NASA Dryden Flight Research Center has developed a flush airdata sensing (FADS) system on a sharp-nosed, wedge-shaped vehicle. This paper details the design and calibration of a real-time angle-of-attack estimation scheme developed to meet the onboard airdata measurement requirements for a research vehicle equipped with a supersonic-combustion ramjet engine. The FADS system has been designed to perform in flights at Mach 3-8 and at -6 deg - 12 deg angle of attack. The description of the FADS architecture includes port layout, pneumatic design, and hardware integration. Predictive models of static and dynamic performance are compared with wind-tunnel results across the Mach and angle-of-attack range. Results indicate that static angle-of-attack accuracy and pneumatic lag can be adequately characterized and incorporated into a real-time algorithm.
Development of a Flush Airdata Sensing System on a Sharp-Nosed Vehicle for Flight at Mach 3 to 8
2000
18 pages
Report
Keine Angabe
Englisch
Avionics , Air data systems , Wind tunnel tests , Wind tunnel models , Supersonic wind tunnels , Detection , Remote sensing , Indicating instruments , Real time operation , Angle of attack , Dynamic pressure , Algorithms , Mach number , Supersonic speed , Hypersonic speed , Supersonic combustion ramjet engines
Development of a Flush Airdata Sensing System on a Sharp-Nosed Vehicle for Flight at Mach 3 to 8
British Library Conference Proceedings | 2000
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