Inhibition method and device for balancing mechanism of fly-by-wire flight control system

Abstract

The invention provides a suppression method and device for a trimming mechanism of a fly-by-wire flight control system. The method comprises the following steps: judging the current working state of the flight control system; according to the redundancy signal output by the displacement sensor, whether the cabin control system is in a non-disengagement state or not is judged; judging whether the transverse trimming position and the longitudinal trimming position are at zero positions or not; the flight control module sends out a balancing suppression enable signal, power supplies of the transverse balancing mechanism and the longitudinal balancing mechanism are cut off, and balancing suppression is successfully started; and after the balancing suppression is successfully started, the aileron balancing switch and the elevator balancing switch are toggled, and the corresponding transverse balancing mechanism and longitudinal balancing mechanism do not act. The method is used for solving the problem that normal functions of a fly-by-wire flight control system are affected by misoperation of a cabin artificial trimming system.

Description

Technical Field

[0001] The present invention relates to the technical field of flight control systems, and in particular to a method for suppressing a trim mechanism of an electric fly-by-wire flight control system and a device for suppressing a trim mechanism of an electric fly-by-wire flight control system using the method. Background Art

[0002] With the development of technology, large aircraft flight control systems usually use fly-by-wire flight control systems. The normal control law uses the "stick command-overload" control law, and has control law functions such as automatic trim, bank hold, and high-speed protection, which significantly improves the flight quality of the aircraft. The cockpit control system has a manual trim function. If the flight control system is in a normal state, if the pilot manipulates the trim switch so that the trim is not in the neutral position, it will affect the normal "stick command-overload" control law function and automatic trim, bank hold and other control law functions, thereby reducing the flight quality and affecting flight safety. Summary of the invention

[0003] In view of the requirements of the control law of the fly-by-wire flight control system on the manual balancing function of the cabin, the present invention provides a method and a device for suppressing the balancing mechanism of the fly-by-wire flight control system, which solves the problem that the normal function of the fly-by-wire flight control system may be affected by the misoperation of the manual balancing system of the cabin.

[0004] The present invention achieves the above-mentioned purpose through the following technical solutions:

[0005] A method for inhibiting a trim mechanism of an electric fly-by-wire flight control system, the method comprising the following steps:

[0006] Step S1, determine the current working state of the flight control system. If it is in a normal working state, execute step S2;

[0007] Step S2, judging whether the cockpit control system is in a non-disconnected state according to the redundancy signal output by the displacement sensor, and if so, executing step S3;

[0008] Step S3, judging whether the lateral trim position and the longitudinal trim position are at zero position according to the collected trim position signals of the lateral trim mechanism and the longitudinal trim mechanism, and if so, executing step S4;

[0009] Step S4, the flight control module sends a trim inhibition enable signal;

[0010] Step S5, after receiving the trim inhibition signal, the conventional power distribution box before the cabin cuts off the power supply of the transverse trim mechanism and the longitudinal trim mechanism. At this time, the trim position is displayed at zero, and the trim inhibition is successfully started;

[0011] Step S6, when the trim inhibition is successfully started, the aileron trim switch and the elevator trim switch are toggled, and the corresponding lateral trim mechanism and longitudinal trim mechanism are not actuated;

[0012] According to a method for suppressing a trim mechanism of an electric flight control system provided by the present invention, in step S3, it is determined whether the lateral and longitudinal trim positions are both at zero position based on the collected trim position signals of the lateral and longitudinal trim mechanisms. If both the lateral and longitudinal trim positions are at zero position, step S4 is continued to be executed; if the lateral or longitudinal trim position is not at zero position, a trim suppression disabling signal is issued, and the user is waited to operate the lateral and longitudinal trim switches to return the lateral and longitudinal trim positions to zero position, and after completion, the execution of step S3 is returned to.

[0013] According to a method for suppressing the trim mechanism of an electric-by-wire flight control system provided by the present invention, in step S1, after determining that the current flight control system is in an abnormal working state, a trim suppression disabling signal is sent through the flight control module to turn off the trim suppression function, that is, the trim suppression function does not need to be executed at present, and the lateral and longitudinal trim mechanisms are allowed to be operated normally through the trim switch.

