Wavelength-Agile Optical Rocket Propulsion Sensor (WORPS)

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NAS13-03019
Agency Tracking Number: 020068
Amount: $100,000.00
Phase: Phase I
Program: STTR
Awards Year: 2003
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, 53717
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Martin J. Chiaverini
 () -
Business Contact
 Eric Rice
Title: President & CEO
Phone: (608) 827-5000
Email: koffarnusl@orbitec.com
Research Institution
 University of Wisconsin - Madison
 Scott Sanders
 1415 Engineering Drive
Madison, WI, 53706
 (608) 263-4980
 Nonprofit college or university
ORBITEC and the University of Wisconsin-Madison propose to develop a low-cost, non-intrusive, wavelength-agile optical rocket propulsion sensor (WORPS) to interrogate rocket exhaust plumes and cryogenic fluid properties. The innovative sensor system is based on a Chirped White Pulse Emitter (CWPE). By rapidly monitoring (1 ?Ys response time) broad absorption spectra, the CWPE can interrogate temperature, pressure, and multiple species concentrations in gases at arbitrary conditions and can simultaneously monitor cryogenic liquid properties, all with a simple design. Along a line-of-sight with non-uniform properties, the CWPE can also record gas temperature distributions rather than just the path-averaged temperature. These capabilities represent a dramatic enhancement of the best diode-laser sensors available just two years ago, which were not wavelength-agile. In Phase I, a prototype WORPS system will be designed and fabricated. The unit will be initially demonstrated by interrogating static gas cells at various mixtures and pressures, flat-flame burners, and dewars of LOX containing known amounts of trace constituents (such and N2). Additional demonstrations will be performed by measuring species concentrations and temperature in exhaust plumes from the combustion of GOX/GH2, GOX/RP-1, and GOX/HTPB in lab-scale thrust chambers operating over a range of pressures and nozzle area ratios.

* Information listed above is at the time of submission. *

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