Design and testing of the U.S. Space Station Freedom primary propulsion systemThe primary propulsion system (PPS) for the Space Station Freedom is discussed in terms of salient design characteristics and key testing procedures. The rocket engine modules contain reboost and attitude control thrusters, and their designs are illustrated showing the mounting structures, thruster solenoid valves, and thrust chambers. The propellant tank assembly for storing gaseous N pressurant and hydrazine propellant is described as are the system avionics, thruster solenoid valves, and latching isolation valves. PPS testing conducted on the development systems includes the use of a propulsion-module development unit, a development test article, and system qualification testing. Specific test articles include functional heaters, mass/thermal simulated components, flight-quality structures, and software control operations.
Document ID
19920071474
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Morano, Joseph S. (McDonnell Douglas Space Systems Co., Space Station Div., Huntington Beach CA, United States)
Delventhal, Rex A. (NASA Johnson Space Center Houston, TX, United States)
Chilcot, Kimberly J. (McDonnell Douglas Space Systems Co., Space Station Div., Huntington Beach CA, United States)