OPTIMUM SATELLITE LAUNCHER TRAJECTORY GUIDED WITH PROPORTIONAL NAVIGATION PLUS GRAVITY COMPENSATION GUIDANCE
The optimum trajectory of a single or multi-stage satellite launcher guided with proportional navigation guidance (PNG) is addressed. The PNG is extended to compensate for the gravity effect. For the trajectory optimization problem, the launcher is modeled as a mass point flying around the center o...
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| Formato: | Artigo |
| Idioma: | English |
| Publicado em: |
University of Baghdad
2006-12-01
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| coleção: | Journal of Engineering |
| Acesso em linha: | https://www.joe.uobaghdad.edu.iq/index.php/main/article/view/2839 |