An aircraft aileron neutral positioning device

Abstract

The present invention discloses an aircraft aileron neutral positioning device. This device uses two voltmeters with measurement outputs to measure the position voltage signal values output by an electric mechanism with position feedback, and uses the contact points of a relay connected to the output ends of the voltmeters to control the on-off of the control circuit of the electric mechanism, so as to accurately position the electric mechanism at the neutral position. This device has an accurate positioning operation mode and a free operation mode, which can meet the requirements of various usage scenarios. This device and method use two voltmeters, which can reduce (eliminate) the errors caused by the sensitivity of the control system during the extension and retraction actions of the aircraft electric mechanism, enabling the aircraft electric mechanism to stop accurately at the same position during the extension and retraction actions. The voltmeter can set the voltage threshold of the output terminal according to a predetermined rule within the measurement range, and can achieve accurate positioning at any position within the full stroke range.

Description

Technical Field

[0001] This application relates to the measurement and processing of analog signals of sensors and the design technology of automatic control logic circuits, and particularly to an aircraft aileron neutral positioning device. Background Art

[0002] During the assembly of a certain type of aircraft, the assembly personnel need to adjust the aileron surface to the neutral position before proceeding to the next step. The original control logic circuit for controlling the deflection angle of the aileron trim tab was built into the aircraft electric mechanism. The assembly personnel only needed to connect the aircraft electric mechanism to a 24V power supply, control the motor of the electric mechanism to rotate forward (reverse), and the electric mechanism would perform the release (retraction) action, thereby driving the aileron surface to deflect upward (downward). When the aileron surface reached the maximum upward (downward) deflection angle position, the motor would automatically reverse and stop at the mid-position of the retraction and extension of the aircraft electric mechanism, and the aileron surface would also exactly stop at the neutral position.

[0003] In the upgraded model of this aircraft, the aircraft designers have upgraded the aircraft electric mechanism that controls the rotation of the aileron trim tab. The new aircraft electric mechanism does not have the function of automatically stopping at the neutral position and will automatically stop when it runs to the maximum upward (downward) deflection angle position. The aircraft electric mechanism only performs the release and retraction actions according to the instructions of the flight control system. At the same time, the electric mechanism converts its position into a voltage signal of 0 - 5V through an internal position signal conversion circuit and feeds it back to the signal input terminal of the flight control system. When the aircraft electric mechanism is at the limit position of retraction, the voltage signal output is 0V. When the aircraft electric mechanism is released from the limit position of retraction, the voltage signal output gradually increases from 0V. When the electric mechanism moves to the neutral position, the voltage signal output value is 2.5V. When the electric mechanism moves to the limit position of release, the voltage signal output value is 5V. When the assembly personnel debug the deflection angle of the aileron surface on-site, they cannot accurately and quickly stop the aileron surface at the neutral position according to the debugging method of the original aircraft electric mechanism used. They must repeatedly control the electric mechanism to perform the release (retraction) action to roughly stop the aileron surface at the neutral position, resulting in low operation efficiency and low positioning accuracy. Summary of the Invention

[0004] To solve the above problems, the present invention provides an aircraft aileron neutral positioning device, which can accurately control the automatic positioning and stopping of the aircraft aileron at a preset position by constantly reading the position feedback voltage value of the aircraft electric mechanism through a voltmeter.

[0005] An aircraft aileron neutral positioning device, comprising a box body, an operation panel, and an electrical component mounting plate. The electrical component mounting plate is fixed under the operation panel inside the box body. The operation panel is embedded with a release control voltmeter and a retraction control voltmeter connected in parallel, a 24V power supply positive terminal, a 24V power supply negative terminal, a power indicator light, an action selection knob, a free running mode self-locking button, an electric mechanism action control momentary button, a free running mode indicator light, and a connection socket. The electrical component mounting plate is equipped with a free running mode relay, an electric mechanism action control relay, a positioning control relay during release, and a positioning control relay during retraction. Set the voltage threshold of the output terminals of the release control voltmeter and the retraction control voltmeter as the neutral position feedback voltage value of the aircraft electric mechanism. Connect the device to the aircraft electric mechanism through the aircraft electric mechanism cable. After connecting the power supply with the power cable, the power indicator light is on. Turn the action selection knob to the "release" gear and press the electric mechanism action control momentary button. The release action control input terminal of the aircraft electric mechanism accesses a 24V high level, and the aircraft electric mechanism executes the release action and drives the aileron to swing. When the aileron swings to the neutral position, it automatically stops, completing the neutral position positioning. Turn the action selection knob to the "retraction" gear and press the electric mechanism action control momentary button. The retraction action control input terminal of the aircraft electric mechanism accesses a 24V high level, and the aircraft electric mechanism executes the retraction action and drives the aileron to swing. When the aileron swings to the neutral position, it automatically stops, completing the neutral position positioning. Turn the action selection knob to the "stop" gear and press the electric mechanism action control momentary button. The aircraft electric mechanism is locked. When the "free running mode self-locking button" is pressed, the free running mode relay is energized and connected, and the device is in the free running mode, which can control the aircraft electric mechanism to move freely within the full stroke range. In this mode, the aileron will not automatically position and stop at the neutral position. By changing the voltage threshold of the output terminals of the release control voltmeter and the retraction control voltmeter, the aircraft electric mechanism can be controlled to automatically position and stop at any preset position.

