| 摘要 |
<p>1,181,668. Measuring electrically. ELLIOTT BROS. (LONDON) Ltd. July 10, 1967 [July 21, 1966], No.32912/66. Heading G1N. [Also in Division G3] In air-responsive apparatus for an aircraft, e. g. a helicopter, a Pitot tube 10, Fig. 1, movable about two perpendicular axes, is kept pointing into the incident air stream by servo means controlled by devices sensitive to the direction of the incident air stream. As described, the tube 10 is pivotally mounted in bearings 11 on an assembly 1 itself pivotally mounted on fixed axis 3. The assembly is provided with vanes 7 and 8, 9, shaped to automatically align themselves with the incident air stream, pivotable about axes parallel to that of bearings 11 and axis 3. The misalignments between the vanes and tube 10 in the planes containing the axes of pivot are sensed by electrical transducers 12, 19 detecting the outputs of differentials 13, 20, Fig. 3, connected to the tube 10 and vanes 8, 9, and assembly 1 and vane 7, respectively. The outputs of the transducers are fed to separate servoamplifiers, servomotors with tachometer feedback and gearing to reposition the tube 10. Alternatively the servosystems may be hydraulic or pneumatic. The control of the orientation of the tube about one axis may be mechanical. Additionally a vertical gyroscope and temperature sensor are provided on the aircraft from the outputs of which and that of the Pitot tube, indications of altitude, rate of climb or descent temperature, airspeed and side slip are computed, Fig. 3, the angles of pitch and yaw being obtained from the angular orientation of the Pitot tube.</p> |
