JP2008185171A - Fluid device - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To achieve an inexpensive and reliable fluid device by using a control valve capable of being manufactured at low cost without sacrificing safety for surely holding a wing surface in a horizontal direction in flight control of an aircraft even when an electrical signal is lost. <P>SOLUTION: The fluid device more inexpensive and more reliable than a conventional electrohydraulic servo valve having a large number of parts is achieved by the usage of the control valve equipped with a sleeve 50, a spool 60, an elastic body 70 energizing one end side of the spool, a solenoid 80 energizing the other end side of the spool, and a differential transformer 90 for detecting a position of the spool, and having a small number of parts. When the electric current supplied to the solenoid 80, for example, a proportional solenoid, is lost by failure, the spool energized by the elastic body 70, for example, a spring, is moved from the one end side to the other end side, and thereby, the wing surface 110 is held to be almost in the horizontal direction, and safety can be secured. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to an elastic body, a control valve energized by a solenoid, and a fluid device including the control valve.

Conventionally, an electrohydraulic system that has a torque motor that moves a shaft called a flapper in response to a supply current, moves the spool position by controlling the pressure balance at both ends of the spool by moving the shaft, and performs hydraulic mechanical feedback control A servo valve (Electro Hydraulic Servo Valve) is known. (For example, see Patent Documents 1 and 2)
There is also known a fluid device that expands and contracts a piston rod of an actuator using the servo valve. (For example, see Patent Document 3)
US Pat. No. 4,624,284 US Patent Publication 3,023,782 US Patent No. 4,513,782

  However, in the conventional electrohydraulic servo valve, in order to drive the spool, a torque motor and a flapper which are mechanically movable parts and a hydraulic circuit for performing pressure balance control at both ends of the spool are necessary. Accordingly, there are problems that the number of parts is large, the time for assembling and adjusting them is also great, and the product cost is increased.

  The present invention provides a control valve that can be manufactured at low cost without sacrificing the safety of reliably holding the wing surface in the horizontal direction even when the electrical signal disappears in flight control of the aircraft. The purpose is to provide.

The fluid device according to the present invention includes an actuator in which one and the other fluid chambers are formed on both sides of a piston rod housed in a cylinder, and the piston rod is moved by supplying and discharging a working fluid to both fluid chambers, and the actuator A control valve that controls supply and discharge of the working fluid supplied to the sleeve, and the control valve biases the sleeve, the spool, the elastic body that biases one end of the spool, and the other end of the spool. A fluid device having a solenoid and a differential transformer for detecting the position of the spool, and comprising: an electric signal from the differential transformer; and an arithmetic circuit for driving the solenoid by an input signal output from a control unit In this case, the solenoid is excited by the electric signal output from the arithmetic circuit, the elastic body is energized, and the spool is moved to the other end side or one end side. By, it has a configuration extending and retracting the piston rod of the actuator.
With this configuration, the control valve of the present invention is configured with fewer parts than a conventional electrohydraulic servovalve, and therefore can be manufactured at low cost.

In the fluid device of the present invention, the control valve is controlled by a steering electric signal input, and the piston rod is connected to an aircraft wing surface.
With this configuration, as described above, a control valve having a small number of parts is used, so that the fluid device can be made inexpensive and highly reliable.

The fluid device of the present invention is configured to connect the piston rod to a spoiler which is an aircraft wing surface.
With this configuration, in the flight control of the aircraft, even when the electrical signal disappears due to a failure, the piston rod is held in the most retracted position (the wing surface is in the horizontal direction), and the fluid device can ensure safety. it can.

  ADVANTAGE OF THE INVENTION According to this invention, while being able to manufacture a control valve with high reliability at low cost, the fluid apparatus which ensured safety | security especially in flight control of an aircraft can be provided.

  Hereinafter, an embodiment of a fluid device according to the present invention will be described with reference to FIGS.

    As shown in FIG. 1, the fluid device 10 according to the present embodiment forms one and the other fluid chambers on both sides of a piston rod 30 housed in the actuator 20, and supplies the working fluid to both fluid chambers. And an actuator 20 that moves the piston rod 30 by discharging, and a control valve 40 that controls the supply and discharge of the working fluid supplied to the actuator 20, and the control valve 40 is elastic to urge the sleeve 50 and one end of the spool 60. Body 70, solenoid 80 that biases the other end of spool 60, and differential transformer 90 that detects the position of spool 60, an electrical signal from differential transformer 91, and a control unit (not shown) A first arithmetic unit 101 that receives the output command signal and performs arithmetic processing for position control; a second arithmetic unit 102 that drives the solenoid 80; It includes a blade surface 110, a.

  Next, as shown in FIG. 1, the operation of the fluid device 10 will be described in the case where the output current from the computing unit 102 to the solenoid 80 is zero.

When no current flows through the solenoid 80 (for example, a proportional solenoid) on the other end side, the spool biased by the elastic body 70 (for example, a spring) moves from the one end side to the other end side. At this time, the working fluid supplied to the P _S port of the control valve 40 flows in the direction for housing the piston rod 30, and is discharged from the P _{R (2)} port of the control valve 40. At the same time, the blade surface 110 connected to the piston rod 30 is maintained in a substantially horizontal direction.

