A method is described by which the fuel consumption neccessary for space vehicle transfer from hyperbolic trajectories to satellite orbits can be reduced by utilization of aerodynamic drag. The space vehicle is guided into a trajectory (conic pericenter radius) which enables it to drag to the desired transfer velocity. Permissible conic periapsis radius values of possible approach trajectories as a function of the spacecraft he/D ratio and guidance method are determined. It is shown that optimal guidance widens the radius range. (Author)
On Required Guidance for Transfer from Hyperbolic Trajectory to the Planetary Satellite Orbit by Aerodynamic Drag in Atmosphere
1972
16 pages
Report
No indication
English