[0014] According to a method for suppressing a trim mechanism of an electric fly-by-wire flight control system provided by the present invention, when the flight control system is in an abnormal state, if the fault is restored, the flight control system returns to a normal working mode;

[0015] If the judgment results of step S2 and step S3 are still "yes", the flight control module sends a trim inhibition enable signal to start the trim inhibition function;

[0016] If the judgment result of step S2 is "yes" and the judgment result of step S3 is "no", a trim inhibition disabling signal is sent through the flight control module to turn off the trim inhibition function; a "longitudinal trim is not in neutral position" or "lateral trim is not in neutral position" alert level warning is provided, and the longitudinal trim mechanism and the lateral trim mechanism of the cockpit control system are controlled by the trim switch;

[0017] If the longitudinal trim mechanism and the lateral trim mechanism are simultaneously returned to zero position through operation, and the judgment condition of step S4 is met at this time, the trim inhibition function is started.

[0018] According to a method for suppressing a trim mechanism of a fly-by-wire flight control system provided by the present invention, if the number of trim position signals generated by the trim mechanism is greater than or equal to 1, the multi-channel trim position signals are comprehensively judged through a flight control module to determine the cabin trim position;

[0019] The displacement sensor is used to monitor the disengagement status of the cockpit control system. The number of effective displacement sensor signals is greater than or equal to 2. The multi-channel displacement sensor signals are used to comprehensively judge the disengagement status of the cockpit control system.

[0020] A redundant flight control module design is adopted, that is, the number of flight control modules is greater than or equal to 1. When a flight control module FCM fails, other flight control modules can take over its work to ensure the continuity and stability of the flight control system.

[0021] According to a method for inhibiting a trim mechanism of an electric fly-by-wire flight control system provided by the present invention, the step of judging whether a lateral trim position and a longitudinal trim position are at zero position comprises:

[0022] Static calibration: When the aircraft is stationary, the trim position is adjusted so that the trim position feedback outputs a specific signal value, that is, the standard value at zero position. At the same time, the neutral position state of the cockpit control system can be checked through the neutral pin.

[0023] Use high-resolution and high-sensitivity displacement sensors to collect status signals of the cockpit control system and trim mechanism;

[0024] By reading the signal value output by the displacement sensor and comparing it with the standard value at zero position, if the difference between the two is within the allowable range, it can be determined that the balancing position is at zero position.

[0025] It can be seen that the present invention can realize effective lateral and longitudinal trim inhibition functions, and avoid the influence of lateral and longitudinal trim not being in the neutral position state on the normal control law of the flight control system. In order to prevent the main flight control system from cutting off the power supply of the trim mechanism when the longitudinal trim mechanism and the lateral trim mechanism are not in the neutral position, that is, starting the trim inhibition function, the main flight control system determines whether the two mechanisms are already in the neutral position through the longitudinal trim mechanism position signal and the lateral trim mechanism position signal forwarded by the RDIU; the present invention only starts the trim inhibition function when both mechanisms are in the neutral position range, the main flight control system is in the normal working mode, and the lateral and longitudinal cockpit control mechanisms are not in the disengaged state after the jamming fault.

[0026] Furthermore, the present invention ensures that accidental operation of the trim mechanism due to misoperation or system failure is avoided during critical stages (such as takeoff, landing, etc.) by judging the working status of the flight control system and the status of the cockpit operating system, thereby reducing instability and potential dangers during flight.

[0027] Furthermore, the present invention monitors the trim position signal to ensure that trim suppression is allowed only when the trim position is at zero, thereby effectively preventing abnormal aircraft attitude caused by non-zero trim and improving the pilot's operating accuracy and the controllability of the aircraft.

[0028] Furthermore, the present invention utilizes redundant signals for status judgment, thereby increasing the redundancy of the system. Even if some sensors fail, the normal operation of the system can be maintained through data from other normally operating sensors, thereby improving the reliability and fault tolerance of the entire system.

