Compound A/Hydrazine Engine Design Study. Part 1
Abstract
The results of the Compound A/Hydrazine Engine Design Study, including the parametric engine information needed to perform mission analyses for evaluation of advanced engine design concepts, are reported in two parts. Part 1 includes parametric engine performance, weight, envelope, and capability for numerous engine concepts utilizing various fuels and different technologies for the feed system, propellant injection, and chamber cooling systems. These concepts encompass passive and active cooling methods, liquid and gaseous propellant injection, and pressure-fed as well as pump-fed systems of both the bleed cycle and the staged-combustion cycle. The applicability as well as comprehensiveness of the data is demonstrated by its use in three different missions specified by the Air Force. These include a synchronous orbit, trailer propulsion, and integrated propulsion for a re-entry vehicle. Payload or ideal velocity increment differences for various engine design concepts are shown. However, in view of the preliminary design concept approach as well as a lack of detailed engine design specifications, a number of basic assumptions were made in evolving the data within the scope of this program. Therefore, a description is provided for modifying the parametric data needed in a mission analysis to make it consistent with a different set of assumptions should new information subsequently become available.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 30, 1968
- Accession Number
- AD0390230
Entities
People
- Christopher S. Henry
- Clayton W. Williams
- Clifford Paavola
- R. V. Coats
- Werner P. Luscher
Organizations
- Aerojet Rocketdyne Holdings