A summary of the constraints and requirements on the Earth Observatory Satellite (EOS-A) orbit and launch vehicle analysis is presented. The propulsion system (hydrazine) and the launch vehicle (Delta 2910) selected for EOS-A are examined. The rationale for the selection of the recommended orbital altitude of 418 nautical miles is explained. The original analysis was based on the EOS-A mission with the Thematic Mapper and the High Resolution Pointable Imager. The impact of the revised mission model is analyzed to show how the new mission model affects the previously defined propulsion system, launch vehicle, and orbit. A table is provided to show all aspects of the EOS multiple mission concepts. The subjects considered include the following: (1) mission orbit analysis, (2) spacecraft parametric performance analysis, (3) launch system performance analysis, and (4) orbits/launch vehicle selection. (Author)
Earth Observatory Satellite System Definition Study. Report 1: Orbit/Launch Vehicle Trade-off Studies and Recommendations
1974
107 pages
Report
No indication
English
Unmanned Spacecraft , Earth orbits , Earth resources technology satellite e , Earth resources technology satellite f , Orbital mechanics , Satellite design , Satellite instruments , Spacecraft launching , Land use , Launch vehicles , Management planning , Mission planning , Remote sensors , Resources management , Space missions , Systems analysis