[0029] Furthermore, once the trim inhibition is successfully initiated in the present invention, the pilot cannot control the trim mechanism by toggling the trim switch, and there is no need to worry about unexpected actions. At this time, the automatic trim function is initiated in the normal control law of the flight control module.

[0030] Furthermore, the present invention avoids the influence of non-command movement of the balancing mechanism by cutting off the power supply for controlling the balancing mechanism.

[0031] A suppression device for a trim mechanism of an electric fly-by-wire flight control system, comprising:

[0032] The cockpit control system is used to be driven by the trim mechanism to generate mechanical motion, and to provide the pilot with control to generate mechanical motion and output displacement instructions;

[0033] The trim mechanism, including the lateral trim mechanism and the longitudinal trim mechanism, provides an artificial trim function for the cockpit control system to offset the stick force of the cockpit control system and feedback the current trim position;

[0034] Displacement sensors are installed in the cockpit control system to convert the mechanical movement of the cockpit control system into electrical signals. They have multiple redundancies. Even if a displacement sensor fails, other sensors can still work normally.

[0035] A flight control module, used for receiving trim position data, determining the disengagement state of the cockpit control system according to the redundancy signal of the displacement sensor, and generating a trim inhibition enable signal or a trim inhibition disable signal according to the flight control system state and the cockpit disengagement state, so as to control the power supply of the trim mechanism;

[0036] Actuator control electronics ACE, used to receive the trim inhibition enable signal or trim inhibition disable signal sent by the flight control module, and further transmit the signal to the conventional power distribution box in front of the cabin to perform power control operations;

[0037] The conventional power distribution box in front of the cabin controls the connection or disconnection of the power supply circuit of the longitudinal trim mechanism according to the received trim inhibition enable signal or trim inhibition disable signal; and then the power on / off of the power supply circuit of the longitudinal trim mechanism controls the power on / off of the power supply circuit of the transverse trim mechanism.

[0038] According to the present invention, a suppression device for the trim mechanism of an electric fly-by-wire flight control system is provided, when multiple displacement sensors are used to simultaneously collect displacement information of a cockpit control system, the collected signals are filtered to remove noise and interference;

[0039] Perform time synchronization to ensure that the signals output by multiple displacement sensors are synchronized in time;

[0040] Compare the output signals of multiple displacement sensors to check whether the differences between them are within the allowable range;

[0041] Redundancy check is performed using the redundant signal. If the signal does not exceed the tolerance compared with other output signals, the signal is considered reliable.

[0042] According to the result of redundancy check and the mechanical characteristics of the cockpit control system, determine whether the cockpit control system is in a non-disconnected state;

[0043] If the output signals of the multiple displacement sensors are consistent and meet the characteristics of the non-disconnected state of the cockpit control system, it can be determined that the cockpit control system is in the non-disconnected state.

[0044] It can be seen that the device of the present invention realizes the trim inhibition function by identifying the working mode of the main flight control system, the disengagement state of the cockpit, whether the lateral and longitudinal trim positions are at zero position, etc. When specific conditions are met, the device will cut off the power supply of the lateral and longitudinal trim mechanisms, prevent the trim mechanisms from operating, and thus protect the normal control law of the flight control system from being disturbed. The device works in coordination with components such as displacement sensors, remote data collectors, remote data concentrators, flight control modules, actuator control electronics, and conventional power distribution boxes in front of the cabin to ensure flight safety.

[0045] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 The present invention is a flow chart of an embodiment of a method for suppressing a trim mechanism of an electric-by-wire flight control system.

[0047] Figure 2 The present invention is a schematic flow chart of trim inhibition enabling in an embodiment of a method for inhibiting a trim mechanism of a fly-by-wire flight control system.

