| 摘要 |
<p>1,080,951. Automatic control of shock waves. HAWKER SIDDELEY DYNAMICS Ltd. Jan. 14, 1965 [Jan. 14, 1964], No. 1621/64. Heading G3R. [Also in Division F1] An aircraft gas turbine engine has a rectangular cross-section intake duct 1 leading to the engine compressor 12. In order to maintain the air mass flow to the compressor constant at a predetermined value corresponding to a predetermined position of a standing shockwave 6 resulting from supersonic flight, a temperature sensitive probe 10 is positioned at the desired position of the shockwave and any deviation of the shockwave from this position is sensed to cause adjustment of a vent 4 and a return of the shockwave to the desired position. The sensing mechanism includes additional temperature probes 9, 11 disposed respectively upstream and downstream of probe 10. An electrical signal corresponding to the average temperature measured by probes 9, 11 is transmitted from an averaging unit 13 to a unit 14 for comparison with the signal from probe 10. Any deviation of the shockwave 6 from its desired position causes a change in signal from probe 10, the resulting error signal passing to an amplifier 15 and to an electro-mechanical or electrohydraulic motor 16 controlling the vent 4. A negative-feedback line 17 stabilizes the system. The invention is applicable also to the control of gas flow through an aircraft engine exhaust duct into the atmosphere according to the position of the shockwave associated with the flow.</p> |
