| Description |
vi, 83 leaves : illustrations ; 29 cm |
| Summary |
"Collision and pursuit course closure maneuvers were studied for correcting position and velocity errors in the terminal phase of spacecraft to satellite rendezvous. Minimum values of the ratio of initial range to velocity necessary to achieve rendezvous were determined for collision closures as a function of the initial line of sight. The time and velocity increment required for rendezvous were computed as a function of initial conditions. Pursuit closure maneuvers were analyzed and time and velocity increments defined as a function of initial range, closing velocity, line of sight angle and angular velocity. The velocity increments required were significantly higher than for a collision closure under similar initial conditions. In addition, the pursuit closure was shown to require very precise control of the initial angular velocity in order to achieve rendezvous. The collision closure maneuver was recommended because the pursuit closure required a greater velocity increment and precise control of the initial angular velocity. An example was presented to illustrate the analysis of a collision closure maneuver i n a rendezvous mission"--Abstract, leaf ii. |
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