[0006] Further, the measurement input terminal of the release control voltage meter and the measurement input terminal of the retraction control voltage meter are connected to the signal output terminal of the aircraft electric mechanism position signal conversion circuit. The positive terminal and negative terminal of the 24V power supply are respectively connected to the positive and negative poles of the power supply. The power indicator is connected to the positive terminal of the 24V power supply. The free-running mode self-locking button and the free-running mode indicator are connected to the free-running mode relay. The instantaneous action button for controlling the electric mechanism action is connected to the relay for controlling the electric mechanism action. The release and retraction contacts of the action selection knob are respectively connected to the release action control input terminal of the aircraft electric mechanism and the retraction action control input terminal of the aircraft electric mechanism, controlling the forward and reverse rotation of the aircraft electric mechanism. The connection socket is connected to the connection plug of the aircraft electric mechanism, reading the position feedback signal of the aircraft electric mechanism through the aircraft electric mechanism cable, providing 24V power to the aircraft electric mechanism, and sending release and retraction action control signals to the aircraft electric mechanism.

[0007] Further, the common points of the free-running mode relay, the relay for controlling the electric mechanism action, the positioning control relay during release, and the positioning control relay during retraction are connected to 0V. The other end of the free-running mode relay is connected to the free-running mode self-locking button. When the free-running mode self-locking button is pressed, the free-running mode relay is energized and connected, controlling the aircraft electric mechanism to move freely within the full stroke range. The other end of the relay for controlling the electric mechanism action is connected to the instantaneous action button for controlling the electric mechanism action. When the instantaneous action button for controlling the electric mechanism action is pressed, the aircraft electric mechanism performs the release or retraction action. The other end of the positioning control relay during release is connected to the output terminal of the release control voltage meter. When the output terminal of the release control voltage meter outputs a 24V high level, the aircraft electric mechanism can perform the release action. The other end of the positioning control relay during retraction is connected to the output terminal of the retraction control voltage meter. When the output terminal of the retraction control voltage meter outputs a 24V high level, the aircraft electric mechanism can perform the retraction action.

[0008] Further, turn the action selection knob to the "Release" position, press the momentary button for the electric mechanism action control. The relay for the electric mechanism action control is energized and turned on. The normally open contact of the action control relay No. 2 is turned on. The aircraft electric mechanism is at the retraction limit position, and the output voltage at the output terminal of the aircraft electric mechanism position signal is 0V. The voltage is less than the voltage threshold at the output terminal of the release control voltmeter, and the output voltage at the output terminal of the release control voltmeter is 0V. The positioning control relay during release is not turned on, and the normally closed contact of the relay remains turned on. The input terminal for the release action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft motor rotates to achieve the release action. The output voltage at the output terminal of the aircraft electric mechanism position signal gradually increases. When the input terminal of the release control voltmeter detects that the output voltage at the output terminal of the aircraft electric mechanism position signal is greater than the voltage threshold at the output terminal of the release control voltmeter, the output voltage at the output terminal of the release control voltmeter quickly changes from 0V to 24V. The positioning control relay during release is immediately turned on, and the normally closed contact of the positioning control relay during release is turned off. The voltage connected to the input terminal for the release action control of the aircraft electric mechanism changes from 24V high level to 0V, and the release action of the aircraft electric mechanism immediately stops at the neutral position.

