The primary purpose of the rocket plume diagnostic program is to investigate the high-altitude near-field radiance signature of rocket motors, and to develop the diagnostic techniques required to characterize various types of rocket plumes. The design, calibration, and installation of a cold-optics LWIR detecting system on one of the Calspan high-altitude test chambers is discussed. Particulate flux measurement techniques are discussed, and the design and development of research rocket motors for use with specific propellant combinations is presented. A test program for small liquid and solid thrusters, such as those proposed for the FAIR II PIE flight program, has been initiated, and experimental data for a monopropellant hydrazine thruster are presented and compared with IR radiance predictions.
Plume Interference Assessment and Mitigation
1973
66 pages
Report
Keine Angabe
Englisch
Infrared & Ultraviolet Detection , Rocket Engines & Motors , Rocket Propellants , Exhaust gases , Combustion products , Infrared radiation , Rocket engines , High altitude , Simulation , Altitude chambers , Liquid propellant rocket engines , Solid propellant rocket engines , Infrared detectors , Detectors , Compatibility , Signal-to-noise ratio , Particles , Collecting methods , Monopropellants , Bipropellants , Performance(Engineering) , Rocket nozzles , Butadienes , Hydrazine , Hydrazine derivatives , Nitrogen oxides , Halogenated hydrocarbons , Halogen compounds , Spectrometers , Aluminum , Ammonium perchlorate , Booster rockets , Attitude control systems , Plumes(Radiation) , Carboxy terminated polymers , Ctpb propellant ingredient , Fair program , Fly along infrared , Htpb propellant ingredient , Hydroxy terminated polymers , Long wavelengths , Polybutadiene/carboxy terminated , Polybutadiene/hydroxy terminated , Short waveleng
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