[0048] Figure 3 The present invention is a schematic diagram of an embodiment of a suppression device for a trim mechanism of a fly-by-wire flight control system. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0050] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0051] See also Figure 1 and Figure 2 The present invention provides a method for suppressing a trim mechanism of an electric fly-by-wire flight control system, the method comprising the following steps:

[0052] Step S1, determine the current working state of the flight control system. If it is in a normal working state, execute step S2;

[0053] Step S2, judging whether the cockpit control system is in a non-disconnected state according to the redundancy signal output by the displacement sensor, and if so, executing step S3;

[0054] Step S3, judging whether the lateral trim position and the longitudinal trim position are at zero position according to the collected trim position signals of the lateral trim mechanism and the longitudinal trim mechanism, and if so, executing step S4;

[0055] Step S4: if the judgments of steps S1, S2 and S3 are all yes, the flight control module sends a trim inhibition enable signal;

[0056] Step S5, after receiving the trim inhibition signal, the conventional power distribution box before the cabin cuts off the power supply of the transverse trim mechanism and the longitudinal trim mechanism. At this time, the signal displayed by the trim position is also not output, indicating that the trim position is at zero position, and the trim inhibition is successfully started;

[0057] Step S6, when the trim inhibition is successfully started, the aileron trim switch and the elevator trim switch are toggled, and the corresponding lateral trim mechanism and longitudinal trim mechanism do not operate.

[0058] Among them, the longitudinal trim mechanism and lateral trim mechanism of the cockpit control system are controlled on demand through the trim switch.

[0059] Wherein, when the judgment result of step S1 is no, the FCM sends a trim inhibition disabling signal, and the trim inhibition function is released;

[0060] Among them, when the judgment result of step S2 is no, the FCM sends a trim inhibition disabling signal, the trim inhibition function is released, and because the disengagement fault is a latching fault, it cannot be recovered in the air.

[0061] In step S3, it is determined whether the lateral and longitudinal trim positions are both at zero position based on the collected trim position signals of the lateral and longitudinal trim mechanisms. If both the lateral and longitudinal trim positions are at zero position, step S4 is continued to be executed; if the lateral or longitudinal trim position is not at zero position, a trim inhibition disable signal is issued, and the user is waited to operate the lateral and longitudinal trim switches to return the lateral and longitudinal trim positions to zero position. After completion, the process returns to step S3.

[0062] In the above step S1, when it is determined that the current flight control system is in an abnormal working state, a trim inhibition disabling signal is sent through the flight control module to turn off the trim inhibition function, that is, the trim inhibition function does not need to be executed at present, and the lateral and longitudinal trim mechanisms are allowed to operate normally through the trim switch.

[0063] In the above step S1, the current working state of the flight control system is determined; if it is in normal mode, step S2 is continued to be executed; if it is in abnormal mode, a trim inhibition disabling signal is issued and step S1 is restarted after waiting for the upgrade mode.

[0064] In the above step S2, the cockpit command displacement sensor signal is collected, and it is determined whether the cockpit control system is in a disengaged state. If it is in a disengaged state, the changed state is latched, and a trim inhibition disable signal is issued, and the process ends; if it is in a non-disengaged state, step S3 is continued.

[0065] When the flight control system is in an abnormal state, if the fault is restored, the flight control system returns to the normal working mode;

[0066] If the judgment results of the above steps S2 and S3 are still "yes", a trim inhibition enable signal is sent through the flight control module to start the trim inhibition function;

[0067] If the judgment result of the above step S2 is "yes" and the judgment result of the above step S3 is "yes", a trim inhibition disabling signal is sent through the flight control module to turn off the trim inhibition function; a "longitudinal trim is not in neutral position" or "lateral trim is not in neutral position" alert level warning is provided, and the longitudinal trim mechanism and the lateral trim mechanism of the cockpit control system are controlled by the trim switch;

[0068] If the longitudinal trim mechanism and the lateral trim mechanism are simultaneously returned to zero position through operation, and the judgment condition of the above step S4 is met at this time, the trim inhibition function is started.

