1 / 23

Project Bellerophon April 17, 2008 Avionics

Project Bellerophon April 17, 2008 Avionics. Overview. 1. Electronic Parts: Component Rating. 1 NASA Electronics Parts Assurance Group. 2. Telecom Analysis: Doppler Shift. Frequency Shift due to Doppler Effect. 3. Telecom Analysis: Data Rate. Change in Link Margin due to Data Rate.

xylia
Download Presentation

Project Bellerophon April 17, 2008 Avionics

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Project BellerophonApril 17, 2008Avionics Avionics AAE 450 Spring 2008

  2. Overview Avionics AAE 450 Spring 2008 1

  3. Electronic Parts: Component Rating 1 NASA Electronics Parts Assurance Group Avionics AAE 450 Spring 2008 2

  4. Telecom Analysis: Doppler Shift Frequency Shift due to Doppler Effect Avionics AAE 450 Spring 2008 3

  5. Telecom Analysis: Data Rate Change in Link Margin due to Data Rate Avionics AAE 450 Spring 2008 4

  6. Telecom Analysis: Path Length Change in Link Margin due to Signal Path Length Avionics AAE 450 Spring 2008 5

  7. Telecom Design: Vehicle Link Budget Simplified Link Budget Minimum Margin: 3 dB Vehicle Margin: 39.2 dB Avionics AAE 450 Spring 2008 6

  8. Range Safety: Personnel • Range Safety Officer (RSO) • An individual who is responsible for the remote destruction and consequent flight termination of the launch vehicle should it be deemed a hazard. • RSO Responsibilities • Evaluate the launch vehicle design as well as oversee the manufacturing process. • Monitors the launch vehicle and environmental conditions prior to launch. • Monitors and tracks the launch vehicle during flight. • Hiring • Budget $1,700 per launch, assuming a 5 day period. Avionics AAE 450 Spring 2008 7

  9. Range Safety: Flight Corridor • Flight Corridor • An imaginary zone that exists in a space above the launch range. • Application • Implemented so that if the launch vehicle where to experience a failure during flight, the vehicle will fall to the ground in an uninhabited area. • Termination • The launch vehicle must be destroyed if it flies outside the predetermined flight corridor. Avionics AAE 450 Spring 2008 8

  10. Non-Space-Rated Sensors Avionics AAE 450 Spring 2008 9

  11. Space-Rated Sensors Avionics AAE 450 Spring 2008 10

  12. Sensor Reliability Analysis: Thermal This table details the reasons for differences in cost. Avionics AAE 450 Spring 2008 11

  13. Power Supply: Power Budget 200g Payload Case, Silver Zinc Battery, Balloon Launch Avionics AAE 450 Spring 2008 12

  14. Power Supply: Battery Selection Avionics AAE 450 Spring 2008 13

  15. Power Supply: AgZn Battery AgZn Benefits • Can charge 4 to 6 times in case of scrub • Capable of controlling gimballing, ignition, and range safety subsystems 1http://www.eaglepicher.com/ Avionics AAE 450 Spring 2008 14

  16. Power Supply: Batteries Estimate Cost: < $10,000 Weight: 2.3-4.5 kg Avionics AAE 450 Spring 2008 15

  17. Installation Cost Primary Contractor: Aircraft Electrician 1 Salary data from www.salary.com Avionics AAE 450 Spring 2008 16

  18. Telecom: Failure Analysis Reliability Factors For a low complexity system with redundancy1: Part ClassReliability Class B: 98.75% Class S: 99.87% Assumptions - Simple system - Low radiation dose - Reliability based on a five year mission plan 1 Wertz, 404. Avionics AAE 450 Spring 2008 17

  19. Mass Budget • First Stage: 6.024 kg total (safety factor=1.2) -wiring: 2kg -sensors 1.02kg -battery 2kg • Second Stage: 30.2664 kg total (safety factor=1.2) -Telecom: 10 kg -CPU: 0.85 kg -Sensors: 1.02 kg -Range Safety: 9.23 kg -Wiring: 2 kg -IMU: 0.122 kg -Battery: 2kg • Third Stage: 1.2 kg total (safety factor=1.2) -Wiring: 1 kg Avionics AAE 450 Spring 2008 18

  20. Payload: Launching Options • Launch lock (US Patent 6508437) • Motorized release • Explosive Bolt/Spring sequence1 • Explosive/Slingshot Sequence 1(Professor Filmer), (International Reference Guide to Space Launch Systems pg 296) Avionics AAE 450 Spring 2008 19

  21. Signal Projection: Assumptions • Assumptions Made • The Earth is spherical in shape. • The area where the signal intercepts the Earth is circular. • Neglect any antenna mounting errors or design issues. • Neglect any atmospheric anomalies which may refract the signal. • The signal propagation from a cluster of directional antennas can be estimated using a omnidirectional antenna. • The signal propagation from an omnidirectional antenna is spherical in shape. Avionics AAE 450 Spring 2008 20

  22. Launch Vehicle Tracking Example Case: Small Payload Launch Vehicle 1Professor Filmer, Purdue University School of Aeronautics and Astronautics Avionics AAE 450 Spring 2008 21

  23. Avionics: Cost Budget Avionics AAE 450 Spring 2008 22

More Related