49ER ROCKETRY NASA USLI PRELIMINARY DESIGN REVIEW 2012-2013 Agenda • Mission • Performance goals • Requirements • Payload Module • Component selection • Electronics flow chart • Data flow chart • Launch Vehicle • Construction • Propulsion • Static Margin • Motor Selection • Recovery Mission • NASA USLI Competition • The NASA University Student Launch Initiative involves students in designing, building and testing of reusable rockets with scientific and engineering payloads. • Mission Statement • The mission of the 49er USLI team is to design and build a rocket capable of carrying a payload to an altitude of 5,280ft. The payload will eject from the booster at motor burnout using forced separation with a spring. The immediate separation will allow for maximum transfer of momentum to an aerodynamic dart. This could be implemented for the design of other boosted darts that need nontraditional separation using a renewable energy source. The payload experiment will serve as a means of data acquisition for dart boundary conditions as well as a collection method of altitude specific scientific reading. Performance Goals • Payload • SMD data Acquisition • Strain behavior of dart • Descent imaging • Rocket • Altitude 5280 Feet • Stable Flight • Renewable, Forced Separation • Safe Recovery Requirements 1.The launch vehicle shall carry a scientific or engineering payload 2.The launch vehicle shall deliver the payload to 5,280ft 3.The launch vehicle and payload shall remain subsonic from launch until landing 4.The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of 1 hour without losing any functionality 5.The launch vehicle shall be launched from a standard firing system using a standard 10 – second countdown 6.The launch vehicle shall use a commercially available solid motor using ammonium perchlorate composite propellant (APCP) 7.The total impulse of the launch vehicle shall not exceed 5,120 Newton-seconds 8.The maximum amount teams may spend on the rocket and payload is $5000 total, this includes all purchased components and materials and the fair market value of all donated components and materials. Flight Plan Payload Module Component Selection Digital Camera • Microcontroller • Arduino Mega 2560 • Transmitter and Receiver • Payload Sensors • 900MHz X-bees Pressure Sensor • Humidity • Battery Sensor • Temperature Sensor • Solar Irradiance Sensor • UV Radiation Sensor • Strain Gauges Payload Module Electronics Flow Chart Launch Vehicle Construction Propulsion Static Margin • Body components • Motor selection • CP and CG • Carbon Fiber Body • Aerotech K270 White Lightning Launch Vehicle and Dart Static Margin Calculated Cp: in Calculated Cg: in Simulated Cp: 70.11 in Simulated Cg: 61.69 in Static Margin- A convention of saying how stable a rocket is the distance between the center of gravity and the center of pressure. - A positive number denotes the design is stable. Simulated Static Margin: 2.69 Upon half scale launch, adjust can be made: -Semi Span -Nose Mass Dart Static Margin Calculated Cp: 35.9 in Simulated Cp: 36.8 in Calculated Cg: 29.0 in Simulated Cg: 29.3 in Simulated Static Margin: 2.38 Both dart and launch vehicle/dart flight will be stable. • Dart flight will be slightly more stable than the flight of launch vehicle and dart. Motor Selection Aero Tech K270W – White Lightning Velocity at launch guide departure: 47 feet per second Spring Separation System • Release • Nychrome burn of spring retaining 550 paracord • Nylon Burns: 110-220°C • Nychrome Temperature: 1004°C • Spring Functionality • Spring force breaks shear pins releasing dart. • Compression: 0.66 inch • Force 79.2 lbs • Manufacturing/Materials Recovery Overview Launch Vehicle-Recovery Separation Method Recovery Method • Fincan/Recovery Bay Separation • Main Parachute • Pyro Charge • 50in Diameter • 1.33g 4F black powder • Decent rate of 22.89 ft/s • Main Parachute Deployment at • Tracking 800ft • Big Red Bee • Altimeters • 2 Featherweight Raven Altimeters Dart-Recovery Separation Method Recovery Method • Dart Separation • Drogue Parachute • Nychrome burn of 550 paracord • 18in Diameter • Altimeters provides 0.73 amps to 5 • Decent rate of 46.7 ft/s inch Nychrome wire • Main Parachute • 1004°C wire temp • 50in Diameter • Nose Cone Separation • Decent rate of 16.8 ft/s • Pyro Charge • Tracking • 2.4g 4F black powder • Big Red Bee • Drogue Parachute at apogee • Main Parachute Deployment at 800ft released with cable cutter • Altimeters • 1 Perfect Flight Perfectflite Stratologger Altimeter • 1 Featherweight Raven Altimeter Overview • Total Weight • 20lb • Estimated Total Cost Rocket • $2,300 • Feasibility of the rocket based upon preliminary calculations and simulation data shows that the rocket can be constructed within the budgetary requirements and will have a stable flight.
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