[0069] In this embodiment, if the number of trim position signals generated by the trim mechanism is greater than or equal to 1, the multi-channel trim position signals are comprehensively judged by the flight control module for the cabin trim position;

[0070] The displacement sensor is used to monitor the disengagement status of the cockpit control system. The number of effective displacement sensor signals is greater than or equal to 2. The multi-channel displacement sensor signals are used to comprehensively judge the disengagement status of the cockpit control system.

[0071] A redundant FCM design is adopted, that is, the number of flight control modules is greater than or equal to 1. When a flight control module FCM fails, other flight control modules can take over its work to ensure the continuity and stability of the flight control system.

[0072] In this embodiment, determining whether the lateral trim position and the longitudinal trim position are at zero position includes:

[0073] Static calibration: When the aircraft is stationary, the trim position is adjusted so that the trim position feedback outputs a specific signal value, that is, the standard value at zero position. At the same time, the neutral position state of the cockpit control system can be checked through the neutral pin.

[0074] Use high-resolution and high-sensitivity displacement sensors to collect status signals of the cockpit control system and trim mechanism;

[0075] By reading the signal value output by the displacement sensor and comparing it with the standard value at zero position, if the difference between the two is within the allowable range, it can be determined that the balancing position is at zero position.

[0076] In this embodiment, when the trim inhibition is successfully activated, no matter how the pilot toggles the aileron trim switch or the elevator trim switch, the corresponding lateral trim mechanism and longitudinal trim mechanism will not have any action. This ensures that under certain conditions, the trim state of the aircraft will not be accidentally changed.

[0077] Although the trim mechanism will not respond to the operation of the conventional trim switch during the trim inhibition period, the longitudinal trim mechanism and lateral trim mechanism of the cockpit control system can still be operated as needed through special trim switches (for example, in emergency situations or specific maintenance tasks). This design ensures flight safety while providing the necessary flexibility.

[0078] In practical applications, first, the system determines whether the flight control system is in an abnormal working state by monitoring various sensors and parameters (such as flight attitude, speed, acceleration, control surface position, etc.). For example, a fault detection and isolation algorithm is provided, which can identify anomalies or faults in the system and make judgments based on them.

[0079] Once it is determined that the flight control system is in an abnormal working state, the flight control module will respond immediately and send a trim inhibition disable signal through the internal logic or communication interface. The purpose of this signal is to tell other components in the system (such as actuator control electronic ACE, front conventional power distribution box, etc.) that there is no need to execute the trim inhibition function at present, that is, to allow the pilot to perform normal operation of the lateral and longitudinal trim mechanisms through the trim switch.

[0080] After the trim inhibition function is released, it is possible to confirm whether the trim mechanism has acted as expected by observing the indicators in the cockpit (such as the trim position indicator) and the flight response of the aircraft.

[0081] When confirming that the flight control system fault has been restored, this can be done by monitoring various system parameters and performance indicators, including but not limited to sensor data, control surface position feedback, system response speed, etc. Once it is confirmed that the system has been restored to stability and the performance meets the requirements, the pilot can prepare for the upgrade operation.

[0082] Among them, the mold lifting operation involves the following steps:

[0083] Execute the upgrade command: When the flight control module FCM receives the upgrade command, the FCM will trigger a series of operations within the system, including reloading control parameters, restoring control logic, etc. and switching to normal working mode.

[0084] In summary, the present invention can realize effective lateral and longitudinal trim inhibition functions, and avoid the influence of lateral and longitudinal trim not being in the neutral position state on the normal control law of the flight control system. In order to avoid the main flight control system cutting off the power supply of the trim mechanism when the longitudinal trim mechanism and the lateral trim mechanism are not in the neutral position, that is, starting the trim inhibition function, the main flight control system determines whether the two mechanisms are already in the neutral position through the longitudinal trim mechanism position signal and the lateral trim mechanism position signal forwarded by the RDIU; the present invention only starts the trim inhibition function when both mechanisms are in the neutral position range, the main flight control system is in the normal working mode, and the lateral and longitudinal cockpit control mechanisms are not in the disengaged state after the jamming fault.

