Maine Space Grant Consortium
- View government funding actions
- Augusta, ME 04330
- Phone: 207-622-4688
- Corporate URL: www.msgc.org
- Estimated Number of Employees: 2
- Estimated Annual Receipts: $400,000
- Business Start Date: 2000
- Contact Person: Terry Shehata
- Contact Phone: 207-622-4688
- Contact Email: terry.shehata@msgc.org
- Business Structure:
- Corporate Entity (Tax Exempt)
- Business Type:
- Non-Profit Organization
- Industries Served: Grantmaking Foundations
- Product Areas: AIRCRAFT HYDRAULIC, VACUUM, AND DE-ICING SYSTEM COMPONENTS, AIRCRAFT HYDRAULIC VACUUM DE-ICING, MISC SHIP & MARINE EQ, MISCELLANEOUS SHIP AND MARINE EQUIPMENT, DIESEL ENGINES AND COMPONENTS, MISCELLANEOUS POWER TRANSMISSION EQUIPMENT, MISC POWER TRANSMISSION EQ, CUTTING TOOLS FOR MACHINE TOOLS, POWER AND HAND PUMPS, PIPE, TUBE AND RIGID TUBING, HOSE AND FLEXIBLE TUBING, FITTINGS - HOSE PIPE & TUBE, HOSE, PIPE, TUBE, LUBRICATION, AND RAILING FITTINGS, VALVES, NONPOWERED, BOLTS, RELAYS AND SOLENOIDS, ELECT ELECTRONIC MEASURING INSTRUMT, ELECTRICAL AND ELECTRONIC PROPERTIES MEASURING AND TESTING INSTRUMENTS
Sampling of Federal Government Funding Actions/Set Asides
In order by amount of set aside monies.
- $249,684 - Monday the 20th of April 2015
National Aeronautics And Space Administration
NASA SHARED SERVICES CENTER
THE SUCCESS OF NEXT GENERATION LAUNCH VEHICLES WITH IMPROVED RELIABILITY AND OPERABILITY DEPENDS IN PART ON THE DEVELOPMENT OF ADVANCED CONTROL SYSTEMS [1]. AN IMPORTANT OBJECTIVE OF LAUNCH VEHICLE CONTROL INVOLVES THE MITIGATION OF UNWANTED OSCILLATION ABOUT THE THREE ROTATIONAL AXES: ROLL, PITCH AND YAW. THE PITCHING AND YAWING DYNAMICS OF THE VEHICLE ARE SIGNIFICANTLY DEGRADED BY THE ELASTICITY OF THE STRUCTURE [2] WHICH MANIFESTS ITSELF AS LATERAL VIBRATIONS OF THE STRUCTURE. WHILE OPTIMAL DESIGN OF THE LAUNCH VEHICLE MAY REDUCE SOME OF THESE EFFECTS, ACTIVE CONTROL SYSTEMS ARE REQUIRED. THE PERFORMANCE OF THE CONTROL SYSTEM, HOWEVER, RELIES ON ACCURATE KNOWLEDGE OF THE VIBRATION CHARACTERISTICS. MODELING THE VIBRATION CHARACTERISTICS FROM FIRST PRINCIPLES IS THE INITIAL DESIGN STEP, FOLLOWED UP WITH EXTENSIVE STRUCTURAL TESTING [3]. ULTIMATELY, EVEN WITH STRUCTURAL TESTING, IT IS VERY DIFFICULT TO DETENNINE WHICH OF THE VIBRATION MODES WILL GET EXCITED DURING A PARTICULAR PHASE OF THE FLIGHT. WHILE MODEM LAUNCH VEHICLE CONTROLLERS RELY ON A PRIORI KNOWLEDGE OF THESE MODES, THE BEST SOLUTION IS TO DETENNINE THE VIBRATION CHARACTERISTICS IN REAL TIME, AND CANCEL ITS EFFECTS IN A FEEDBACK CONTROL ALGORITHM (FIGURE-LA). THIS NEW APPROACH REQUIRES MANY SENSORS WHICH HAVE TO BE NETWORKED WIRELESSLY, AS IT BECOMES RAPIDLY IMPRACTICAL TO HAVE ALL OF THEM "WIRED" TO ETHER.
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