[0009] Further, turn the action selection knob to the "Retract" position, press the momentary button for the electric mechanism action control. The relay for the electric mechanism action control is energized and turned on. The normally open contact of the action control relay No. 1 is turned on. The aircraft electric mechanism is at the release limit position, and the output voltage at the output terminal of the aircraft electric mechanism position signal is 5V. The voltage is greater than the voltage threshold at the output terminal of the retraction control voltmeter, and the output voltage at the output terminal of the retraction control voltmeter is 24V. The positioning control relay during retraction is turned on, and the normally open contact of the positioning control relay during retraction remains turned on. The input terminal for the retraction action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft motor rotates to achieve the retraction action. The output voltage at the output terminal of the aircraft electric mechanism position signal gradually decreases. When the input terminal of the retraction control voltmeter detects that the output voltage at the output terminal of the aircraft electric mechanism position signal is less than the voltage threshold at the output terminal of the retraction control voltmeter, the output voltage at the output terminal of the retraction control voltmeter quickly changes from 24V to 0V. The positioning control relay during retraction is immediately turned off, and the normally open contact of the positioning control relay during retraction is turned off. The voltage connected to the input terminal for the retraction action control of the aircraft electric mechanism changes from 24V high level to 0V, and the retraction action of the aircraft electric mechanism immediately stops at the neutral position.

[0010] Further, the normally open contact 1# of the free-running mode relay and the normally open contact 2# of the free-running mode relay are respectively connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism, and are respectively connected in parallel with the normally closed contact of the positioning control relay during extension and the normally open contact of the positioning control relay during retraction. When the free-running mode self-locking button is pressed, the button closes and self-locks, the free-running mode relay is energized and turned on, the normally open contact 1# of the free-running mode relay and the normally open contact 2# of the free-running mode relay close, and the free-running mode indicator light is lit, indicating to the user that the device is in the free-running mode. The action selection knob is turned to the "extension" position, and the momentary action control button of the electric mechanism is pressed. The action control relay of the electric mechanism is energized and turned on, the normally open contact 2# of the action control relay is turned on, the extension action control input terminal of the aircraft electric mechanism is connected to a 24V high level, and the aircraft motor rotates to achieve the extension action. Because the normally open contact 2# of the free-running mode relay connected to the extension control circuit is always in the closed state, when the aircraft electric mechanism passes the neutral position, the disconnection of the normally closed contact of the positioning control relay during extension will not stop the extension action of the aircraft electric mechanism, and it will only automatically stop after the aircraft electric mechanism reaches the extension limit position. The action selection knob is turned to the "retraction" position, and the momentary action control button of the electric mechanism is pressed. The action control relay of the electric mechanism is energized and turned on, the normally open contact 1# of the action control relay is turned on, the retraction action control input terminal of the aircraft electric mechanism is connected to a 24V high level, and the aircraft motor rotates to achieve the retraction action. Because the normally open contact 1# of the free-running mode relay connected to the retraction control circuit is always in the closed state, when the aircraft electric mechanism passes the neutral position, the disconnection of the normally open contact of the positioning control relay during retraction will not stop the retraction action of the aircraft electric mechanism, and it will only automatically stop after the aircraft electric mechanism reaches the retraction limit position. When the free-running mode self-locking button is pressed again to disconnect the button, the free-running mode relay is de-energized, the free-running mode indicator light goes out, the normally open contact 1# of the free-running mode relay and the normally open contact 2# of the free-running mode relay connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism are disconnected, and the free-running mode is cancelled.

[0011] Further, by changing the output terminal voltage thresholds of the extension control voltmeter and the retraction control voltmeter, turn the action selection knob to the "retraction" gear and press the momentary action control button of the electric mechanism. The aircraft electric mechanism performs the retraction action. When the aircraft electric mechanism moves to the preset position corresponding to the output terminal voltage threshold of the retraction control voltmeter, it automatically positions and stops. Turn the action selection knob to the "extension" gear and press the momentary action control button of the electric mechanism. The aircraft electric mechanism performs the extension action. When the aircraft electric mechanism moves to the preset position corresponding to the output terminal voltage threshold of the extension control voltmeter, it automatically positions and stops.

[0012] The advantages of the present invention are as follows: A voltmeter with a measurement output is selected to detect the position voltage signal of the electric mechanism of the aircraft, which has high positioning accuracy and low cost. The "free running mode" is set, which can control the electric mechanism of the aircraft to run freely within the full stroke range, facilitating the user to use it during debugging, maintenance, etc. The user can set the voltage thresholds of the output terminals of the two voltmeters according to the predetermined rules (V2 = V1 + 0.1, 0V < V1 < 5V, 0V < V2 < 5V, V2 is the voltage threshold of the output terminal of the retraction control voltmeter, and V1 is the voltage threshold of the output terminal of the extension control voltmeter), so that the electric mechanism of the aircraft can automatically stop at any preset stop position within the full stroke. Two voltmeters with measurement outputs are used. When the electric mechanism of the aircraft extends from the minimum stroke to the maximum stroke, the normally closed contact of the intermediate relay connected to the output terminal of the extension control voltmeter is used to control the on-off of the extension action of the electric mechanism. When the electric mechanism of the aircraft retracts from the maximum stroke to the minimum stroke, the normally open contact of the intermediate relay connected to the output terminal of the retraction control voltmeter is used to control the on-off of the retraction action of the electric mechanism. Through on-site test measurement, by setting the voltage thresholds of the output terminals of the two voltmeters according to the above-mentioned predetermined rules, the positioning error caused by the hysteresis in the voltage measurement of the control system, the relay action, and the stop of the electric mechanism of the aircraft can be reduced (eliminated), so that the electric mechanism of the aircraft can accurately stop at the position corresponding to (V1 + V2) / 2 of the position voltage signal during the retraction and extension actions.

