PASSIVE AERODYNAMIC ATTITUDE STABILIZATION OF NEAR EARTH SATELLITES. VOLUME 2. AERODYNAMIC ANALYSIS
Abstract
Aerodynamic drag and stability coefficients of several simple satellite configurations are calculated using nearly exact, free molecule theory. The models are the cylinder, sphere, pointed cone, truncated cone, power law body, hemisphere-cylinder and cone-cylinder. For maximum aerodynamic effects, favorable center-of mass locations are obtained by concentrating a homogeneous payload forward of the center-of volume. Aft portion of the models were assumed to be rigid, but massless, shells or skirts. Based upon the analysis of satellite angular motion, aerodynamic pitching moment slope is combined with the pitching moment of inertia to form a stability parameter which, when maximized, describes the optimum external geometry of each model for a specified payload mass distribution. The optimum configurations are shown to have low fineness ratios (order of unity), permitting the gravitational torque to augment the aerodynamic torque. Pointed and truncated conical bodies and the power law bodies were the most stable.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0267522
Entities
People
- Paul H. Davison