Solar Rocket Component Study
Abstract
A program was conducted to identify the most promising solar-thermal rocket thruster concept and to design, fabricate, and deliver to the Air Force Rocket Propulsion Laboratory, a demonstrator absorber/thruster based on the selected concept for subsequent ground test evaluation. A concept assessment, in which windowless and windowed designs involving both direct and indirect propellant heating, resulted in the selection of the windowless heat exchanger cavity configuration. The selection considered the criteria of achievable specific impulse, thrust achievable, durability, complexity, technical risk, and relative cost. Based on the concept selected, a ground test demonstration absorber/thruster was designed. Supporting detailed thermal, stress, and performance analyses were conducted together with evaluations of critical materials and fabrication processes. the projected performance of the demonstrator absorber/thruster was a specific impulse of 7930 N sec/kg (807 lbf sec/lbm), with a thrust of 3.69 N (0.83 lbf). Fabrication and assembly were completed and the thruster satisfactorily leak-checked. The absorber coil was fabricated from rhenium by the same process. Radiation shielding and insulation minimized heat losses. Keywords include: Solar Thermal Propulsion, Solar Absorber, Thruster performance, Absorber/Thruster Design, Rhenium fabrication, Hydrogen Performance, Solar Window, Window Heat Transfer, Absorber/Thruster, and Heat Transfer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1985
- Accession Number
- ADA154186
Entities
People
- J. M. Shoji