Rendezvous Display and Control Simulation

Display and control techniques associated with the rendezvous of a spacecraft launched into an earth orbit in or about the same plane of a previously orbited target vehicle were investigated. In order to acquire representative data and conditions, an analog computer providing for real time studies in six degrees of freedom, and a simulated spacecraft cockpit with displays and controls were mechanized. Target range and bearing information was programmed by the computer while the operator in the cockpit made the necessary changes in orbital velocity to accomplish near docking. The space vehicle´s motion and rates were presented in a variety of display configurations to allow evaluation of the operator´s ability to successfully reduce the range and rate of closure parameters with minimum fuel consumption. Included in the experimental display configurations were indicators with linear and quasi-logarithmic scales, edge reading and computed program meters and integrated oscilloscope presentations using quickened techniques. Motion and control equations, as well as the system block diagram of the simulation are shown in this paper. The data obtained during the simulation can serve to illustrate the relative workability of selected groups of displays and controls and demonstrates that an operator can control the rendezvous maneuvers using such preferred groups of displays.