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Operator performance in flying a simulated remote maneuvering unit (RMU) on a coplanar satellite inspection mission was evaluated under two conditions of RMU attitude control and two conditions of cockpit instrumentation. The maneuver was repeatedly performed successfully using either an on-off acceleration-command attitude control system or an on-off rate-command attitude control system, each with either a full panel of cockpit instruments (six) or only one cockpit instrument. The rate-command system was found to be superior for pitch control during station keeping and for roll control in general. The acceleration-command system was superior for pitch control during the trajectory portions of the mission. Because both control systems had disadvantages, consideration of a variable rate-control system is recommended. More economical and precise RMU control was obtained under the full-panel cockpit instrumentation condition irrespective of the control system used. The instruments of most value were found to be those which provided X (longitudinal) and Z (vertical) distance information. The limitations of the simulation and the advantages and disadvantages of an 'inside-out' versus an 'outside-in' television display of the target and its surrounds are also discussed.
Six subjects successfully reorinted the attitude of a simulated remote maneuvering unit (RMU) using an on-off acceleration command control system. RMU attitude was determined solely by viewing the space scene being televised by the RMU. That scene consisted of a spherical target, the earth horizon, and a star background, all of which interacted realistically as a function of the subject's RMU control inputs. The RMU was controlled under three conditions of angular acceleration: 4, 8, and 12 degrees/sec sq. Four deg/sec sq. resulted in least expenditure of fuel and most accurate rate control without a sacrifice in time. These results and subjects' preference data recommended pitch, yaw, and roll accelerations of 4 deg/sec sq. when using an on-off acceleration command control system. Subjects relied primarily on the orientation of the earth horizon for RMU roll reference. Because the horizon was not always in view, errors in roll were significantly greater than those in pitch and yaw. This result may have been an artifact of the simulation; too few stars were simulated to allow their use as an adequate roll reference. Simultaneous or separate attitude control resulted in equally effective RMU reorientation. Similarly, pilots and nonpilots performed equally well. However, pilots can usually be trained faster than nonpilots. (Author).