DEVELOPMENT OF LOW PRESSURE LIGHT WEIGHT ROCKET SYSTEM COMPONENTS.
Abstract
New concepts were investigated for integration of components for low pressure liquid propellant rocket engines. Combining the functions of many components in complete subsystems, and use of new design concepts in the subsystems greatly reduced the number of parts required to perform subsystem functions. System integration and simplification ultimately lead to improved reliability and weight reduction. Two integrated subsystems were investigated: a system for propellant tank pressurization, and a system for propellant flow control. The pressurization system included all the functions normally provided by fill and drain valves, solenoid operated shut-off valve, pressure regulator, check-valves and relief valves. The propellant system included all the functions normally provided by fill and drain valves, check valves, shut-off valves, and propellant mixture ratio control device. The pressurization system weighed 0.31 lbs. and utilized the flow force concept in both the regulator and check valves. This concept is based on application of the forces generated on valve elements by the change in momentum of the working fluid. The propellant system weighed 0.43 lbs. and used a mechanical ratio control device for flow ratio control at any flow rate or pressure. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1963
- Accession Number
- AD0432593
Entities
People
- Hans F. Eckardt