Integrated Powerhead Demonstration: Full Flow Cycle Development
Abstract
The Integrated Powerhead Demonstration (IPD) is a 1,112,000 N (250,000 Ib(sub f)) thrust (at sea level) LOX/LH2 demonstration of a full flow cycle in an integrated system configuration. Aerojet and Rocketdyne are on contract to the Air Force Research Laboratory to design, develop, and deliver the required components, and to provide test support to accomplish the demonstration. Rocketdyne is on contract to provide a fuel and oxygen turbopump, a gas-gas injector, and system engineering and integration. Aerojet is on contract to provide a fuel and oxygen preburner, a main combustion chamber, and a nozzle. The IPD components are being designed with Military Spaceplane (MSP) performance and operability requirements in mind. These requirements include: lifetime >/- 200 missions, mean time between overhauls >/- 100 cycles, and a capability to throttle from 20% to 100% of full power. These requirements bring new challenges both in designing and testing the components. This paper will provide some insight into these issues. Lessons learned from operating and supporting the space shuttle main engine (SSME) have been reviewed and incorporated where applicable. The IPD program will demonstrate phase I goals of the Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program while demonstrating key propulsion technologies that will be available for MSP concepts. The demonstration will take place on Test Stand 2A at the Air Force Research Laboratory at Edwards AFB. The component tests will begin in 1999 and the integrated system tests will be completed in 2002.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 05, 1997
- Accession Number
- ADA397910
Entities
People
- Jason Jones
- William A. Hayes
- William D. Boyce
- William F. Sack
Organizations
- Boeing Defense, Space & Security