Patent GB-900922-A (GB)
Title: Improvements relating to air inlet shock control apparatus
IPC: F02C7/057
Filed: 1960-07-15
Abstract: 900,922. Automatic control systems for shock waves. UNITED AIRCRAFT CORPORATION. July 15, 1960 [July 20, 1959], No. 24768/60. Class 38 (4). [Also in Groups XXVI and XL (c)] A supersonic intake duct having a region in its length wherein a shock wave may be located, has means for varying the flow in the duct, a signal generator in a downstream subsonic flow region for directing a signal travelling upstream towards the shock wave region, a signal receiver for receiving the reflected echo signals from the shock wave region and means responsive to the signal for varying the flow in the duct. A supersonic air intake 10, Fig. 1, has an upstream opening 12, a convergent portion 14 in which are located oblique shock waves 16 terminating in a normal shock 18 which is preferably located at the upstream end of the minimum area or throat portion 20. The duct has a divergent portion leading to an air breathing power plant 24. A high-frequency sound generator 26 directs sound in an upstream direction toward the normal shock 18 where it is reflected, the echo travelling downstream to a receiver 28. The sound generator 26 sends out intermittent signals which are echoed back to the receiver. The signal generator and the receiver both send their signals to the acoustic system 30 which senses a resultant signal to the inlet geometry control 34 which may control the opening of by-pass door 36 or actually vary the physical geometry of the inlet. The geometry control may be any form of hydraulic or electrical servo device. The acoustic system, Fig. 2, comprises a power supply feeding an oscillator 42 which is connected to a pulse transmitter gate 44. The transmitter gate 44 is a form of time interrupter which permits the oscillating signal to be transmitted for a predetermined time and is then interrupted for a length of time sufficient for the receiver 28 to sense the echo. This function is performed by the transmitterreceiver selector switch 46 so that a highfrequency sound signal of a predetermined frequency and a given pulse is transmitted to the sound generator 26 at the same time the echo timer 54 is signalled to start the timing cycle. The echo received by the receiver 28 is transmitted to the selector switch 46. Since the local speed of sound changes along the duct axis, the signal received by the echo timer will not be an exact measurement of the shock wave position. Measurements of Mach number and stagnation or inlet air temperature are therefore fed to a calibration signal programmer 58 which feeds a comparator 60 which determines the difference between the desired and measured echo timer. The difference is fed to the inlet geometry control 34. In a modification, an intake is provided with a throat which is of constant or nearly constant cross-section over a predetermined length. In a further modification, Figs. 4 and 5 (not shown), a pair of sound reflectors are spaced along the axis of flow on either side of the required position of the shock wave. The signal from the sound generator is scanned first on one sound reflector, then on the shock wave and finally on the second sound reflector. The echoes from these sources are compared in a comparator and their relationship determines the nature of the signal transmitted to the inlet geometry controls.