Use of an Aerodynamic Turn to Maximize the Orbit Inclination Change for the Space Shuttle Orbiter.
Abstract
Previous studies have shown that the Space Shuttle Orbiter can achieve larger orbit inclination changes using an aerodynamic turn than can be obtained using a rocket motor burn. This analysis determines the angle of attack and bank angle histories which maximize the change in inclination angle while satisfying final altitude and velocity loss constraints. The angle of attack and bank angle are modelled as polynomial functions of time with unknown coefficients. The optimum values of the coefficients are determined by a gradient optimization technique. Additionally, the sensitivity of the change in inclination angle to changes in the orbit apogee altitude is examined. It is shown that the Space Shuttle Orbiter can obtain higher inclination angle changes with higher apogee altitudes. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1979
- Accession Number
- ADA079855
Entities
People
- Glenn S. Geary
Organizations
- Air Force Institute of Technology