| 摘要 |
<p>836,955. Fluid pressure servomotor control systems. UNITED AIRCRAFT CORPORATION. Feb. 19, 1958 [June 4, 1957], No. 5383/58. Class 135. In an arrangement for maintaining a constant ratio between reference pressures P 1' P 2 in a duct 16 upstream and downstream respectively of a fixed-area orifice 12 and determined by the ratio of the end areas of a freely floating differential piston valve 22, the sensitivity of the system is increased by a hinged valve 14 providing a variable-area discharge orifice 28 for the duct 16 and connected to a servo-piston 30 subjected to pressure P 2 . The lower and upper ends of valve 22 are subjected to the pressures P 1 , P 2 respectively, and movement of the valve controls the supply of pressure fluid to the duct 16 from an inlet 18. Assuming that upon departure from steady-state conditions valve 14 moves to the right to increase the area of orifice 28, the resulting fall in pressure P 2 results in upward movement of valve 22 and reduction in the supply of pressure fluid, and at the same time causes movement of servo-piston 30 to the left to close valve 14 to increase the rate at which the steady state is restored. The valve 22 and piston 30 operate in the reverse manner if valve 14 moves to the left to cause an increase in pressure P 2 . The regulator may be used to receive an input signal, such as an engine speed signal, through an adjustable pivot 50 for valve 14 and to provide a corrective output signal from the servo-piston 30 to the fuel throttle valve.</p> |
