| 摘要 |
An aircraft gyro simulator is operable in a dynamic mode to produce simulated pitch, roll and azimuth signals as a function of control wheel commands, flight control system commands, control surface status and the stored equations of flight for the aircraft under test. In its manual mode, the simulator responds to manual control commands to individually vary pitch, roll or azimuth, thereby testing aircraft systems response. In addition, multiple channels of tracking gyro signals may be produced, with each channel having a manually controlled offset of one or more gyro signals to test aircraft employing multiple autopilot systems.
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