Presentation on theme: "P RELIMINARY D ESIGN R EVIEW University of North Dakota Frozen Fury Rockety Team."— Presentation transcript:
P RELIMINARY D ESIGN R EVIEW University of North Dakota Frozen Fury Rockety Team
DIMENSIONS Vehicle Length: 114 in. / 9.5 ft. Diameter: 6.0 in. Span: 12.0 in. Unloaded mass: 900.9002 oz. Fin Dimensions Root: 20.0 in. Tip: 12.0 in. Sweep length: 0 in. Semi Span: 6.0 in.
V EHICLE MATERIALS & JUSTIFICATIONS Airframe: Carbon fiber Superior strength to weight ratio Fin Birch plywood in carbon fiber Past experience with Combined materials provide a strong, rigid fin Bulk-Head / Centering-Ring Birch plywood Locally available, cabinet quality grain with few knots
S TATIC STABILITY MARGIN CP 77.6030 in CG 59.9158 in Safety Margin 2.96
P LAN FOR VEHICLE SAFETY VERIFICATION AND TESTING Flight Simulation in RockSim Verify that vehicle descends at safe velocity for recovery Recovery Subsystem: Altimeters Vacuum testing - pressure changes trigger altimeter activity Black powder ejection charges Will ensure we have enough force to separate rocket safely through various conditions Parachute Deployment Especially for drogue parachute after payload integration Testing of Batteries and Cameras Payload Testing and Confirmation Camera, Wiring, Storage Device, & Camera Mounts Stability after payload integration
B ASELINE MOTOR SELECTION AND JUSTIFICATION Motor Aerotech L2200G. This motor type is still under discussion due to the payload component weights being unknown Altitude: 5076.35 ft. ± 3.00% Diameter: 75 mm. Length: 665 mm. Burn: 2.40 sec. Thrust: 2104.9852 N. Impulse: 5051.9644 N*Sec.
T HRUST - TO - WEIGHT RATIO AND RAIL EXIT VELOCITY Thrust-to-Weight Ratio: Rail Exit Velocity:
L AUNCH VEHICLE VERIFICATION AND TEST PLAN OVERVIEW Sub-scale Construction: Now – Jan. 25 Launch: Jan. 26 – 31 Full-scale Construction: Jan 26 – Feb. 15 Test flight #1: Feb. 16 - 28 Test flight #2: Mar. 12 – 29 Final launch : May 17 – 18
RECOVERY SUBSYSTEM Our recovery system consist of altimeters, ejection charges, and parachutes. The parachutes are attached to nylon shock chord with D-rings. Black powder charges will go off based on the altimeter readings. Drogue parachute: 36 in. Deploy 5 seconds after apogee Descend at a velocity of 49.9 ft./sec. Main parachute: 72 in. Deploy at 700 ft. Descent rate of 23.4 ft./sec.
B ASELINE PAYLOAD DESIGN Hazard Detection Payload (3.1) Payload Faring/Deployment System (220.127.116.11) Liquid Sloshing Analysis Payload (18.104.22.168)
H AZARD D ETECTION P AYLOAD (3.1) Purpose: to scan the ground during decent and relay any landing hazards, in real time, to a ground station. Consist of a camera and the necessary electronics. Major challenges: Creating a 2-way communications system for the rocket. Limited video storage. Viewing video from cameras near real-time from a ground station.
P AYLOAD F ARING /D EPLOYMENT S YSTEM (22.214.171.124) Purpose: to deploy the Hazard Detection Payload Consist of an altered nose cone and mechanical separation system Nose cone: Cut into two pieces that will be friction fitted together. Each half will be attached to the body tube with hinges. Mechanical cone separation system: Separates the nose cone halves when the drogue chute is deployed Consist of a tether: one end attached to the drogue chute the other to a screw that will have levers with a gear on one end. Initially the levers will be orientated towards the base corners of the nose cone. After drogue is deployed, the tether will pull on the screw causing the levers to expand and separate the two halves of the nose cone. To prevent the halves from interfering with the camera, the hinges attaching the nose cone halves will lock once the halves are out of the cameras viewing area. Major Challenges: Drogue chute fails to exert enough force on the levers. Failure of cones separation will cause hinges to not lock.
L IQUID S LOSHING A NALYSIS P AYLOAD (126.96.36.199) Purpose: research liquid sloshing in microgravity to support liquid propulsion system upgrades and development. Experiment will be done through a partitioned tank. Liquid in one half cylinder is allowed to move freely Liquid in the other half cylinder will be controlled by a low pressure piston. Four cameras used to collect data: Each tank will be filmed by two cameras. Two cameras are positioned along the body tube 180° from each other. Another two are positioned on the top of one tank, and the bottom of the other Top choice for camera: GoPro HD Hero 960 helmet camera 60 frames per sec, 848x480 resolution. The data from the cameras will be stored onboard. Analyzed post flight. Major challenges: Developing the appropriate software to analyze the video taken by the cameras Ensuring the rocket remains balanced.
P AYLOAD VERIFICATION AND TEST PLAN OVERVIEW Hazard Detection Payload (3.1) Require static ground tests to determine the abilities the camera and software in identifying potential landing hazards. Testing before and after payload integration to launch vehicle. Payload Faring/Deployment System (188.8.131.52) The mechanical system will require static ground tests to determine the force required to separate the nose cone. Liquid Sloshing Analysis Payload (184.108.40.206) Several dynamic ground tests to measure the liquid sloshing patterns Allow us to determine liquid patterns in standard gravity. Will use this data to compare with data collected in-flight.