[0013] The following further describes this application in detail with reference to the accompanying drawings of the embodiments. Description of the Drawings

[0014] Figure 1 Schematic Diagram of the Box

[0015] Figure 2 Schematic Diagram of the Control Principle

[0016] Figure 3 Schematic Diagram of the Operation Panel

[0017] Figure 4 Schematic Diagram of the Use and Connection

[0018] Description of the numbers in the figure: 1. Discharge control voltmeter; 2. Measurement input terminal of the discharge control voltmeter; 3. Retraction control voltmeter; 4. Measurement input terminal of the retraction control voltmeter; 5. Action selection knob; 6. Normally open contact of action control relay 1#; 7. Normally open contact of action control relay 2#; 8. Normally open contact of the positioning control relay during retraction; 9. Normally open contact of free running mode relay 1#; 10. Normally closed contact of the positioning control relay during discharge; 11. Normally open contact of free running mode relay 2#; 12. Aircraft motor; 13. Power cable; 14. Retraction limit position; 15. Neutral position; 16. Discharge limit position; 17. Position signal output terminal of the aircraft motor mechanism; 18. Discharge action control input terminal of the aircraft motor mechanism; 19. Retraction action control input terminal of the aircraft motor mechanism; 20. Self-locking button for free running mode; 21. Free running mode relay; 22. Momentary action button for motor mechanism action control; 23. Indicator light for free running mode; 24. Motor mechanism action control relay; 25. Output terminal of the discharge control voltmeter; 26. Discharge positioning control relay; 27. Output terminal of the retraction control voltmeter; 28. Retraction positioning control relay; 30. Discharge; 31. Retraction; 32. Connection socket; 33. Power indicator light; 34. Positive terminal of the 24V power supply; 35. Negative terminal of the 24V power supply; 36. Operation panel; 37. Cabinet; 38. Connection plug; 39. Cable of the aircraft motor mechanism; 40. Aircraft motor mechanism; 41. Stop. Detailed implementation method

[0019] See the appendix Figures 1-4, An aircraft aileron neutral positioning device, comprising a box body 37, an operation panel 36, and an electrical component mounting plate. The electrical component mounting plate is fixed under the operation panel 36 inside the box body 37. The operation panel 36 is embedded with a release control voltmeter 1 and a retraction control voltmeter 3 connected in parallel, a 24V power supply positive terminal 34, a 24V power supply negative terminal 35, a power indicator 33, an action selection knob 5, a free running mode self-locking button 20, an electric mechanism action control momentary button 22, a free running mode indicator 23, and a connection socket 32. On the electrical component mounting plate, there are installed a free running mode relay 21, an electric mechanism action control relay 24, a positioning control relay 26 during release, and a positioning control relay 28 during retraction. Set the voltage threshold of the output terminals of the release control voltmeter 1 and the retraction control voltmeter 3 to the feedback voltage value of the neutral position 15 of the aircraft electric mechanism 40. Connect the device to the aircraft electric mechanism 40 through the aircraft electric mechanism cable 39. After connecting the power supply with the power cable 13, the power indicator 33 lights up. Turn the action selection knob 5 to the "release 30" gear position and press the electric mechanism action control momentary button 22. The release action control input terminal 18 of the aircraft electric mechanism is connected to a 24V high level. The aircraft electric mechanism 40 performs the release action and drives the aileron to swing. When the aileron swings to the neutral position 15, it automatically stops, completing the positioning of the neutral position 15. Turn the action selection knob 5 to the "retraction 31" gear position and press the electric mechanism action control momentary button 22. The retraction action control input terminal 19 of the aircraft electric mechanism is connected to a 24V high level. The aircraft electric mechanism 40 performs the retraction action and drives the aileron to swing. When the aileron swings to the neutral position 15, it automatically stops, completing the positioning of the neutral position 15. Turn the action selection knob 5 to the "stop 41" gear position and press the electric mechanism action control momentary button 22. The aircraft electric mechanism 40 is locked. When the "free running mode self-locking button 20" is pressed, the free running mode relay 21 is energized and connected. The device is in the free running mode and can control the aircraft electric mechanism 40 to move freely within the full stroke range. In this mode, the aileron will not automatically position and stop at the neutral position 15. By changing the voltage threshold of the output terminals of the release control voltmeter 1 and the retraction control voltmeter 3, the aircraft electric mechanism 40 can be controlled to automatically position and stop at any preset position.

