USAF Cost Optimized Booster System Studies
Abstract
This report involves the investigation, analysis, and cost optimization of conventional two-stage tandem booster systems which utilized state-of-the-art advanced concept propulsion systems in the 0.6 to 3 million pound thrust range. Numerous configurations utilizing various combinations of engine types, thrust ratings, and propellants were considered and optimized for both performance and costs. The most promising configurations in the 600 K and 1500 K thrust classes for both state-of-the-art and advanced propulsion systems were adopted for investigation of 800 K and 3000 K thrust booster systems. Various alternate booster system concepts were also investigated and evaluated on a cost comparison basis with the selected two-stage booster system configurations incorporating advanced high chamber pressure engines. The basis for evaluation and comparison of the various configurations and concepts was dollar cost per pound of payload in a 300-nautical-mile orbit. In order to determine economic trends influenced by varying launch rates, costing was based on a 10-year launch program consisting of 10, 100, and 1,000 total launches.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 22, 1961
- Accession Number
- ADA551616