SPHERES Mars Orbiting Sample Return External Orbiting Capture

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX11CF58P
Agency Tracking Number: 104350
Amount: $99,974.00
Phase: Phase I
Program: SBIR
Awards Year: 2011
Solitcitation Year: 2010
Solitcitation Topic Code: S5.04
Solitcitation Number: N/A
Small Business Information
Aurora Flight Sciences Corporation
MA, Cambridge, MA, 02142-1189
Duns: 604717165
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 James Francis
 Principal Investigator
 (617) 500-0276
Business Contact
 Scott Hart
Title: Financial Analyst
Phone: (617) 500-0536
Email: shart@aurora.aero
Research Institution
NASA's Mars Sample Return (MSR) mission scenario utilizes a small Orbiting Sample (OS) satellite, launched from the surface of Mars, which will rendezvous with an Orbiter/Earth Return Vehicle (ERV). When the radio beacon-equipped OS is within range of the ERV's optical sensors, the ERV will optically track and approach the OS, maneuvering itself to place the OS within its capture device.One of the key technologies required to accomplish this mission involves a low-mass, highly reliable mechanism that detects contact with and captures the OS, and, once the OS is captured, moves the OS to a containment area for the return trip to Earth. There is an on-going body of research into such capture mechanism designs and the various advantages and challenges of these technologies. Aurora Flight Sciences and its research partner, the Massachusetts Institute of Technology (MIT) Space Systems Laboratory (SSL), propose to develop a flight-quality OS-detection and capture mechanism design based on research data and experience with the Mars Orbiting Sample Retrieval test bed and develop a risk-mitigation strategy that utilizes the International Space Station as a system checkout and launch platform for system testing in Low Earth Orbit (LEO). This proposal leverages the state-of-the-art research into sample capture mechanisms, contact dynamics and capture mechanism detection methods and builds on the team's experience with the Synchronized Position, Hold, Engage, and Reorient Experimental Satellites (SPHERES) system to develop a low cost, LEO test strategy that minimizes the risk for later Mars deployment.

* information listed above is at the time of submission.

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