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M.E.T.E.O.R. Instrumentation Platform Sponsor: Harris Corporation

M.E.T.E.O.R. Instrumentation Platform Sponsor: Harris Corporation. 2006-2007 Matt Lipschutz Rashmi Shah Adam Gutterman Jessica DeSignor Rick Frisicano Peter Rozwood. Balloon. Overview. M icrosystems E ngineering and T echnology for the E xploration of O uter Space R egions.

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M.E.T.E.O.R. Instrumentation Platform Sponsor: Harris Corporation

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  1. M.E.T.E.O.R.Instrumentation PlatformSponsor:Harris Corporation 2006-2007 Matt Lipschutz Rashmi Shah Adam Gutterman Jessica DeSignor Rick Frisicano Peter Rozwood Team # 7103

  2. Balloon Overview • Microsystems • Engineering and • Technology for the • Exploration of • Outer Space • Regions Platform Rocket Picosat Track Objective: Develop a low-cost balloon-assisted in-air rocket launch system capable of placing small (~1kg) satellite payloads into a low-earth orbit (LEO). Team # 7103

  3. Instrumentation Platform • Project Objective: • Further develop an independent balloon-lofted computational platform capable of monitoring the environment and communicating in near real time with ground control stations • Key Customer Needs: • Transition component infrastructure to MSP430 microprocessor • Design and implement RF power amplifier for video transmission • Design and implement custom portable microcontroller-based text overlay • Develop modular transient thermal model • Analyze and redesign legacy components such as radios and sensors Team # 7103

  4. Prior Power System Analysis • System power efficiency was unacceptable • Battery setup was prone to failure • Negative (-)9V was supplied from single unregulated 9V battery • Linear regulators • Voltage rails: +12, +/-9, +5, +3.3 • +/-9 and +3.3V rails each powered single device Team # 7103

  5. Improved Power System Design • Efficiency: • Linear: 3.3V at 20% efficiency to 80% efficiency using new switcher (from 18V) • Linear: 12V at 75% efficiency to 95% efficiency using new switcher (from 18V) • Surface mount parts (latest switching power supplies) • New voltage rails (+/-12, +5, +3.3) all use switching voltage regulators • Possibility of mitigating noise issues through filters Team # 7103

  6. Central Microprocessor • MSP430 chosen for homogeneity and low power consumption • Primary functions: • Process ground control commands • Data collection: • GPS: position, altitude, speed • Sensors: temperature, pressure, humidity and accelerometer • Generate data packets for the following: • Transmission to ground based receivers • Video text overlay • On-board data storage • Send commands to peripheral devices Team # 7103

  7. Sensors • Purpose: Characterize atmosphere to accurately predict launch conditions • Redesign of sensor network • Utilize I2C bus on MSP430 • Replace analog sensors with digital equivalents • Increase sensor accuracy • Decreased power consumption • Simplified data acquisition Team # 7103

  8. Video Subsystem • Multiplex between five fixed-position analog (NTSC) video cameras • Video information will be relayed to ground control stations to monitor the rocket before, during, and after launch, as well as monitoring the status of the ascent balloon and descent parachute. • Video information will also be utilized during retrieval to estimate orientation. Team # 7103

  9. Custom Text Overlay • Text is overlaid on video transmission • Acts as a redundant sensor information downlink • Text overlay is receivable without the use of specialized radios or reception equipment • Text overlay system must be “portable” • Problems with obsolete components creates demand for a portable software solution with a minimum of specialized hardware Team # 7103

  10. TV Transmitter Improvements • Increase range for which the video signal may be received • Current system range: 4 miles • New system range: Up to 100 miles • Increase power transmitted • Power transmitted > 1W • Ideal: 5W • Allow for the use of smaller less specialized receive antenna • Enable the mobile station to chase the payload while viewing its status Team # 7103

  11. TV Transmitter Design • Subsystem design meets customer needs • Transmitter: Continuously transmits video signal to ground • RF power amplifier: Increase transmit power to at least 5W • Subsystem design meets customer specifications except: • Maximum attainable range: 80 miles • Mitigations • Range cannot be increased since receiving network is predetermined Team # 7103

  12. Radio Data Link • Facilitates communication between platform and ground • Downlink: Sends position reports and sensor data • Can be received directly with specialized receivers • Data posted automatically to Internet using existing infrastructure: requires only a URL to access • Uplink: Receives commands from ground station and sends them to central processor Team # 7103

  13. Results of Previous Launch • Data received by multiple sources and posted to internet • Time of flight: approx 1.5 hours • Range: 62 mi • Max altitude: 67942 ft • Max speed: 70 mph • Data transmission failed at peak of flight Team # 7103

  14. Radio Data Link Improvements • Modularity of system: Uses multiple components that can be removed or replaced if necessary • Simplify operation • Configuration is via GUI on PC • No reconfiguration required at launch time; system will operate normally at power-up • Redundancy • Extra GPS and circuitry: Position reports are still sent even if central microprocessor fails Team # 7103

  15. Thermal Analysis • Create transient thermal model of the instrumentation platform during flight Problems: • Electronics generate heat • Properties of air change significantly during flight • Operating temperature range of electronic components Team # 7103

  16. Thermal Model Styrofoam Enclosure Feed-through holes Electronics “block” Aluminum mesh Team # 7103

  17. Thermal Results Team # 7103

  18. Risk Assessment • Loss of communication with ground control • Insufficient battery life • Inadequate processing power for text overlay microprocessor • Central microprocessor failure • Thermal issues (overheating/freezing) • Excess humidity • Midair collision Team # 7103

  19. MSD II project Schedule • 3/17/07: Send out board layout design • 4/07/07: Final debug • 4/14/07: Burst-balloon launch • 4/21/07: Zero-pressure balloon launch • 5/10/07: Cumulative design review • 5/18/07: Final presentation • Budget estimate: • $4500 (Includes burst and zero-pressure balloons, two complete boards, two launches) Team # 7103

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