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49er Rocketry Conceptual Design Review

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49er Rocketry Conceptual Design Review Powered By Docstoc
					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.
                                At Apogee the

Flight Plan             3       payload chute
                                   deploys




                                                Payload descends to the
                                                     landing Zone
                                                4



            Payload
             ejects
        2




        1
             Rocket
            Launches        5
                       Landing Zone
Payload Module

Component Selection
• Microcontroller             • Digital Camera
  • Arduino Mega 2560         • Transmitter and
• Payload Sensors              Receiver
  • Pressure Sensor            • 900MHz X-bees
  • Humidity Sensor           • Battery
  • Temperature Sensor
  • Solar Irradiance Sensor
  • UV Radiation Sensor
  • Strain Gauges
Payload Module

Electronics Flow Chart

               Temperature                                    Solar
Strain Gauge                  Humidity   Pressure                       Ultra Violet
                 Sensor                                    Irradiance
                               Sensor     Sensor                          Sensor
                                                             Sensor




     SD card                 Arduino                Xbee                        Xbee   Ground Station




                             Camera
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
                       Motor Details
          Diameter (mm)                    54
          Length (cm)                     57.9
          Propellant Mass (g)            1188
          Average Thrust (N)             249.8
          Max Thrust (N)                 438.4
          Burn Time (s)                   7.9
          Total Impulse (Ns)             1968
          G (m/s^2)                       9.81
          K270W Max Acceleration (g's)    3.59

  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

          Boosted Dart                        Finn
            Payload                           Can
                             Transition
       Payload           Spring Mechanism
      Parachute




   Payload                           Booster Can
 Drogue Chute                       Main Parachute
 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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