초록 ▼

An aircraft flight control system for use with a dual or tandem hydraulic actuator coupled to a flight control surface through an actuating rod. Each half of the tandem actuator is controlled by a respective electrohydraulic servovalve. Each electrohydraulic servovalve is controlled by signals appli

An aircraft flight control system for use with a dual or tandem hydraulic actuator coupled to a flight control surface through an actuating rod. Each half of the tandem actuator is controlled by a respective electrohydraulic servovalve. Each electrohydraulic servovalve is controlled by signals applied to either of two actuating coils. Control signals are applied to the actuating coils from three controllers. The control signals are generated as a function of the difference between the flight control signal and a feedback signal indicative of the position of the actuating rod. Each electrohydraulic servovalve includes a pair of linear variable differential transformers generating feedback signals indicative of the position of the valve stem in each electrohydraulic servovalve. The valve feedback signals are compared to each other and to reference signals corresponding to the expected value of such feedback signals in order to detect and identify malfunctions in the flight control system. In one embodiment, the electrohydraulic servovalves are controlled by two channels of a primary controller in normal operation. In the event of a malfunction, control is transferred to one of two secondary controllers. In another embodiment, the electrohydraulic servovalves are controlled by respective primary controllers, with control being transferred to one of two channels of a secondary controller in the event of a malfunction.

대표청구항 ▼

A hydraulic flight control system comprising: a tandem hydraulic actuator having an actuating rod connected to a pair of pistons mounted in respective first and second cylinders; first and second electrohydraulic servovalves controlling the flow of hydraulic fluid into and out of said first and seco

A hydraulic flight control system comprising: a tandem hydraulic actuator having an actuating rod connected to a pair of pistons mounted in respective first and second cylinders; first and second electrohydraulic servovalves controlling the flow of hydraulic fluid into and out of said first and second hydraulic cylinders, respectively, each of said electrohydraulic servovalves being controlled by a pair of actuating coils; first, second and third controller means receiving a flight control signal, said first controller means having a control channel that is capable of providing an output to one actuating coil of said first electrohydraulic servovalve for operating said first electrohydraulic servovalve, said second controller means having a control channel that is capable of providing an output to one actuating coil of said second electrohydraulic servovalve for operating said second electrohydraulic servovalve, said third control having first and second control channels that are capable of providing respective outputs to the other actuating coils of said first and second electrohydraulic servovalves for operating either or both of said electrohydraulic servovalves; and monitor and control logic means for monitoring the performance of said controller means, electrohydraulic servovalves and actuator, said monitor and control logic means selectively enabling said controller means so that each of said electrohydraulic servovalves is operated by only one controller means at a time and, in the event of a malfunction in the performance of one electrohydraulic servovalve or controller means driving said electrohydraulic servovalve, enabling the other controller means connected to said electrohydraulic servovalve.