[0020] The measurement input terminal 2 of the release control voltmeter and the measurement input terminal 4 of the retraction control voltmeter are connected to the position signal output terminal 17 of the aircraft electric mechanism. The positive terminal 34 of the 24V power supply and the negative terminal 35 of the 24V power supply are respectively connected to the positive and negative poles of the power supply. The power indicator lamp 33 is connected to the positive terminal 34 of the 24V power supply. The free running mode self-locking button 20 and the free running mode indicator lamp 23 are connected to the free running mode relay 21. The momentary button 22 for controlling the operation of the electric mechanism is connected to the relay 24 for controlling the operation of the electric mechanism. The release 30 and retraction 31 contacts of the action selection knob 5 are respectively connected to the release action control input terminal 18 of the aircraft electric mechanism and the retraction action control input terminal 19 of the aircraft electric mechanism, controlling the forward and reverse rotations of the aircraft electric mechanism 40. The connection socket 32 is connected to the connection plug 38 of the aircraft electric mechanism 40, reading the position feedback signal of the aircraft electric mechanism 40 through the aircraft electric mechanism cable 39, providing 24V power to the aircraft electric mechanism 40, and sending release and retraction action control signals to the aircraft electric mechanism 40.

[0021] The common points of the free running mode relay 21, the relay 24 for controlling the operation of the electric mechanism, the positioning control relay 26 during release, and the positioning control relay 28 during retraction are connected to 0V. The other end of the free running mode relay 21 is connected to the free running mode self-locking button 20. When the free running mode self-locking button 20 is pressed, the free running mode relay 21 is energized and connected, controlling the aircraft electric mechanism 40 to move freely within the full stroke range. The other end of the relay 24 for controlling the operation of the electric mechanism is connected to the momentary button 22 for controlling the operation of the electric mechanism. When the momentary button 22 for controlling the operation of the electric mechanism is pressed, the aircraft electric mechanism 40 performs release or retraction actions. The other end of the positioning control relay 26 during release is connected to the output terminal 25 of the release control voltmeter. When the output terminal 25 of the release control voltmeter outputs a 24V high level, the aircraft electric mechanism 40 can perform the release action. The other end of the positioning control relay 28 during retraction is connected to the output terminal 27 of the retraction control voltmeter. When the output terminal 27 of the retraction control voltmeter outputs a 24V high level, the aircraft electric mechanism 40 can perform the retraction action.

[0022] Turn the action selection knob 5 to the "Release 30" position, press the momentary button 22 for the electric mechanism action control. The electric mechanism action control relay 24 is energized and turned on. The normally open contact 7 of the action control relay 2# is closed. The aircraft electric mechanism 40 is at the retraction limit position 14. The output voltage of the output terminal 17 of the aircraft electric mechanism position signal is 0V. The voltage is less than the voltage threshold of the output terminal of the release control voltmeter. The output voltage of the output terminal 25 of the release control voltmeter is 0V. The positioning control relay 26 during release is not turned on. The normally closed contact 10 of the positioning control relay during release remains closed. The input terminal 18 for the release action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft motor 12 rotates to achieve the release action. The output voltage of the output terminal 17 of the aircraft electric mechanism position signal gradually increases from 0V. When the measurement input terminal 2 of the release control voltmeter detects that the output voltage of the output terminal 17 of the aircraft electric mechanism position signal is greater than the voltage threshold of the output terminal of the release control voltmeter, the output voltage of the output terminal 25 of the release control voltmeter quickly changes from 0V to 24V. The positioning control relay 26 during release is immediately turned on. The normally closed contact 10 of the positioning control relay during release is opened. The voltage connected to the input terminal 18 for the release action control of the aircraft electric mechanism changes from 24V high level to 0V. The release action of the aircraft electric mechanism 40 immediately stops at the neutral position 15.

