Tsuki Nanchakuriku Kidou Sekkei (Lunar Soft Landing Orbit Design)
Tsuki Nanchakuriku Kidou Sekkei (Lunar Soft Landing Orbit Design)
- Neue Suche nach: K. Nakajima
- Neue Suche nach: K. Nagano
- Neue Suche nach: K. Nakajima
- Neue Suche nach: K. Nagano
The following subjects necessary for lunar soft landing orbit design are reviewed: (1) methods to solve minimum fuel consumption problems; (2) lunar soft landing orbit design based on the results of the fuel consumption problems; and (3) future problems. The answer to the minimum fuel consumption by Pontryagin's maximum principle are presented. Lunar soft landing orbit design using a spherical model are presented for four assumed cases. Powered descending time-altitude profile, transient angle-altitude profile, powered descending time-vertical speed profile, powered descending time-control angle profile, and powered descending time-speed profile in down-range direction are showed. The following has become clear: (1) when powered descent begins from an elliptical orbit, starting from the perigee point is advantageous if the speed increase necessary for landing is employed as the criteria; and (2) constant thrust acceleration level exists to minimize necessary speed increase.
Dokumentinformationen
Tsuki Nanchakuriku Kidou Sekkei (Lunar Soft Landing Orbit Design)
1991
21 pages
Report
Keine Angabe
Englisch
Extraterrestrial Exploration , Spacecraft Trajectories & Flight Mechanics , Flight optimization , Lunar landing , Orbit calculation , Soft landing , Orbital mechanics , Descent trajectories , Equations of motion , Interplanetary trajectories , Landing simulation , Lunar exploration , Lunar landing modules , Lunar orbits , Lunar probes , Pontryagin principle , Foreign technology