阅读说明：本技术 一种刹车减速控制系统 (Brake deceleration control system ) 是由 安宇晗 杨飞 于 2019-10-30 设计创作，主要内容包括：本申请属于刹车系统总体设计领域,特别涉及一种刹车减速控制系统。包括：指令传感器、刹车控制器、液压阀组、机轮刹车装置以及轮速传感器,所述刹车控制器与所述指令传感器电连接,所述液压阀组与所述刹车控制器电连接,所述机轮刹车装置与所述液压阀组机械连接,所述轮速传感器安装在机轮上,并与所述刹车控制器电连接；所述刹车减速控制系统具有刹车模式和防滑模式。本申请的刹车减速控制系统,实现了飞机层面的闭环控制,有效解决刹车系统与刹车装置匹配性问题,能适应不同结构形式的机轮刹车装置。(The application belongs to the field of overall design of brake systems, and particularly relates to a brake deceleration control system. The method comprises the following steps: the airplane wheel brake device is mechanically connected with the hydraulic valve group, and the wheel speed sensor is mounted on an airplane wheel and electrically connected with the brake controller; the brake deceleration control system has a braking mode and an anti-skid mode. The application discloses brake speed reduction control system has realized the closed-loop control of aircraft aspect, effectively solves braking system and brake equipment matching nature problem, can adapt to the wheel brake equipment of different structural style.)

1. A brake deceleration control system, comprising: the airplane wheel brake device is mechanically connected with the hydraulic valve group, and the wheel speed sensor is mounted on an airplane wheel and electrically connected with the brake controller; the brake deceleration control system has a braking mode and an anti-skid mode, wherein,

in the case of the braking mode, the brake is operated,

the command sensor converts the brake operating force into a command signal and sends the command signal to the brake controller, the brake controller generates a control signal according to the command signal and a preset brake control rate, the hydraulic valve group generates a first brake signal according to the control signal, and the airplane wheel brake device brakes according to the first brake signal;

in the non-slip mode of operation,

the wheel speed sensor acquires a wheel speed signal of the wheel and sends the wheel speed signal to the brake controller, the brake controller generates an anti-skid signal according to the wheel speed signal, the hydraulic valve group generates a second brake signal according to the anti-skid signal, and the wheel brake device brakes according to the second brake signal.

2. The brake deceleration control system of claim 1, wherein the brake control rate is a correspondence between the command signal and a deceleration rate of the aircraft.

3. The brake deceleration control system according to claim 1, wherein a driver applies the brake operating force to the command sensor through a foot pedal.

4. The brake deceleration control system according to claim 1, wherein the hydraulic valve sets comprise two sets, and the wheel braking device comprises prismatic shutters for coupling signals of the two sets of hydraulic valve sets.

Technical Field

The application belongs to the field of overall design of brake systems, and particularly relates to a brake deceleration control system.

Background

The airplane wheel brake system generally adopts a control mode of instructing the brake pressure, namely, the brake instruction input and the brake pressure of a brake device have a certain proportional relation, and the brake pressure is controlled by adjusting the brake instruction input, so that the aim of airplane sliding brake is fulfilled.

At present, the airplane wheel brake system is an open-loop system or a brake pressure closed-loop system, when the command input of the system is fixed, the brake pressure is also a fixed value and cannot be dynamically adjusted along with the change of external conditions, and the adaptability to the interference of the external conditions and the like is poor. At present, the brake material mainly comprises a carbon-carbon composite brake material, and the carbon-ceramic composite brake material is applied in a small range. The two brake materials have certain defects in actual use, the performance attenuation of the carbon-carbon composite brake material is overlarge during wet braking, and the average braking torque (or braking distance) is reduced to about 30% when the average braking torque (or braking distance) is serious; when the two brake materials are used for braking with high kinetic energy (stopping taking off), the brake torque can be attenuated to different degrees, and the brake pressure cannot be dynamically adjusted, so that the brake distance is too long, and the risk that the airplane rushes out of a runway exists. And the torque characteristic of the braking device has large dispersion, which can reach about +/-25% at most, so that the matching performance of the braking system and the braking device is poor, which is expressed that the braking system is hard or soft, and the pilot has poor operation experience.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The present application is directed to a brake deceleration control system that solves at least one of the problems of the prior art.

The technical scheme of the application is as follows:

a brake deceleration control system comprising: the airplane wheel brake device is mechanically connected with the hydraulic valve group, and the wheel speed sensor is mounted on an airplane wheel and electrically connected with the brake controller; the brake deceleration control system has a braking mode and an anti-skid mode, wherein,

in the case of the braking mode, the brake is operated,

the command sensor converts the brake operating force into a command signal and sends the command signal to the brake controller, the brake controller generates a control signal according to the command signal and a preset brake control rate, the hydraulic valve group generates a first brake signal according to the control signal, and the airplane wheel brake device brakes according to the first brake signal;

in the non-slip mode of operation,

the wheel speed sensor acquires a wheel speed signal of the wheel and sends the wheel speed signal to the brake controller, the brake controller generates an anti-skid signal according to the wheel speed signal, the hydraulic valve group generates a second brake signal according to the anti-skid signal, and the wheel brake device brakes according to the second brake signal.

