Description and performance of the Langley differential maneuvering simulator
National Aeronautics and Space Administration, 1973 - Technology & Engineering - 92 pages
The differential maneuvering simulator for simulating two aircraft or spacecraft operating in a differential mode is described. Tests made to verify that the system could provide the required simulated aircraft motions are given. The mathematical model which converts computed aircraft motions into the required motions of the various projector gimbals is described.
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2-needle absolute magnification Actual system Airspeed Angle of attack APPENDIX attacker body-axis system axis system azimuth mirror buffet buffet-signal camera camera zoom lens cockpit command of sky-Earth CRT projector Deadband deg/sec differential maneuvering simulator dimensionless drive Earth transparency equation ft/div g-suit gimbal angle gimbal center in./sec kinescope knots lamp position lamp servos Langley differential maneuvering Langley Research Center law of cosines line of sight m/sec Mach number math model mirror gimbal motion needle rotation no-load velocity performance pilot pitch gimbal position error potentiometer projection geometry projection screen projection servos Quaternion rad/in-lb rad/m-N rad/in-lb rad/m-N rad/in-lb rad/m-N rad/sec2 deg/sec2 range relative to center rotation Total accuracy servo dynamics shown in figure sky-Earth gimbal sky-Earth lamp sky-Earth projector sky-Earth scene steady-state time lag synchronization target-image Target-image projection target-mirror target-model gimbals transformation matrix transparency relative U.S. Customary Units vector which defines z-components of vector zoom lens