Ascent and Descent Trajectory Optimization of Ariane 5/Hermes
Ascent and Descent Trajectory Optimization of Ariane 5/Hermes
- Neue Suche nach: C. Jaensch
- Neue Suche nach: K. Schnepper
- Neue Suche nach: K. H. Well
- Neue Suche nach: C. Jaensch
- Neue Suche nach: K. Schnepper
- Neue Suche nach: K. H. Well
An overview over the state-of-the-art of trajectory optimization of aerospace vehicles is given with emphasis on applications to Ariane 5 ascent trajectories and Hermes reentry trajectories. Some of the numerical methods used in the past are briefly reviewed. Two relatively new methods under development, both of which need efficient sequential quadratic programming for solving the associated nonlinear programming problems are described in more detail. A detailed description of the equations of motion, the boundary conditions and the flight path constraints for the Ariane 5 ascent and the Hermes reentry is presented and numerical results are given for an optimal ascent into geostationary transfer orbit, into a sun-synchronous orbit, into a 28.5 degree transfer orbit for the Ariane 5/Hermes combination, and an optimal reentry from a 28.5 degree orbit to Istres. Trajectory optimization of space vehicles with airbreathing engines is considered.
Dokumentinformationen
Ascent and Descent Trajectory Optimization of Ariane 5/Hermes
1990
27 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Ariane launch vehicle , Ascent trajectories , Descent trajectories , Flight paths , Hermes manned spaceplane , Trajectory optimization , Nonlinear programming , Quadratic programming , Boundary conditions , Equations of motion , Geosynchronous orbits , Numerical analysis , Reentry trajectories , Transfer orbits , Foreign technology
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