Review of Hydrazine Monopropellant Development
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Report Number: AFOSR 69-2951TR p. 148-190
Author(s): Marcus, Milton
Corporate Author(s): Hamilton Standard, Division of United Aircraft Corporation
Date of Publication: 1969-12
DoD Task:
Identifier: This paper is part of a conference proceedings. See AD0703442
Abstract:
The use of hydrazine monopropellant rocket engines has been firmly established as an efficient and reliable approach to the attitude control of a large variety of satellites, missiles, and other spacecraft. This technology has been undergoing intensive development since the advent of a spontaneous decomposition catalyst, Shell 405, about five years ago. The first successful space flight application was recently demonstrated (Nov. 1967) on the NASA Applications Technology Satellite, ATS-3. Hamilton Standard furnished hydrazine monopropellant rocket engine assemblies for the ATS-3 to the prime contractor, Hughes Aircraft Company. Many other current spacecraft programs, sponsored by the military services, NASA, and Comsat Corporation, also are committed to using this technology for attitude control. At this point, it is important for potential users to understand the advantages, performance capabilities, and limitations of this system. In this paper the applications are discussed and the advantages outlined. The performance potential of these engines is then presented, including a detailed discussion of the development of reaction chamber technology. The propellant and catalyst are discussed in detail with emphasis on advanced research in these areas. The paper concludes with statement of the future potential in this technology in spacecraft propulsion systems.
Author(s): Marcus, Milton
Corporate Author(s): Hamilton Standard, Division of United Aircraft Corporation
Date of Publication: 1969-12
DoD Task:
Identifier: This paper is part of a conference proceedings. See AD0703442
Abstract:
The use of hydrazine monopropellant rocket engines has been firmly established as an efficient and reliable approach to the attitude control of a large variety of satellites, missiles, and other spacecraft. This technology has been undergoing intensive development since the advent of a spontaneous decomposition catalyst, Shell 405, about five years ago. The first successful space flight application was recently demonstrated (Nov. 1967) on the NASA Applications Technology Satellite, ATS-3. Hamilton Standard furnished hydrazine monopropellant rocket engine assemblies for the ATS-3 to the prime contractor, Hughes Aircraft Company. Many other current spacecraft programs, sponsored by the military services, NASA, and Comsat Corporation, also are committed to using this technology for attitude control. At this point, it is important for potential users to understand the advantages, performance capabilities, and limitations of this system. In this paper the applications are discussed and the advantages outlined. The performance potential of these engines is then presented, including a detailed discussion of the development of reaction chamber technology. The propellant and catalyst are discussed in detail with emphasis on advanced research in these areas. The paper concludes with statement of the future potential in this technology in spacecraft propulsion systems.