Dual-redundancy electronic control brake valve of controller
By employing a dual-redundancy controller design, parallel installation of dual information computing boards, and redundant communication, the instability of existing electronically controlled brake valves in the event of a single-point failure is resolved, resulting in higher braking performance and safety.
Patent Information
- Application Number
- CN202511670402.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-14
- Publication Date
- 2026-01-09
AI Technical Summary
The braking performance and safety of existing electronically controlled brake valves need to be improved, especially the system stability is insufficient when the controller fails at a single point.
The controller adopts a dual-redundancy design, which includes two information computing boards installed in parallel. Redundant control is achieved through serial port and PWM communication, ensuring that the other board can take over when one information computing board fails, thereby improving system stability and safety.
It improves braking performance and safety, reduces the failure rate, and ensures that the system can still function normally in the event of a single board failure.
Smart Images
Figure CN121291353A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft braking system technology, and in particular to an electronically controlled brake valve with dual-redundant controller. Background Technology
[0002] With the rapid development of modern transportation, the safety and efficiency of braking systems have become key factors in aircraft design and manufacturing. Electro-hydraulic braking systems, as an innovative technology, have gradually become an important development direction in the field of automotive braking systems. Electro-hydraulic braking systems represent a significant innovation in automotive braking technology in recent years. They combine the advantages of traditional hydraulic braking with advanced electronic control technology, achieving precise control of braking pressure through an electronic control unit. However, the braking performance and safety of currently electronically controlled brake valves can still be further improved. Summary of the Invention
[0003] To address the problems mentioned in the background section, the present invention provides an electronically controlled brake valve with dual redundancy in the controller.
[0004] This invention discloses the following technical solution: a dual-redundant electronically controlled brake valve, comprising a brake valve body, a support, an electric mechanism, a pressure sensor module, and a controller assembly. The brake valve body is located at the front end of the support, the electric mechanism is installed inside the support, and the electric mechanism is connected to the brake valve body to drive the brake valve body to work. The pressure sensor module is installed on the brake valve body to collect the hydraulic pressure signal of the brake valve, and the pressure sensor module is connected to the controller assembly. The controller assembly is installed at the top of the support, and the controller assembly includes a power information processing board and two information computing boards. The controller assembly is communicatively connected to a flight control computer.
[0005] Furthermore, the controller component and the flight control computer use bidirectional communication, including serial port and PWM communication. The serial port transmits the hydraulic pressure signal collected by the pressure sensor module to the flight control computer, and the PWM communication transmits the control signal of the flight control computer to the controller component.
[0006] Furthermore, the pressure sensor module is mounted on the brake valve body at a 90° angle along the radial direction to ensure accurate detection of pressure data.
[0007] Furthermore, the two information computing boards are installed side by side on one side of the power information processing board. The main function of the power information processing board is to receive control commands sent from the receiver and transmit them to the information computing control board, identify the fault signal of the information computing control board, and transfer the control function to the other information computing control board, so that the product can work normally when one information computing control board fails.
[0008] Beneficial effects: Compared with the prior art, the electronically controlled brake valve of the present invention improves product stability by setting a dual-redundancy controller. The controller assembly is equipped with two information computing boards, so that if one information computing board fails, the other information computing board will control the valve. The flight control computer adjusts the brake valve according to sensor data to ensure normal operation during the service life period, effectively reducing the failure rate and improving braking performance and safety. Attached Figure Description
[0009] Figure 1 This is a schematic diagram of the installation of the power information processing board and the information computing board of the present invention; Figure 2 This is a schematic diagram illustrating the working principle of the present invention; In the diagram: 1-Power information processing board, 2-Information calculation board. Detailed Implementation
[0010] like Figure 1 and Figure 2 As shown, a dual-redundant electronically controlled brake valve includes a brake valve body, a support, an electric mechanism, a pressure sensor module, and a controller assembly. The brake valve body is located at the front end of the support. The electric mechanism is installed inside the support and is connected to the brake valve body to drive the brake valve body. The pressure sensor module is installed on the brake valve body to collect the hydraulic pressure signal of the brake valve. The pressure sensor module is connected to the controller assembly, which is installed at the top of the support. The controller assembly includes a power information processing board 1 and two information computing boards 2. The controller assembly is communicatively connected to a flight control computer.
[0011] The controller assembly and the flight control computer communicate bidirectionally, including serial port and PWM communication. The serial port transmits the hydraulic pressure signal collected by the pressure sensor module to the flight control computer, while the PWM communication transmits the control signal from the flight control computer to the controller assembly. The pressure sensor module is mounted on the brake valve body at a 90° angle along the radial direction to ensure accurate pressure detection data. The two information processing boards 2 are mounted side by side on one side of the power information processing board 1. The main function of the power information processing board 1 is to receive control commands sent from the receiver and transmit them to the information processing control board. It also identifies fault signals from the information processing control board and transfers the control function to the other information processing control board, enabling the product to work normally when one information processing control board fails.
[0012] During use, the controller component receives control signals output by the flight control computer. The controller component controls the electric mechanism to work according to the control signals and outputs pressure corresponding to the control signals of the flight control computer. The controller has a self-test function. After the product is powered on, it performs a self-test on the information calculation board 2. If one of the information calculation boards 2 fails, it automatically switches to the other information calculation work and feeds back the fault information to the flight control computer. After the power information processing board 1 recognizes the self-test fault signal of the information calculation board 2, it starts the other information calculation board 2 to work. If both information calculation boards 2 are normal, one of the information calculation boards 2 is used. The unused information calculation board 2 is not powered on during periods of non-use to ensure the lifespan of electronic components.
[0013] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.
Claims
1. A dual-redundant electronically controlled brake valve, characterized in that: The system includes a brake valve body, a support, an electric mechanism, a pressure sensor module, and a controller assembly. The brake valve body is located at the front end of the support. The electric mechanism is installed inside the support and is connected to the brake valve body to drive the brake valve body to work. The pressure sensor module is installed on the brake valve body to collect the hydraulic pressure signal of the brake valve. The pressure sensor module is connected to the controller assembly, which is installed at the top of the support. The controller assembly includes a power information processing board (1) and two information calculation boards (2). The controller assembly is communicatively connected to the flight control computer.
2. The electronically controlled brake valve with dual redundancy according to claim 1, characterized in that: The controller component and the flight control computer communicate bidirectionally, including serial port and PWM communication. The serial port transmits the hydraulic pressure signal collected by the pressure sensor module to the flight control computer, and the PWM communication transmits the control signal of the flight control computer to the controller component.
3. The electronically controlled brake valve with dual redundancy according to claim 1, characterized in that: The pressure sensor module is mounted on the brake valve body at a 90° angle along the radial direction of the brake valve body.
4. The electronically controlled brake valve with dual redundancy according to claim 1, characterized in that: The two information computing boards (2) are installed side by side on one side of the power information processing board (1).