A logic method for ground non-hydraulic protection of servo steering gear

Abstract

The present application belongs to the technical field of aircraft servo actuator system servo control, and is a servo servo ground hydraulic protection logic method. The software connected to the servo is designed to execute the servo ground hydraulic protection logic. The software receives the aircraft status in real time. When the aircraft is in the ground state, all the hydraulic systems of the aircraft are in a pressure-free state, and the absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time, the servo ground hydraulic protection logic is executed; when it is judged that the aircraft is in a flight state, any hydraulic system of the aircraft is in a pressure state, and the absolute value of the drive coil control instruction is lower than a certain amplitude and lasts for a period of time, the servo ground hydraulic protection module is exited. The servo ground hydraulic protection module is exited, thereby avoiding the servo servo from drying up for a long time when the pressure of the hydraulic system on the aircraft is not established, thereby improving the product life and avoiding product damage.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft servo actuator system steering gear control, and in particular to a servo steering gear ground non-hydraulic protection logic method. Background Art

[0002] The servo actuation system is a system on an aircraft that controls the deflection angle of the control surface. It is used to control the flight direction of the aircraft and complete flight actions such as pitch, roll, and yaw. The servo actuation system uses a controller to control the servo steering gear to distribute hydraulic flow and drive the actuator cylinder to move. The controller collects the actuator cylinder position signal to complete the control closed loop. When the hydraulic pressure in the system is not established or is low, the steering gear works for a long time but the actuator cylinder cannot move to the controller command position, causing the steering gear to dry burn, reducing the product life and even causing damage.

[0003] Therefore, how to effectively protect the servo when there is no hydraulic protection and ensure the service life of the servo is a problem that needs to be solved. Summary of the invention

[0004] The purpose of this application is to provide a servo steering gear ground non-hydraulic protection logic method to solve the problem in the prior art that the steering gear is dry-burned when there is no hydraulic protection, resulting in the equipment being easily damaged.

[0005] The technical solution of the present application is: a servo steering gear ground non-hydraulic protection logic method, comprising:

[0006] Set up the software connected to the servo to determine the aircraft status. When the following conditions are met, the software executes the servo ground hydraulic protection logic:

[0007] a) The software determines that the aircraft is on the ground;

[0008] b) The software determines that all hydraulic systems of the aircraft are in a pressure-free state;

[0009] c) The absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time;

[0010] The aircraft status is judged again. When the following conditions are met, the software exits the servo ground hydraulic protection logic:

[0011] a) The software determines that the aircraft is in flight;

[0012] b) The software determines that any hydraulic system of the aircraft is under pressure;

[0013] c) The absolute value of the force drive coil control command is lower than a certain amplitude and lasts for a period of time, and the servo steering gear ground hydraulic protection module is exited.

[0014] Preferably, when the steering gear ground non-hydraulic protection logic is activated, the software limits the amplitude of the force driving coil driving instruction to a safe amplitude.

[0015] Preferably, the safety amplitude is 9.5A.

[0016] Preferably, when the servo steering gear ground hydraulic protection logic is executed, the absolute value of the force drive coil control instruction exceeds 1A and lasts for more than 90s.

[0017] Preferably, when the servo steering gear ground hydraulic protection logic is exited, the amplitude of the cancellation force drive coil drive instruction is limited to a safety amplitude.

[0018] Preferably, the absolute value of the force drive coil control instruction is lower than 0.5A and lasts for more than 5s, and the servo steering gear ground no hydraulic protection logic is exited.

[0019] The present application discloses a servo steering gear ground no hydraulic protection logic method, which executes the servo steering gear ground no hydraulic protection logic by designing software connected to the servo steering gear, wherein the software receives the aircraft status in real time, and executes the servo steering gear ground no hydraulic protection logic when the aircraft is on the ground, all hydraulic systems of the aircraft are in a pressure-free state, and the absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time; and exits the servo steering gear ground no hydraulic protection module when it is determined that the aircraft is in a flight state, any hydraulic system of the aircraft is in a pressured state, and the absolute value of the drive coil control instruction is lower than a certain amplitude and lasts for a period of time. The servo steering gear ground no hydraulic protection module is exited, and the control is simple and stable, and no manual operation is required. The system can automatically judge, thereby avoiding the situation where the servo steering gear is dry-burned for a long time when the pressure of the hydraulic system on the aircraft is not established, thereby improving the product life and avoiding product damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0021] Figure 1 This is a schematic diagram of the overall process of this application. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0023] A servo-actuator ground non-hydraulic protection logic method, such as Figure 1 As shown, assuming that the onboard system is a dual-redundancy hydraulic system, and a steering gear type direct-drive servo valve steering gear is used, the example includes the following steps:

[0024] Step S100, setting the software connected to the steering gear to judge the aircraft status, and when the following conditions are met, the software executes the steering gear ground hydraulic protection logic;

[0025] The servo steering gear ground no hydraulic protection logic method is implemented by the software in the controller. It is used to protect the steering gear's force drive coil and limit the maximum working current of the force drive coil when the aircraft is on the ground and all hydraulic systems are in alarm. The specific logic is as follows:

[0026] a) The software determines that the aircraft is on the ground;

[0027] b) The software determines that all hydraulic systems of the aircraft are in a pressure-free state, specifically, the software determines that both the first and second hydraulic systems of the aircraft are in a pressure-free state;

[0028] c) The absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time;

[0029] Preferably, when the servo steering gear ground hydraulic protection logic is executed, the absolute value of the force drive coil control instruction exceeds 1A and lasts for more than 90s.

[0030] Preferably, when the steering gear ground no hydraulic pressure protection logic is started, the software limits the amplitude of the driving coil driving instruction to a safe amplitude. Through this kind of steering gear ground no hydraulic pressure protection logic, the steering gear can be effectively protected.

[0031] Preferably, the safety amplitude is 9.5A.

[0032] Step S200, the aircraft status is judged again. When the following conditions are met, the software exits the servo ground hydraulic protection logic:

[0033] a) The software determines that the aircraft is in flight;

[0034] b) The software determines that any hydraulic system of the aircraft is in a pressurized state, specifically, the software determines that one or more of the aircraft's hydraulic systems I and II are in a pressurized state;

[0035] c) The absolute value of the force drive coil control command is lower than a certain amplitude and lasts for a period of time, and the servo steering gear ground hydraulic protection module is exited.

[0036] Preferably, when the servo steering gear ground hydraulic protection logic is exited, the amplitude of the cancellation force drive coil drive instruction is limited to a safety amplitude of 0.5A.

[0037] Preferably, the absolute value of the force drive coil control instruction is lower than 0.5A and lasts for more than 5s, and the servo steering gear ground no hydraulic protection logic is exited.

[0038] The present application executes the servo ground no-hydraulic protection logic by designing software connected to the servo. The software receives the status of the aircraft in real time. When the aircraft is on the ground, all hydraulic systems of the aircraft are in a pressure-free state, and the absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time, the servo ground no-hydraulic protection logic is executed; when it is judged that the aircraft is in a flight state, any hydraulic system of the aircraft is in a pressured state, and the absolute value of the drive coil control instruction is lower than a certain amplitude and lasts for a period of time, the servo ground no-hydraulic protection module is exited. The servo ground no-hydraulic protection module is exited. The control is simple and stable, and no manual operation is required. The system can automatically judge, avoiding the situation where the servo servo is dry-burned for a long time when the pressure of the hydraulic system on the aircraft is not established, thereby improving the product life and avoiding product damage.

[0039] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A servo steering gear ground non-hydraulic protection logic method, characterized in that: include: Set up the software connected to the servo to determine the aircraft status. When the following conditions are met, the software executes the servo ground hydraulic protection logic: a) The software determines that the aircraft is on the ground; b) The software determines that all hydraulic systems of the aircraft are in a pressure-free state; c) The absolute value of the force drive coil control instruction exceeds a certain amplitude and lasts for more than a period of time; The aircraft status is judged again. When the following conditions are met, the software exits the servo ground hydraulic protection logic: a) The software determines that the aircraft is in flight; b) The software determines that any hydraulic system of the aircraft is under pressure; c) The absolute value of the force drive coil control command is lower than a certain amplitude and lasts for a period of time, and the servo steering gear ground hydraulic protection module is exited.

2. The servo steering gear ground non-hydraulic protection logic method according to claim 1, characterized in that: When the servo ground hydraulic protection logic is activated, the software limits the amplitude of the force drive coil drive instruction to a safe amplitude.

3. The servo steering gear ground non-hydraulic protection logic method according to claim 2, characterized in that: The safety amplitude is 9.5A.

4. The servo steering gear ground non-hydraulic protection logic method according to claim 1, characterized in that: When the servo steering gear ground hydraulic protection logic is executed, the absolute value of the force drive coil control instruction exceeds 1A and lasts for more than 90s.

5. The servo steering gear ground non-hydraulic protection logic method according to claim 1, characterized in that: When the servo steering gear ground hydraulic protection logic is exited, the amplitude of the cancel force drive coil drive instruction is limited to the safety amplitude.

6. The servo steering engine ground non-hydraulic protection logic method as claimed in claim 1, characterized in that In: The absolute value of the force drive coil control instruction is less than 0.5A and lasts for more than 5s. Exit the servo actuator ground no hydraulic protection logic.

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