[0023] Turn the action selection knob 5 to the "Retract 31" position, press the momentary button 22 for the electric mechanism action control. The electric mechanism action control relay 24 is energized and turned on. The normally open contact 6 of the action control relay 1# is closed. The aircraft electric mechanism 40 is at the release limit position 16. The output voltage of the output terminal 17 of the aircraft electric mechanism position signal is 5V. The voltage is greater than the voltage threshold of the output terminal of the retraction control voltmeter. The output voltage of the output terminal 27 of the retraction control voltmeter is 24V. The positioning control relay 28 during retraction is turned on. The normally open contact 8 of the positioning control relay during retraction remains closed. The input terminal 19 for the retraction action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft motor 12 rotates to achieve the retraction action. The output voltage of the output terminal 17 of the aircraft electric mechanism position signal gradually decreases from 5V. When the measurement input terminal 4 of the retraction control voltmeter detects that the output voltage of the output terminal 17 of the aircraft electric mechanism position signal is less than the voltage threshold of the output terminal of the retraction control voltmeter, the output voltage of the output terminal 27 of the retraction control voltmeter quickly changes from 24V to 0V. The positioning control relay 28 during retraction is immediately turned off. The normally open contact 8 of the positioning control relay during retraction is opened. The voltage connected to the input terminal 19 for the retraction action control of the aircraft electric mechanism changes from 24V high level to 0V. The retraction action of the aircraft electric mechanism 40 immediately stops at the neutral position 15.

[0024] The normally open contact 9 of the free-running mode relay and the normally open contact 11 of the free-running mode relay are respectively connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism 40, and are respectively connected in parallel with the normally closed contact 10 of the positioning control relay during extension and the normally open contact 8 of the positioning control relay during retraction. When the free-running mode self-locking button 20 is pressed, the button closes and self-locks, the free-running mode relay 21 is energized and turned on, the normally open contact 9 of the free-running mode relay and the normally open contact 11 of the free-running mode relay close, and the free-running mode indicator light 23 lights up, indicating to the user that the device is in the free-running mode. Turn the action selection knob 5 to the "extension 30" position, press the momentary button 22 for the electric mechanism action control, the electric mechanism action control relay 24 is energized and turned on, the normally open contact 7 of the action control relay 2 is turned on, the extension action control input terminal 18 of the aircraft electric mechanism is connected to the 24V high level, and the aircraft motor 12 rotates to achieve the extension action. Because the normally open contact 11 of the free-running mode relay in the extension control circuit is always in the closed state, when the aircraft electric mechanism 40 passes the neutral position 15, the extension action of the aircraft electric mechanism 40 will not stop even if the normally closed contact 10 of the positioning control relay during extension is disconnected, and it will automatically stop only after the aircraft electric mechanism 40 reaches the extension limit position 16. Turn the action selection knob 5 to the "retraction 31" position, press the momentary button 22 for the electric mechanism action control, the electric mechanism action control relay 24 is energized and turned on, the normally open contact 6 of the action control relay 1 is turned on, the retraction action control input terminal 19 of the aircraft electric mechanism is connected to the 24V high level, and the aircraft motor 12 rotates to achieve the retraction action. Because the normally open contact 9 of the free-running mode relay in the retraction control circuit is always in the closed state, when the aircraft electric mechanism 40 passes the neutral position 15, the retraction action of the aircraft electric mechanism 40 will not stop even if the normally open contact 8 of the positioning control relay during retraction is disconnected, and it will automatically stop only after the aircraft electric mechanism 40 reaches the retraction limit position 14. When the free-running mode self-locking button 20 is pressed again to disconnect the button, the free-running mode relay 21 is de-energized, the free-running mode indicator light 23 goes out, the normally open contact 9 of the free-running mode relay and the normally open contact 11 of the free-running mode relay connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism 40 are disconnected, and the free-running mode is cancelled.

[0025] Change the output terminal voltage thresholds of the retraction control voltmeter 1 and the extension control voltmeter 3. Turn the action selection knob 5 to the "Retraction 31" position, press the electric mechanism action control momentary button 22, and the aircraft electric mechanism 40 performs the retraction action. When the aircraft electric mechanism 40 moves to the preset position corresponding to the output terminal voltage threshold of the retraction control voltmeter 3, it automatically positions and stops. Turn the action selection knob 5 to the "Extension 30" position, press the electric mechanism action control momentary button 22, and the aircraft electric mechanism 40 performs the extension action. When the aircraft electric mechanism 40 moves to the preset position corresponding to the output terminal voltage threshold of the extension control voltmeter 1, it automatically positions and stops.

