Inlet control system for supersonic aircraft

摘要

861,005. Fluid-pressure servomotor-control systems. BENDIX CORPORATION. Feb. 20, 1959 [April 23, 1958], No. 5963/59. Class 135. [Also in Group XXVI] To obtain maximum pressure recovery at the air inlet of an engine of a supersonic aircraft, the oblique shock wave occurring at the inlet is positioned in accordance with Mach number by positioning an inlet wedge member 14 as a function of static and total head pressures as measured by detectors 63, 64. Since such an arrangement may provide a greater air flow than is required over a portion of the operating range a by-pass gate or valve 17 is provided for diverting air from the engine and this valve is controlled by the Mach number measured by static and total head detectors 118, 122 and modified in accordance with the position of the member 14. The member 14, with which is movable a pivoted member 16 situated within the forward portion of the engine nacelle 10 to provide a suitable inlet configuration, is positioned by a servomotor 22 under the control of a spool valve 34 which is moved hydraulically in response to movement between nozzles 48, 50 of a flapper 56 actuated by a diaphragm 58 subject on its upper face to static pressure and on its lower face to total head pressure which has passed through a restriction 68 and a chamber 70 containing a bleed 76 which is adjusted by a needle 74 controlled by a cam 142 movable by the servomotor 22. Sonic flow through the bleed 76 is obtained by connecting it to an ejector 82 fed, e.g. from the compressor of the engine. The by-pass valve 17 is operated by a servomotor 90 controlled by a diaphragm 112 and spool valve 108 similar to those controlling the servomotor 22, a variable bleed 134 being governed by a cam 144 also movable by the servomotor 22. At some angles of attack the system may limit air flow to a greater extent than desired and to overcome this the by-pass valve 17, when closed, opens a valve 152 which bleeds the chamber 70 to cause the inlet area to be increased, this bleed being closed by a valve 162 actuated by an abutment 156 on the cam 142 as the wedge member 14 reaches its fully open position. At the same time a valve 164 is opened by an abutment 166 so that the lower face of the diaphragm 112 is subject to full total head pressure whereby the by-pass valve 17 is maintained closed until the member 14 moves away from its fully open position. At high Mach numbers, when movement of the member 14 ceases, the static head 118 controls the servomotor 90 to maintain the shock wave that is normal to the air flow at a given position along the length of the head.