Electric control brake valve for airplane

Abstract

An electronic control brake valve for an airplane comprises a valve body, a cavity, a motor assembly, pressure sensors, a Hall sensor and a central controller, the valve body is located at the front end of the cavity, the motor assembly is installed in the cavity and connected with the valve body, the number of the pressure sensors is three, the pressure sensors are installed on the valve body, and the Hall sensor is connected with the central controller. The number of the Hall sensors is three, the Hall sensors are installed at the positions, corresponding to the motor assembly, of the cavity, the pressure sensor and the Hall sensors are connected with the central controller, the brake valve and the flight control computer are in two-way communication including serial port communication and PWM communication, and the central controller has a fault feedback function. The three pressure sensors and the three Hall sensors are arranged to detect the pressure of the brake valve and the stroke of the motor respectively, so that the electric control system has the performance of redundancy control, the failure rate is effectively reduced, and the brake performance and safety are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft brake systems, and in particular to an electric-controlled brake valve for aircraft. Background Art

[0002] With the rapid development of modern transportation, the safety and efficiency of the braking system have become key factors in aircraft design and manufacturing. As an innovative technology, the electronic hydraulic braking system has gradually become an important development direction in the field of automotive braking systems.

[0003] The electronic hydraulic brake system is an important innovation in automobile braking technology in recent years. It combines the advantages of traditional hydraulic braking and advanced electronic control technology, and achieves precise control of brake pressure through an electronic control unit. However, the braking performance and safety of the electronically controlled brake valve can be further improved. Summary of the invention

[0004] In order to solve the problems mentioned in the above background technology, the present invention provides an electronically controlled brake valve for aircraft, which reduces the failure rate of the brake valve and improves the braking performance and safety of the brake valve.

[0005] The present invention discloses the following technical scheme: an electrically controlled brake valve for an aircraft, comprising a valve body, a cavity, a motor assembly, a pressure sensor, a Hall sensor and a central controller, wherein the valve body is located at the front end of the cavity, the motor assembly is installed in the cavity, the motor assembly is connected to the valve body, there are three pressure sensors, the pressure sensors are installed on the valve body, there are three Hall sensors, the Hall sensors are installed at corresponding positions between the cavity and the motor assembly, the pressure sensor and the Hall sensor are connected to the central controller, two-way communication is adopted between the brake valve and the flight control computer, including serial communication and PWM communication, and the central controller is provided with a fault feedback function.

[0006] Furthermore, the pressure sensors are installed on the valve body at 90° in a radial direction of the valve body.

[0007] Furthermore, the Hall sensor is installed along the length direction of the cavity.

[0008] Beneficial effect: Compared with the prior art, the electronically controlled brake valve for aircraft of the present invention respectively detects the pressure and motor stroke of the brake valve by setting three pressure sensors and three Hall sensors, and transmits the output voltage signal to the central controller. The central controller transmits the signal to the flight control computer. The flight control computer adjusts the brake valve according to the sensor data to ensure its normal operation, so that the electronic control system has the performance of redundancy control, ensuring that when one of the sensors fails, the other sensors can work normally, effectively reducing the failure rate and improving the braking performance and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 It is a schematic diagram of installing the pressure sensor of the present invention on the valve body; Figure 2 It is a schematic diagram of the installation of the Hall sensor of the present invention; Figure 3 It is a schematic diagram of the installation of the Hall sensor of the present invention; Figure 4 It is a working principle diagram of the present invention; In the figure: 1-valve body, 2-cavity, 3-motor assembly, 4-pressure sensor, 5-Hall sensor. DETAILED DESCRIPTION

[0010] like Figures 1 to 4 As shown, an electrically controlled brake valve for an aircraft comprises a valve body 1, a cavity 2, a motor assembly 3, a pressure sensor 4, a Hall sensor 5 and a central controller, wherein the valve body 1 is located at the front end of the cavity 2, the motor assembly 3 is installed in the cavity 2, the motor assembly 3 is connected to the valve body 1, and is used to provide hydraulic pressure to the valve body 1, there are three pressure sensors 4, the pressure sensors 4 are installed on the valve body 1, and are used to detect the hydraulic pressure of the brake valve, there are three Hall sensors 5, the Hall sensors 5 are installed at the corresponding positions of the cavity 2 and the motor assembly 3, and are used to detect the stroke of the motor assembly 3 and control the movement range of the motor assembly 3, the pressure sensor 4 and the Hall sensor 5 are connected to the central controller, and the central controller is used to receive sensor signals, and the central controller transmits the signals to the central controller. The signal is fed back to the flight control computer, and the pulse width modulation signal output by the flight control computer is transmitted to the brake valve to control the operation of the motor assembly 3, so that the valve body 1 outputs a stable hydraulic pressure proportional to the pulse width modulation signal. For example, if the pulse width modulation signal takes a value of 0~12V, the corresponding output pressure is 0~3Mpa. If the pulse width modulation signal takes 6V, the output pressure is 1.5Mpa. Two-way communication is adopted between the brake valve and the flight control computer, including serial communication and PWM communication. The flight control computer outputs a pulse width modulation signal to the brake valve, and the brake valve feeds back the feedback signal and the fault signal to the flight control computer through the serial communication. The central controller is provided with a fault feedback function. If the two signals of the sensor are the same and the other signal is different, the fault signal of the branch with different signals is transmitted to the flight control computer, which is beneficial to signal processing.

[0011] The pressure sensor 4 is installed on the valve body 1 at 90° in the radial direction of the valve body 1 to ensure accurate pressure detection data; the Hall sensor 5 is installed along the length direction of the cavity 2 to ensure accurate stroke of the motor assembly 3 in the detection cavity 2.

[0012] When in use, the central controller receives the voltage signal from the pressure sensor and the Hall sensor and transmits it to the flight control computer. The flight control computer records the hydraulic pressure of the valve body in real time, and transmits the pulse width modulation signal that controls the operation of the motor assembly to the brake valve based on the hydraulic pressure and the stroke data of the motor assembly. The control motor assembly outputs a stable hydraulic pressure proportional to the pulse width modulation signal, thereby improving the braking performance and safety of the brake valve. Since three pressure sensors and three Hall sensors are used, failure of the brake valve due to failure of one of the sensors can be avoided, effectively reducing the failure rate.

[0013] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An electrically controlled brake valve for an aircraft, comprising a valve body (1), a cavity (2), a motor assembly (3), a pressure sensor (4), a Hall sensor (5) and a central controller, characterized in that: The valve body (1) is located at the front end of the cavity (2); the motor assembly (3) is installed in the cavity (2); the motor assembly (3) is connected to the valve body (1); there are three pressure sensors (4) installed on the valve body (1); there are three Hall sensors (5) installed at positions corresponding to the cavity (2) and the motor assembly (3); the pressure sensor (4) and the Hall sensor (5) are connected to a central controller; two-way communication is adopted between the brake valve and the flight control computer, including serial communication and PWM communication; the central controller is provided with a fault feedback function.

2. The electrically controlled brake valve for aircraft according to claim 1, characterized in that: The pressure sensors (4) are installed on the valve body (1) in sequence at 90° along the radial direction of the valve body (1).

3. The electrically controlled brake valve for aircraft according to claim 1, characterized in that: The Hall sensor (5) is installed along the length direction of the cavity (2).

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