Orbital Transfer Vehicle Engine Technology
Abstract
New technologies for space-based, reusable, throttleable, cryogenic orbit transfer propulsion are being evaluated. The supporting tasks for the design of a dual-expander cycle engine thrust chamber design are documented in this report. This supports plans for development of a new Orbit Transfer Vehicle (OTV) to be operational in the late 1990s. Critical to the economical operation of a space based OTV is a new H2/O2 rocket engine with capabilities superior to available engines. Available engine characteristics and those required of a new engine are summarized. In total, these requirements represent a substantial advance in the state-of-the-art technologies and a considerable challenge to rocket engine designers. OTV engine studies have identified a dual-propellant expander cycle as offering advantages over either staged combustion or gas generator cycles. The purpose of the studies documented in this report was to research the materials used in the thrust chamber design, the supporting fabrication methods necessary to complete the design, and the modification of the injector element for optimum injector/chamber compatibility.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1991
- Accession Number
- ADA243733
Entities
People
- J. A. Schneider
Organizations
- Aerojet Rocketdyne Holdings