O2/H2 Advanced Maneuvering Propulsion Technology Program Engine System Studies. Volume I. Aerospike Engine Configuration Design and Analysis
Abstract
The engine system design and analysis studies provide a detailed definition of two 25,000-pound-thrust O2/H2 aerospike engines. The single-panel aerospike engine design point corresponds to the demonstrator thrust chamber configuration, specifically, chamber pressure and area ratio equal to 750 psia and 110:1, respectively. A second engine system and component design and operational description also is provided for the selected optimum aerospike engine employing a double-panel thrust chamber cooling circuit. The double-panel aerospike engine design has a chamber pressure and area ratio of 1000 psia and 200:1, respectively. These engine systems are designed to provide 5:1 throttling and off-design mixture ratio operation. The study effort also included the effects of variations in certain design parameters on engine performance, weight, propellant flow balances, life capability, development time and cost, and maintenance requirements. Additional parametric information is provided for design thrust levels between 8000 and 50,000 pounds.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1971
- Accession Number
- AD0890753