Small Business Innovation Research/Small Business Tech Transfer
Hypersonic Free-Flight Measurement of Aeroshell Forces and Flowfields, Phase I
Project Description
A Hypersonic Gun Tunnel and laser based high speed imaging systems will be used to generate a unique, free flight, aerodynamic data base of potential Mars aeroshell configurations. These experiments will provide reliable bench mark data for CFD code validation and help aerocapture modeling and optimize aeroshell payload and design. The experiments will be conducted at hypersonic Mach numbers in air and in simulated Martian atmospheric test gases and will cover the hypersonic continuum flow regime. The innovative test results will help improve aerocapture analysis and prediction techniques that will lead to reduced deceleration propellant launch weight, increased payload, and improved delivery accuracy. These improved measurement capabilities will greatly enhance U.S. commercial and military competitiveness in aerospace vehicle design and production, and help regain and stimulate a viable customer-testing base, which will help preserve and improve our national wind tunnel testing infrastructure. These new capabilities will provide significant test data improvements, which will greatly enhance our ability to understand the physical flow phenomena associated complex flows over advanced aerospace vehicles.
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Anticipated Benefits
Potential NASA Commercial Applications: During the twenty-first century, industries will thrive in orbit and in space colonies, with research laboratories and manufacturing plants taking advantage of the microgravity environment and new sources of raw materials. If U.S. companies do not lead these activities, others will, putting the U.S. at a commercially competitive disadvantage. To encourage private investment, we must reduce payload and mission costs. Improved aerocapture technology will help achieve this. To maintain a commercial edge, we must improve aerocapture technology for orbit insertion since it provides significant economic advantages over conventional chemical propulsion methods by reducing vehicle mass and mission pay load cost. The improved experimental techniques developed with SBIR support will contribute to cost-effective aeroshell design techniques for aerocapture entry vehicles.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Langley Research Center
(LaRC)
|
Lead Organization | NASA Center | Hampton, Virginia |
| Complere, Inc. | Supporting Organization |
Industry
Small Disadvantaged Business (SDB)
|
Pacific Grove, California |
Primary U.S. Work Locations
-
California
-
Virginia
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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.