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F I T S a t III Mars Airplane Package. Mechanical Engineering Dept. Aerospace Engineering Dept. Electrical Engineering Dept. Computer engineering Dept. Physics & Space Sciences Dept. Mathematical Sciences Dept. April 17 th , 2003. Introduction. History Strong Foundation Analysis

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f i t s a t iii mars airplane package

F I T S a t IIIMars Airplane Package

Mechanical Engineering Dept.

Aerospace Engineering Dept.

Electrical Engineering Dept.

Computer engineering Dept.

Physics & Space Sciences Dept.

Mathematical Sciences Dept.

April 17th, 2003

introduction
Introduction
  • History
  • Strong Foundation
  • Analysis
  • Interdisciplinary team
  • FITSat III
development stages
Development Stages
  • Design:
    • Rocket
    • Aerial Exploration Vehicle
    • Communications and Electronics Equipment
  • Construction of Scaled-Down Functional Prototypes
  • Test Launch
  • Post-launch analysis
  • Redesign
  • Construction of Full Scale Vehicles
  • Final Launch
rocket
Rocket
  • Software used
  • Configuration
  • Motor
  • Nosecone
software used
Software Used
  • Pro-Engineer
    • 3D Modeling
software for electronics
Software for Electronics
  • Circuit Maker
    • Traxmaker

Boards Used for Rocket

configuration
Configuration
  • Single-Stage Burn
  • Prototype 3 Sections
    • Computer (Upper)
    • Payload (Middle)
    • Motor (Lower)
  • Full Scale 2 Sections)
    • Computer/Payload (Upper)
    • Motor (Lower)
motor
Motor
  • Aerotech K-560W
    • Motor diameter 75 mm
    • Total impulse 2490 Ns
    • Calculated burn time 4.4 sec.
    • Maximum thrust 799 N
    • Average thrust 563 N
    • Motor length 396 mm
    • Total weight 2.750 Kg
    • Propellant weight 1.427 Kg
nosecone
Nosecone

Formula is used to compute the drag coefficient of a solid of revolution immersed in an incompressible, inviscid fluid:

We used the Prandtl-Glauert corrections to account for compressibility effects.

aerial exploration vehicle
Aerial Exploration Vehicle
  • BWB Design
  • Deployment
  • Composite construction
  • Sensing equipment
aerial exploration vehicle1
Aerial Exploration Vehicle

Objectives

  • Carry Max Payload of 6 lbs
  • Demonstrate stability in Pitch, Yaw and Roll
  • Operate at a Ceiling of 8,000 feet.
plane electronics
Plane Electronics
  • Circuit Maker
    • Traxmaker

Boards Used for AEV

wing deployment mechanism
Wing Deployment Mechanism
  • Deployable Wings
  • Design Lift Capability 10 lbs
  • Wing Span 66 inches
  • Aspect Ratio 10
  • Body length 32 inches
  • Body width 13 inches
  • Thickness of body 5.75 inches
ground control station communications
Ground Control Station Communications
  • Computers
  • Antenna
  • Video transceiver
  • Data transceiver
  • Cellular web cast
communication
Communication

Rocket and Plane contain the following:

  • 900 MHz Data Transmitter
  • 2.4 GHz Video Transmitter
  • GPS System

Prototype Electronics

electronic components
Electronic Components
  • Microcontroller based system measuring the following:
    • Static Pressure
    • Dynamic Pressure
    • Acceleration in X, Y, & Z direction
    • Temperature
what s left
What’s Left?
  • Finish construction of Full-scale rocket
  • Finalize testing of electronic components
  • Integration of systems into full-scale AEV
  • Prepare for final launch set for May 2nd at noon in Palm Bay.
thanks
Thanks
  • FitSat III would like to thank our sponsors.
  • With their support this project has become a reality.
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