Claims

1. An aircraft aileron neutral positioning device, characterized in that It includes a box body, an operation panel, and an electrical component mounting board. The electrical component mounting board is fixed under the operation panel inside the box body. The operation panel is embedded with a release control voltmeter and a retraction control voltmeter connected in parallel, a 24V power supply positive terminal, a 24V power supply negative terminal, a power indicator light, an action selection knob, a free running mode self-locking button, an electric mechanism action control momentary button, a free running mode indicator light, and a connection socket. On the electrical component mounting board, there are installed a free running mode relay, an electric mechanism action control relay, a positioning control relay during release, and a positioning control relay during retraction. Set the voltage threshold of the output terminals of the release control voltmeter and the retraction control voltmeter to the feedback voltage value of the neutral position of the aircraft electric mechanism. Connect the device to the aircraft electric mechanism through the aircraft electric mechanism cable. After connecting the power supply with the power cable, the power indicator light is on. Turn the action selection knob to the "release" gear and press the electric mechanism action control momentary button. The input terminal for the release action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft electric mechanism performs the release action and drives the aileron to swing. When the aileron swings to the neutral position, it automatically stops, completing the neutral position positioning. Turn the action selection knob to the "retraction" gear and press the electric mechanism action control momentary button. The input terminal for the retraction action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft electric mechanism performs the retraction action and drives the aileron to swing. When the aileron swings to the neutral position, it automatically stops, completing the neutral position positioning. Turn the action selection knob to the "stop" gear and press the electric mechanism action control momentary button. The aircraft electric mechanism is locked. When the "free running mode self-locking button" is pressed, the free running mode relay is energized and connected. The device is in the free running mode, and the aircraft electric mechanism can be controlled to move freely within the full stroke range. In this mode, the aileron will not automatically position and stop at the neutral position. By changing the voltage threshold of the output terminals of the release control voltmeter and the retraction control voltmeter, the aircraft electric mechanism can be controlled to automatically position and stop at any preset position.

2. The neutral positioning device for the aileron of an aircraft according to claim 1, characterized in that The measurement input terminals of the release control voltmeter and the retraction control voltmeter are connected to the signal output terminal of the aircraft electric mechanism position signal conversion circuit. The 24V power supply positive terminal and the 24V power supply negative terminal are respectively connected to the positive and negative poles of the power supply. The power indicator light is connected to the 24V power supply positive terminal. The free running mode self-locking button and the free running mode indicator light are connected to the free running mode relay. The electric mechanism action control momentary button is connected to the electric mechanism action control relay. The release and retraction contacts of the action selection knob are respectively connected to the input terminal for the release action control of the aircraft electric mechanism and the input terminal for the retraction action control of the aircraft electric mechanism, controlling the forward and reverse rotation of the aircraft electric mechanism. The connection socket is connected to the connection plug of the aircraft electric mechanism, reading the position feedback signal of the aircraft electric mechanism, providing 24V power to the aircraft electric mechanism, and sending release and retraction action control signals to the aircraft electric mechanism.

3. The neutral positioning device for the aileron of an aircraft according to claim 1, wherein The common points of the free-running mode relay, the electric mechanism action control relay, the positioning control relay during release, and the positioning control relay during retraction are connected to 0V. The other end of the free-running mode relay is connected to the free-running mode self-locking button. When the free-running mode self-locking button is pressed, the free-running mode relay is energized and connected, controlling the electric mechanism of the aircraft to move freely within the full stroke range. The other end of the electric mechanism action control relay is connected to the electric mechanism action control momentary button. When the electric mechanism action control momentary button is pressed, the electric mechanism of the aircraft performs the release or retraction action. The other end of the positioning control relay during release is connected to the output terminal of the release control voltmeter. When the output terminal of the release control voltmeter outputs a high level of 24V, the electric mechanism of the aircraft can perform the release action. The other end of the positioning control relay during retraction is connected to the output terminal of the retraction control voltmeter. When the output terminal of the retraction control voltmeter outputs a high level of 24V, the electric mechanism of the aircraft can perform the retraction action.

4. The neutral positioning device for the aileron of an aircraft according to claim 1, wherein Turn the action selection knob to the "Release" position and press the electric mechanism action control momentary button. The electric mechanism action control relay is energized and connected, and the normally open contact 2# of the action control relay is connected. The electric mechanism of the aircraft is at the retraction limit position, and the output voltage of the output terminal of the electric mechanism position signal is 0V. The voltage is less than the voltage threshold of the output terminal of the release control voltmeter, and the output voltage of the output terminal of the release control voltmeter is 0V. The positioning control relay during release is not connected, and the normally closed contact of the relay remains connected. The input terminal of the release action control of the electric mechanism of the aircraft is connected to a high level of 24V, and the aircraft motor rotates to achieve the release action. The output voltage of the output terminal of the electric mechanism position signal of the aircraft gradually increases from 0V. When the input terminal of the release control voltmeter detects that the output voltage of the output terminal of the electric mechanism position signal of the aircraft is greater than the voltage threshold of the output terminal of the release control voltmeter, the output voltage of the output terminal of the release control voltmeter quickly changes from 0V to 24V, and the positioning control relay during release is immediately connected. The normally closed contact of the positioning control relay during release is disconnected, and the voltage connected to the input terminal of the release action control of the electric mechanism of the aircraft changes from a high level of 24V to 0V, and the release action of the electric mechanism of the aircraft immediately stops at the neutral position.

