49er Rocketry Conceptual Design Review_2_ by pptfiles


 • Mission
 • Performance goals
 • Requirements
 • Payload Module
  • Component selection
  • Electronics flow chart
  • Data flow chart
 • Launch Vehicle
  •   Construction
  •   Propulsion
  •   Static Margin
  •   Motor Selection
  •   Recovery
• 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
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
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
                 • 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

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:
 • 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
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
   • 1 Featherweight Raven Altimeter
• 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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