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A Hot Gas Servocontrol System for Aerospace Applications
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1965 by SAE International in United States
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This paper presents a new concept for a solid propellant powered, hot gas, high performance servocontrol system for aerospace applications along with a discussion of the program presently being accomplished to develop and demonstrate this system. The system discussed is designed to provide operational flight controls for a two stage, air launched missile with goals of improved reliability, weight reduction, and increased range as a result of weight reduction. Two separate systems are discussed with the first stage system providing control of aerodynamic surfaces and the second stage gimbaling the propulsion nozzle and also including reaction nozzle roll control. Both systems are supplied from solid propellant gas generators providing a supply gas at 1950°F. This program has led to the conclusion that high temperature pneumatic controls will satisfactorily provide the necessary power and response to fly a missile requiring high accuracy and to accomplish this in a severe environment with a reduction in system weight and complexity. The results of performance testing and environmental testing of the system and components are presented to demonstrate the suitability of the system for aerospace applications
CitationRivard, J., Ochs, P., and Wallick, D., "A Hot Gas Servocontrol System for Aerospace Applications," SAE Technical Paper 650350, 1965, https://doi.org/10.4271/650350.
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