5. The aircraft aileron neutral positioning device according to claim 1, characterized in that Turn the action selection knob to the "Retract" position, press the momentary button for the electric mechanism action control. The relay for the electric mechanism action control is energized and turned on. The normally open contact of the action control relay No. 1 is turned on. The aircraft electric mechanism is in the extended limit position. The output voltage of the output terminal of the aircraft electric mechanism position signal is 5V, and the voltage is greater than the voltage threshold of the output terminal of the retract control voltmeter. The output voltage of the output terminal of the retract control voltmeter is 24V. When retracting, the positioning control relay is turned on, and the normally open contact of the positioning control relay when retracting remains in the on state. The input terminal for the retract action control of the aircraft electric mechanism is connected to a 24V high level. The aircraft motor rotates to achieve the retract action. The output voltage of the output terminal of the aircraft electric mechanism position signal gradually decreases. The input terminal for measuring the retract control voltmeter detects that the output voltage of the output terminal of the aircraft electric mechanism position signal is less than the voltage threshold of the output terminal of the retract control voltmeter. The output voltage of the output terminal of the retract control voltmeter quickly changes from 24V to 0V. The positioning control relay when retracting is immediately turned off, and the normally open contact of the positioning control relay when retracting is disconnected. The voltage connected to the input terminal for the retract action control of the aircraft electric mechanism changes from 24V high level to 0V. The retract action of the aircraft electric mechanism immediately stops at the neutral position.

6. The neutral positioning device for an aircraft aileron according to claim 1, characterized in that The normally open contact No. 1 of the free-running mode relay and the normally open contact No. 2 of the free-running mode relay are respectively connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism, and are respectively connected in parallel with the normally closed contact of the positioning control relay during extension and the normally open contact of the positioning control relay during retraction. When the free-running mode self-locking button is pressed, the button closes and self-locks, the free-running mode relay is energized and connected, the normally open contact No. 1 of the free-running mode relay and the normally open contact No. 2 of the free-running mode relay close, and the free-running mode indicator light is lit, prompting the user that the device is in the free-running mode. Turn the action selection knob to the "extension" position, press the momentary button for the action control of the electric mechanism, the action control relay of the electric mechanism is energized and connected, the normally open contact No. 2 of the action control relay is connected, the input terminal for the extension action control of the aircraft electric mechanism is connected to a 24V high level, and the aircraft electric motor rotates to achieve the extension action. Because the normally open contact No. 2 of the free-running mode relay connected to the extension control circuit is always in the closed state, when the aircraft electric mechanism passes the neutral position, the disconnection of the normally closed contact of the positioning control relay during extension will not stop the extension action of the aircraft electric mechanism, and it will only automatically stop after the aircraft electric mechanism reaches the extension limit position. Turn the action selection knob to the "retraction" position, press the momentary button for the action control of the electric mechanism, the action control relay of the electric mechanism is energized and connected, the normally open contact No. 1 of the action control relay is connected, the input terminal for the retraction action control of the aircraft electric mechanism is connected to a 24V high level, and the aircraft electric motor rotates to achieve the retraction action. Because the normally open contact No. 1 of the free-running mode relay connected to the retraction control circuit is always in the closed state, when the aircraft electric mechanism passes the neutral position, the disconnection of the normally open contact of the positioning control relay during retraction will not stop the retraction action of the aircraft electric mechanism, and it will only automatically stop after the aircraft electric mechanism reaches the retraction limit position. When the free-running mode self-locking button is pressed again to disconnect the button, the free-running mode relay is de-energized, the free-running mode indicator light goes out, and the normally open contact No. 1 of the free-running mode relay and the normally open contact No. 2 of the free-running mode relay connected to the control circuits for the extension and retraction actions of the aircraft electric mechanism are disconnected, and the free-running mode is cancelled.

7. The neutral positioning device for the aileron of an aircraft according to claim 1, wherein Change the output terminal voltage threshold of the extension control voltmeter and the retraction control voltmeter. Turn the action selection knob to the "retraction" gear, press the momentary button for the action control of the electric mechanism, and the aircraft electric mechanism performs the retraction action. When the aircraft electric mechanism moves to the preset position corresponding to the output terminal voltage threshold of the retraction control voltmeter, it automatically positions and stops. Turn the action selection knob to the "extension" gear, press the momentary button for the action control of the electric mechanism, and the aircraft electric mechanism performs the extension action. When the aircraft electric mechanism moves to the preset position corresponding to the output terminal voltage threshold of the extension control voltmeter, it automatically positions and stops.

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