| 摘要 |
<p>935,728. Pressure responsive apparatus. INTERCONTINENTAL DYNAMICS CORPORATION. Jan. 22, 1962 [Jan. 23, 1961], No. 2259/62. Class 106 (2). A testing instrument for calibrating the altimeter and air-speed indicator of aircraft comprises two manifolds, 22 and 26, which can be connected, by lines 27 and 28, to the static and Pitot inlet ports, respectively, of the aircraft, the static manifold 22 being maintained at a pressure, with respect to vacuum, pre-set on an "altitude" dial 15 and the Pitot manifold 26 being maintained at another pressure, with respect to the static pressure, pre-set on an " air-speed " dial 16. The pressures are maintained constant at the chosen values with the aid of transducers 60, 45 and electronic servoamplifiers 62, 46 which supply to solenoidoperated control valves 61, 44 regulating the manifold pressures output current proportional to error signals generated by the difference between the pre-set pressures and the existing pressures as measured, in terms of altitude and air-speed respectively, by a calibrated altimeter 13 and air-speed indicator 14. The altimeter 13 is a standard diaphragm or capsule type in which the static pressure is compared with vacuum. This pressure may be chosen above or below the ambient pressure by manual operation of valve 50 whereby manifold 22 may be connected to the high-pressure side or the low-pressure side of pump 30. The correct sign for the static error signal is automatically given by a reversing switch 59 adjusted by movement of the valve 50. The pump 31 for the Pitot manifold 26 has its inlet connected to the static manifold 22. Should the servos fail, the manifolds may be bled manually by means of valves 70 and 41. The control valves 61 and 44 have resilient portions which come down on to obliquelytruncated conical nozzles: in this way the rate of air flow can be finely controlled.</p> |
