Trough Region Plume Signatures (TRPS)

Award Information
Agency:
Department of Defense
Branch
Missile Defense Agency
Amount:
$99,995.00
Award Year:
2005
Program:
SBIR
Phase:
Phase I
Contract:
W9113M-05-C-0072
Award Id:
74715
Agency Tracking Number:
044-0950
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
655 Deep Valley Drive, Suite 335, Rolling Hills Estate, CA, 90274
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
625432679
Principal Investigator:
Blaine Pearce
Principal Scientist
(310) 541-1933
bep@aero-optics.com
Business Contact:
G. Freeman
President
(310) 541-1933
gnf@aero-optics.com
Research Institution:
n/a
Abstract
The altitude region 40-70 km (signature trough region) is a segment of missile trajectories in which MDA signature simulation capability is least reliable. Important phenomena include afterburning cessation, turbulent-laminar transition, reduced mixing and onset of collision enhancement. Aero Optics, Inc. (AOI) and Calspan-University at Buffalo Research Center (CUBRC) propose the Trough Region Plume Signatures (TRPS) measurements-simulation program to collect and exploit highly resolved missile plume flow and radiation measurements in this altitude region. The unique capability of CUBRC's Large Energy National Shock Tunnel (LENS) is proposed for the measurements. LENS provides the altitude-velocity environment that matches missile trajectories along with demonstrated capability to measure gas dynamic and radiative properties of rocket plumes in shock tunnel test environments. Proposed measurements include mean and fluctuating flow and radiance properties, and particulate trajectories for liquid and solid propellants. Computations of the test flow field and radiation will be made with standard and newly developed flow/radiation simulation tools. The overall objective is a collection of gas dynamic and radiative measurements under well-defined conditions that support improved modeling and simulation. Phase I is test planning involving shock tunnel conditions, instrumentation, rocket motor design, demonstration of facilities and measurements, and supporting simulations. Phase II is implementation of the plan, data collection and archiving, analysis and exploitation of the data for improved simulations.

* information listed above is at the time of submission.

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