Hybrid propulsion based on fluid-controlled solid gas generatorsThe use of fuel-rich solid (gas generator-type) propellants for hybrid propulsion affords some design and utilization efficiency advantages. Both forward and aft liquid injection control concepts are evaluated from the operational standpoints of ballistics, throttling, stability and extinguishment. Steady-state and non-steady ballistics analyses are employed for this evaluation. Stability of solid motor operation is enhanced by fluid injection with adequate injector pressure drop. Efficient throttling and reliable extinguishment are attained through a combination of solid propellant combustion tailoring, grain design, control valves and sensors. Initial results from a laboratory-scale slab combustor, combining a gas generator propellant with gaseous oxygen injection, are also presented.
Document ID
19930066275
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cohen, Norman S. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Strand, Leon D. (JPL Pasadena, CA, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2550
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit