| 摘要 |
Aircraft altitude is visually displayed at a front panel of a flight instrument in analog form by a rotating pointer and in digital form by means of a rotary drum digital indicator. Barometric pressure is converted into rectilinear motion to drive a mechanical-to-electrical transducer providing a signal to a servo amplifier having an output coupled to a servomotor. The servomotor drives both the rotating pointer and the rotary drum digital indicator. Also coupled to the mechanical-to-electrical transducer is a manually adjustable set input signal to correct for atmospheric pressure along a given flight path with respect to sea level. Temperature and altitude error corrections are also coupled to the transducer to correct the servomotor drive signal to give a true indicated altitude display. Also driven by the servomotor is a pressure altitude encoder for providing absolute altitude digital signals for transmission to a ground station. As a further extension, the servomotor drives a velocity generator that functions integrally with an altitude selector to provide vertical velocity control signals to the aircraft autopilot system.
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