The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed. Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of launching to space payloads of 800 KG or more. A hybrid launcher in which EML is used for the first 2 KM/sec followed by chemical rocket stages was also tested. A cost estimates study shows that one to two EML launches per day are needed to break even, compared to a four-stage rocket. Development models are discussed for: (1) Earth orbital missions; (2) lunar base supply mission; (3) solar system escape mission; (4) Earth escape missions; (5) suborbital missions; (6) electromagnetic boost missions; and (7) space-based missions. Safety factors, environmental impacts, and EML systems analysis are discussed. Alternate systems examined include electrothermal thrustors, an EML rocket gun; an EML theta gun, and Soviet electromagnetic accelerators.
Preliminary Analysis of Space Mission Applications for Electromagnetic Launchers
1984
338 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Electromagnetic propulsion , Hypervelocity launchers , Railgun accelerators , Space missions , Systems analysis , Technology assessment , Cost estimates , Environment effects , Hazardous material disposal (In space) , Lunar bases , Safety factors , Space stations
Electromagnetic launchers for space applications
Tema Archiv | 1989
|Tema Archiv | 1989
|