Optionally, the braking control rate is a corresponding relationship between the command signal and a deceleration rate of the aircraft.

Alternatively, the driver applies the brake operating force to the command sensor through a foot pedal.

Optionally, the hydraulic valve banks include two sets, and the wheel braking device includes prismatic valves for coupling signals of the two sets of hydraulic valve banks.

The invention has at least the following beneficial technical effects:

the application discloses brake speed reduction control system has realized the closed-loop control of aircraft aspect, effectively solves braking system and brake equipment matching nature problem, can adapt to the wheel brake equipment of different structural style.

Drawings

FIG. 1 is a schematic illustration of a brake deceleration control system according to an embodiment of the present application;

FIG. 2 is a schematic illustration of a braking mode of the brake deceleration control system according to an embodiment of the present application;

FIG. 3 is a brake control rate diagram of the brake deceleration control system according to one embodiment of the subject application;

FIG. 4 is a schematic view of a brake wheel braking arrangement of the brake deceleration control system of one embodiment of the present application;

FIG. 5 is a schematic view of a brake wheel braking arrangement of the brake deceleration control system of another embodiment of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1 to 5.

The application provides a brake speed reduction control system, includes: the device comprises a command sensor, a brake controller, a hydraulic valve group, an airplane wheel brake device and a wheel speed sensor.

Specifically, brake controller is connected with the command sensor electricity, and hydraulic pressure valves is connected with brake controller electricity, and wheel brake equipment is connected with hydraulic pressure valves machinery, and the wheel speed sensor is installed on the wheel to be connected with brake controller electricity.

The brake deceleration control system has a brake mode and an anti-skid mode, when in the brake mode, the command sensor converts brake operating force into a command signal and sends the command signal to the brake controller, the brake controller generates a control signal according to the command signal and a preset brake control rate, the hydraulic valve group generates a first brake signal according to the control signal, and the airplane wheel brake device brakes according to the first brake signal; when the anti-skidding mode is used, the wheel speed sensor acquires wheel speed signals of the wheel and sends the wheel speed signals to the brake controller, the brake controller generates anti-skidding signals according to the wheel speed signals, the hydraulic valve group generates second brake signals according to the anti-skidding signals, and the wheel brake device brakes according to the second brake signals. The connection form of the wheel brake device and the brake deceleration control system can comprise two types, in one embodiment of the application, the hydraulic valve groups comprise two groups, the wheel brake device is mechanically connected with the wheel brake device after coupling signals of the two groups of hydraulic valve groups through the prismatic valve, in another embodiment, the two groups of hydraulic valve groups and the wheel brake device can be directly and respectively mechanically connected, and the design and use requirements of the brake system on the aspects of framework, control logic, channel switching and the like can be met under different brake device connection forms.

In one embodiment of the present application, the brakes are in the form of pedal actuation, which provides for differential braking. A driver applies brake operating force to the command sensor through the pedal plate, the command sensor outputs a voltage signal to the brake controller, the brake controller adjusts input current of the hydraulic valve group according to a preset brake control rate, and the hydraulic valve group outputs brake pressure corresponding to the input current, so that the airplane brakes according to the deceleration rate expected by the pilot. The command signal of the command sensor and the deceleration rate of the aircraft satisfy a certain corresponding relationship, which is set in advance, as shown in fig. 3, and the actual corresponding relationship is subject to the user's requirement.

The application discloses brake deceleration control system, when the brake operating force of system input is fixed, the brake pressure of hydraulic pressure valves output is not the fixed value, and brake pressure is along with external condition's change dynamic adjustment, guarantees that the aircraft deceleration rate satisfies the requirement of input command. If the aircraft cannot reach the expected deceleration rate under the current conditions (water accumulation, thin ice and other runway pavements, or large kinetic energy landing and the like), the brake deceleration control system can set the optimal deceleration rate allowed by the current pavements to brake.

In an embodiment of this application, wheel speed sensor response wheel speed, send the wheel speed signal for brake controller, brake controller resolves the wheel speed signal of input, if the brake pressure that the driver applyed makes the produced brake torque of wheel be higher than the ground binding torque between wheel and the runway at that time, the wheel produces deep slipping (locking), brake controller output antiskid signal, the brake pressure who makes hydraulic valve group output reduces, wheel angular velocity resumes, deep slipping removes.

According to the brake deceleration control system, the control process is a process of continuously adjusting the brake-loose brake pressure, so that the tire abrasion is reduced, the tire burst is prevented, and the ground sliding safety of the airplane is ensured.

The application of the brake deceleration control system is under the premise of ensuring that the deceleration rate of the airplane is unchanged, the brake pressure is controlled according to the external conditions, the dynamic adjustment of the brake torque is realized, the binding force on the ground is fully utilized, and the brake distance is effectively shortened. The problem of insufficient braking torque of an open-loop braking or braking pressure closed-loop system under unfavorable braking conditions can be effectively solved. The airplane can effectively control the braking torque, shorten the braking distance and reduce the risk of the airplane rushing out of the runway under the conditions of high humidity environment and high kinetic energy landing. The system has strong compatibility, can effectively overcome the problem that the braking system is hard or soft due to large dispersion of the moment characteristics of the braking device, and improves the operation experience of pilots.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.