Thereby, even when the current supplied to the solenoid 80 disappears due to a failure or the like, the piston rod 30 can be held at the most housed position.
Further, as described above, with this configuration, even when the electrical signal disappears due to a failure in flight control of the aircraft, the piston rod 30 is held at the most retracted position (the wing surface is substantially horizontal) to ensure safety. It can be set as the fluid apparatus 10 made.

  Next, as shown in FIG. 2, the operation of the fluid device 10 will be described in the case where the output current from the calculation unit 102 is applied to the solenoid 80.

When a command signal (voltage corresponding to a predetermined rudder angle signal) for operating the blade surface is input from the control unit (not shown) to the calculation unit 102, an electric signal (converted by an amplifier) output via the calculation circuit 102 is input. The solenoid 80 is excited by the current), and the spool is moved to one end side against the elastic body 70. At this time, the working fluid supplied to the P _S port of the control valve 40 flows in a direction to extend the piston rod 30, and is discharged from the P _{R (1)} port of the control valve 40. At the same time, the blade surface 110 connected to the piston rod 30 moves in a substantially vertical direction.

Here, the displacement amount of the spool 60 is detected by the differential transformer 90, and compared with the command signal in the calculation unit 102, the solenoid 80 is controlled so as to obtain a predetermined control surface angular velocity.
Next, similarly, a displacement amount of the piston rod 30 corresponding to the steering angle of the blade surface is detected by the differential transformer 91 connected to the piston rod 30 in the actuator 20, and compared with the command signal in the calculation unit 101. And the signal to the calculating part 102 which controls the solenoid 80 is output so that it may become a predetermined rudder angle.

  Specifically, it is generated by the voltage corresponding to the predetermined angular velocity of the blade surface input to the second calculation unit 102 via the first calculation unit 101 and the displacement of the spool 60 detected by the differential transformer 90. The feedback voltage is equalized, and the current value for exciting the solenoid 80 is set to be a current value that balances the reaction force of the elastic body 70 facing the spool 60, so that the spool 60 is proportional to the input voltage to the arithmetic unit 102. Stops at the displacement. As a result, the flow rate of the control valve can be controlled to control the speed of the actuator and the angular speed of the blade surface 110. (Inner loop control)

  Further, the voltage corresponding to the predetermined steering angle signal input in the first calculation unit 101 and the feedback voltage generated by the displacement of the piston rod 30 detected by the differential transformer 91 are subtracted (or added), The feedback voltage generated by the displacement of the spool 60 detected by the differential transformer 90 is subtracted (or added) to the voltage value by the second arithmetic unit 102, and the current value for exciting the solenoid 80 is the elastic body facing the spool 60. Calculation processing is performed so that the current value is balanced with the reaction force of 70, and the spool 60 is stopped at the hydraulic neutral pressure of the control valve. Thereby, the angle of the predetermined blade surface 110 can be controlled through the inner loop that controls the speed of the actuator by controlling the flow rate of the control valve. (Outer loop control)

  Further, the second calculation unit 102 can be set so that an offset value is given to the neutral point of the spool 60. By providing this offset value, the wing surface 110 can be controlled up and down, and the fluid device of the present invention can also be used for ailerons and elevators on flight control wing surfaces of aircraft.

  As described above, there is an effect that a highly reliable control valve can be manufactured at low cost, and in particular, it is possible to provide a fluid device that ensures safety in flight control of an aircraft, which is useful. is there.

The fluid apparatus which concerns on one embodiment of this invention shows the state when the solenoid is not excited. The fluid apparatus which concerns on one embodiment of this invention WHEREIN: The state when a solenoid is excited is shown.

Explanation of symbols

DESCRIPTION OF SYMBOLS 10 Fluid apparatus 20 Actuator 30 Piston rod 40 Control valve 50 Sleeve 60 Spool 70 Elastic body 80 Solenoid 90,91 Differential transformer 101 1st calculating part 102 2nd calculating part 110 Blade surface 120 for flight control 120 Fluid pump 121 Tank

Claims (3)

  One and the other fluid chambers are formed on both sides of the piston rod accommodated in the cylinder, and the piston rod is moved by supplying and discharging the working fluid to both fluid chambers, and the working fluid supplied to the actuator is supplied. A control valve for controlling the discharge, the control valve including a sleeve, a spool, an elastic body that biases one end of the spool, a solenoid that biases the other end of the spool, and a position of the spool Output from the arithmetic circuit in a fluid device comprising an electric signal from the differential transformer and an arithmetic circuit for driving the solenoid by a command signal output from the control unit. By energizing the solenoid by the generated electrical signal, energizing the elastic body and moving the spool to the other end side, Fluid and wherein the expanding and contracting the piston rod. 2. The fluid device according to claim 1, wherein the control valve is controlled by a steering electric signal input and connects the piston rod to an aircraft wing surface. The fluid device according to claim 2, wherein the blade surface is a spoiler.