F i t s a t iii mars airplane package
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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

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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.


Questions

Questions?


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