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F I T S a t III Mars Airplane Package

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 4 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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  1. 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 4th, 2003

  2. Introduction • History • Strong Foundation • Analysis • Interdisciplinary team • FITSat III

  3. 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

  4. Rocket • Software used • Configuration • Motor • Nosecone

  5. Software Used • Pro-Engineer • 3D Modeling

  6. Pro/Mechanica • Structural Analysis

  7. Rocksim • Static Stability

  8. Configuration • Single-Stage Burn • Prototype 3 Sections • Computer (Upper) • Payload (Middle) • Motor (Lower) • Full Scale 2 Sections) • Computer/Payload (Upper) • Motor (Lower)

  9. 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

  10. EAS O3600 Motor • 45.5” Long • 6” Diameter • Propellant Weight 20 kg • Actual Burn Time 5.9 secs • Total Thrust 29850 Ns

  11. 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.

  12. Aerial Exploration Vehicle • BWB Design • Deployment • Composite construction • Sensing equipment

  13. Objectives • Carry Max Payload of 6 lbs • Demonstrate stability in Pitch, Yaw and Roll • Operate at a Ceiling of 8,000 feet.

  14. 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

  15. Ground Control Station Communications • Computers • Antennae • Video transceiver • Data transceiver • Cellular web cast

  16. Rocket and Plane contain the following: • 900 MHz Data Transmitter • 2.4 GHz Video Transmitter • GPS System

  17. Microcontroller based system measuring the following: • Static Pressure • Dynamic Pressure • Acceleration in X, Y, & Z direction • Temperature

  18. Conclusion • Timelines • Worthiness for Students • Worthiness for Industry Etc, etc, etc…

  19. What’s Next? • Begin construction of Full-scale rocket • Finalize testing of electronic components • Integration of systems into full-scale AEV • Prepare for final launch set for beginning of May.

  20. Thanks • We’d like to thank our sponsors. Without their support this project wouldn’t have become a reality.

  21. Questions?

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