[0085] Furthermore, the present invention ensures that accidental operation of the trim mechanism due to misoperation or system failure is avoided during critical stages (such as takeoff, landing, etc.) by judging the working status of the flight control system and the status of the cockpit operating system, thereby reducing instability and potential dangers during flight.

[0086] Furthermore, the present invention monitors the trim position signal to ensure that trim suppression is allowed only when the trim position is at zero, thereby effectively preventing abnormal aircraft attitude caused by non-zero trim and improving the pilot's operating accuracy and the controllability of the aircraft.

[0087] Furthermore, the present invention utilizes redundant signals for status judgment, thereby increasing the redundancy of the system. Even if some sensors fail, the normal operation of the system can be maintained through data from other normally operating sensors, thereby improving the reliability and fault tolerance of the entire system.

[0088] Furthermore, once the trim inhibition is successfully initiated, the pilot cannot control the trim mechanism by toggling the trim switch, and there is no need to worry about unexpected actions. At this time, the automatic trim function is activated in the normal control law of the flight control module, which simplifies the operating process and improves flight efficiency.

[0089] Furthermore, the present invention avoids unnecessary energy consumption by cutting off the power supply of the control balancing mechanism, thereby extending the service life of the equipment and reducing maintenance and replacement costs.

[0090] Embodiment of a suppression device for a trim mechanism of a fly-by-wire flight control system

[0091] like Figure 3 As shown, this embodiment provides a suppression device for a trim mechanism of an electric fly-by-wire flight control system, comprising:

[0092] The cockpit control system is used to be driven by the trim mechanism to generate mechanical motion, and to provide the pilot with control to generate mechanical motion and output displacement instructions;

[0093] The trim mechanism, including the lateral trim mechanism and the longitudinal trim mechanism, provides an artificial trim function for the cockpit control system to offset the stick force of the cockpit control system and feedback the current trim position;

[0094] Displacement sensors are installed in the cockpit control system to convert the mechanical movement of the cockpit control system into electrical signals. They have multiple redundancies. Even if a displacement sensor fails, other sensors can still work normally.

[0095] A remote data feedback device, used to collect feedback signals from the trim mechanism and forward them to the flight control module;

[0096] A flight control module is used to receive trim position data from a remote data feedback device, determine the disengagement state of a cockpit control system according to a redundancy signal of a displacement sensor, and generate a trim inhibition enable signal or a trim inhibition disable signal according to a flight control system state and a cockpit disengagement state, so as to control the power supply of a trim mechanism;

[0097] Actuator control electronics ACE, used to receive the trim inhibition enable signal or trim inhibition disable signal sent by the flight control module, and further transmit the signal to the conventional power distribution box in front of the cabin to perform power control operations;

[0098] The conventional power distribution box in front of the cabin controls the connection or disconnection of the power supply circuit of the longitudinal trim mechanism according to the received trim inhibition enable signal or trim inhibition disable signal; and then the power on / off of the power supply circuit of the longitudinal trim mechanism controls the power on / off of the power supply circuit of the transverse trim mechanism.

[0099] In this embodiment, when multiple displacement sensors are used to simultaneously collect displacement information of the cockpit control system, the collected signals are filtered to remove noise and interference;

[0100] Perform time synchronization to ensure that the signals output by multiple displacement sensors are synchronized in time;

[0101] Compare the output signals of multiple displacement sensors to check whether the differences between them are within the allowable range;

[0102] Redundancy check is performed using the redundant signal. If the signal does not exceed the tolerance compared with other output signals, the signal is considered reliable.

[0103] According to the result of redundancy check and the mechanical characteristics of the cockpit control system, determine whether the cockpit control system is in a non-disconnected state;

[0104] If the output signals of the multiple displacement sensors are consistent and meet the characteristics of the non-disconnected state of the cockpit control system, it can be determined that the cockpit control system is in the non-disconnected state.

