Accession Number:

ADA243733

Title:

Orbital Transfer Vehicle Engine Technology

Descriptive Note:

Contractor rept.

Corporate Author:

AEROJET PROPULSION DIV SACRAMENTO CA

Personal Author(s):

Report Date:

1991-11-01

Pagination or Media Count:

234.0

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 H2O2 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 injectorchamber compatibility.

Subject Categories:

  • Metallurgy and Metallography
  • Manufacturing and Industrial Engineering and Control of Production Systems
  • Rocket Engines
  • Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE