allow for wiring to pass from one section to another • Must be installed facing specific direction to slide over solar panel wiring

  33. Modular Payload System

  34. Payload Integration • Slots in MPS slide over solar panel wiring Terminal block where positive and negative leads from solar panel connect to payload

  35. Removal of the MPS • Nosecone must be removed • A strap will be connected to the two stainless steel rods the can be used to pull out the MPS • When the mid section is exposed the wires from solar panel are disconnected • The entire unit is taken to computer for data retrieval via USB cable

  36. Educational Engagement Plan & Status • Status: Complete • 160 Students engaged at Rockwall-Heath High School • February 10th- Students designed fins in Rocksim and constructed fins at home • February 14th- Approximately 80 rockets were built during school hours. All parts were supplied other than fins and egg padding • February 26th- Rockets were launched at Tate Farms, a local ranch

  37. Educational Engagement Plan & Status • February 15th and 16th the team visited Cain Middle School • Students who volunteered to stay after school received a brief presentation • Students then built rockets from paper and other scratch materials • Rockets were launched on February 26th as well

  38. Questions? ∆t Delta-T Ltd. www.deltatltd.com

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