[0105] Specifically, the lateral / longitudinal trim mechanism in the cockpit control system is connected to the onboard emergency busbar through the front solid-state distribution box and the trim switch. Under normal circumstances, the front solid-state distribution box will receive the trim inhibition command and cut off the power supply to the lateral / longitudinal trim mechanism. At this time, the user cannot control the lateral / longitudinal trim mechanism by operating the lateral / longitudinal trim switch;

[0106] The lateral / longitudinal trim mechanism converts the current trim position into an electrical signal and transmits the signal to the FCM; the FCM then determines whether to produce a trim inhibition or non-inhibition signal based on the current working mode and cockpit disconnection status, and transmits it to the ACE, which then transmits it to the solid-state distribution box in front of the cabin to control the on / off of the lateral / longitudinal trim mechanism power supply circuit.

[0107] In this embodiment, the remote data feedback device includes:

[0108] Remote data collector RDC, used to collect feedback signals from the trim mechanism and send them to the remote data concentrator RDIU;

[0109] The remote data concentrator RDIU is used to receive data collected by the remote data collector RDC and forward it to the flight control module.

[0110] Among them, the flight control module is used to identify the working mode of the main flight control system and whether it is in a normal working state.

[0111] Among them, the flight control module is used to identify the redundant signal output by the displacement sensor and determine whether the cockpit is in a non-disconnected state.

[0112] The flight control module is used to determine the collected signals of the trim positions of the lateral and longitudinal trim mechanisms, and to determine whether the lateral and longitudinal trim positions are at zero position.

[0113] When the flight control module identifies that the judgments of steps S1, S2 and S3 are all "yes", it sends a trim inhibition enable signal.

[0114] When the flight control module identifies that the judgment result of step S1 is "no", it sends a trim inhibition disabling signal.

[0115] When the flight control module identifies that the judgment result of step S2 is "no", it sends a trim inhibition disabling signal.

[0116] When the flight control module identifies that the judgment result of step S3 is "no", it sends a trim inhibition disabling signal.

[0117] When the flight control module identifies that the judgment result of step S4 is "yes", it sends a trim inhibition enable signal.

[0118] In summary, the device of the present invention realizes the trim inhibition function by identifying the working mode of the main flight control system, the disengagement state of the cockpit, whether the lateral and longitudinal trim positions are at zero position, etc. When specific conditions are met, the device will cut off the power supply of the lateral and longitudinal trim mechanisms, prevent the trim mechanisms from operating, and thus protect the normal control law of the flight control system from being disturbed. The device works in coordination with components such as displacement sensors, remote data collectors, remote data concentrators, flight control modules, actuator control electronics, and conventional power distribution boxes in front of the cabin to ensure flight safety.

[0119] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0120] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A method for inhibiting a trim mechanism of a fly-by-wire flight control system, characterized in that: The method comprises the following steps: Step S1, determine the current working state of the flight control system. If it is in a normal working state, execute step S2; Step S2, judging whether the cockpit control system is in a non-disconnected state according to the redundancy signal output by the displacement sensor, and if so, executing step S3; Step S3, judging whether the lateral trim position and the longitudinal trim position are at zero position according to the collected trim position signals of the lateral trim mechanism and the longitudinal trim mechanism, and if so, executing step S4; Step S4, the flight control module sends a trim inhibition enable signal; Step S5, after receiving the trim inhibition signal, the conventional power distribution box before the cabin cuts off the power supply of the transverse trim mechanism and the longitudinal trim mechanism. At this time, the trim position is displayed at zero, and the trim inhibition is successfully started; Step S6, when the trim inhibition is successfully started, the aileron trim switch and the elevator trim switch are toggled, and the corresponding lateral trim mechanism and longitudinal trim mechanism do not operate.

2. The method according to claim 1, characterized in that: In step S3, it is determined whether the lateral and longitudinal trim positions are both at zero position based on the collected trim position signals of the lateral and longitudinal trim mechanisms. If both the lateral and longitudinal trim positions are at zero position, step S4 is continued to be executed; if the lateral or longitudinal trim position is not at zero position, a trim inhibition disable signal is issued, and the user is waited to operate the lateral and longitudinal trim switches to return the lateral and longitudinal trim positions to zero position. After completion, the process returns to step S3.

3. The method according to claim 1, characterized in that: In step S1, when it is determined that the current flight control system is in an abnormal working state, a trim inhibition disabling signal is sent through the flight control module to turn off the trim inhibition function, that is, the trim inhibition function does not need to be executed at present, and the lateral and longitudinal trim mechanisms are allowed to operate normally through the trim switch.

4. The method according to claim 1, characterized in that: When the flight control system is in an abnormal state, if the fault is restored, the flight control system returns to the normal working mode; If the judgment results of step S2 and step S3 are still "yes", the flight control module sends a trim inhibition enable signal to start the trim inhibition function; If the judgment result of step S2 is "yes" and the judgment result of step S3 is "no", a trim inhibition disabling signal is sent through the flight control module to turn off the trim inhibition function; a "longitudinal trim is not in neutral position" or "lateral trim is not in neutral position" alert level warning is provided, and the longitudinal trim mechanism and the lateral trim mechanism of the cockpit control system are controlled by the trim switch; If the longitudinal trim mechanism and the lateral trim mechanism are simultaneously returned to zero position through operation, and the judgment condition of step S4 is met at this time, the trim inhibition function is started.

5. The method according to claim 1, characterized in that: If the number of trim position signals generated by the trim mechanism is greater than or equal to 1, the multi-channel trim position signals are comprehensively judged by the flight control module to determine the cabin trim position; The displacement sensor is used to monitor the disengagement status of the cockpit control system. The number of effective displacement sensor signals is greater than or equal to 2. The multi-channel displacement sensor signals are used to comprehensively judge the disengagement status of the cockpit control system. A redundant flight control module design is adopted, that is, the number of flight control modules is greater than or equal to 1. When a flight control module fails, other flight control modules can take over its work to ensure the continuity and stability of the flight control system.

6. The method according to claim 1, characterized in that The determining whether the lateral trim position and the longitudinal trim position are at zero position comprises: Static calibration: When the aircraft is stationary, the trim position is adjusted so that the trim position feedback outputs a specific signal value, that is, the standard value at zero position. At the same time, the neutral position state of the cockpit control system can be checked through the neutral pin. Use high-resolution and high-sensitivity displacement sensors to collect status signals of the cockpit control system and trim mechanism; By reading the signal value output by the displacement sensor and comparing it with the standard value at zero position, if the difference between the two is within the allowable range, it can be determined that the balancing position is at zero position.

7. A suppression device for a trim mechanism of a fly-by-wire flight control system, characterized in that: include: The cockpit control system is used to be driven by the trim mechanism to generate mechanical motion and provide the pilot with control to generate mechanical motion and output displacement instructions; The trim mechanism, including the lateral trim mechanism and the longitudinal trim mechanism, provides an artificial trim function for the cockpit control system to offset the stick force of the cockpit control system and feedback the current trim position; Displacement sensors are installed in the cockpit control system to convert the mechanical movement of the cockpit control system into electrical signals. They have multiple redundancies. Even if a displacement sensor fails, other sensors can still work normally. The flight control module is used to receive the trim position data, determine the disengagement state of the cockpit control system according to the redundancy signal of the displacement sensor, and generate a trim inhibition enable signal or a trim inhibition disable signal according to the flight control system state and the cockpit disengagement state to control the power supply of the trim mechanism.

8. The device according to claim 7, characterized in that: When using multiple displacement sensors to simultaneously collect displacement information of the cockpit control system, filter the collected signals to remove noise and interference; Perform time synchronization to ensure that the signals output by multiple displacement sensors are synchronized in time; Compare the output signals of multiple displacement sensors to check whether the differences between them are within the allowable range; Redundancy check is performed using the redundant signal. If the signal does not exceed the tolerance compared with other output signals, the signal is considered reliable. According to the result of redundancy check and the mechanical characteristics of the cockpit control system, determine whether the cockpit control system is in a non-disconnected state; If the output signals of the multiple displacement sensors are consistent and meet the characteristics of the non-disconnected state of the cockpit control system, it can be determined that the cockpit control system is in the non-disconnected state.

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