阅读说明：本技术 一种刹车系统 (brake system ) 是由 赵兴平 常凯 谢彦 秦成 苏静 于 2019-09-03 设计创作，主要内容包括：本申请属于飞机刹车控制技术领域,具体涉及一种刹车系统,包括：应急刹车阀,与液压源连接；液压源为应急刹车阀提供液压能源；刹车装置,与应急刹车阀连接；应急刹车手柄,与应急刹车阀电气连接,其转动时,应急刹车阀对应输出相应的液压压力,该液压压力驱动刹车装置与飞机机轮抵触,以此实现对飞机机轮的应急刹车。(the application belongs to the technical field of aircraft brake control, concretely relates to braking system, include: the emergency brake valve is connected with the hydraulic source; the hydraulic source provides hydraulic energy for the emergency brake valve; the brake device is connected with the emergency brake valve; the emergency brake handle is electrically connected with the emergency brake valve, when the emergency brake handle rotates, the emergency brake valve correspondingly outputs corresponding hydraulic pressure, and the hydraulic pressure drives the brake device to be abutted against airplane wheels, so that emergency braking of the airplane wheels is realized.)

1. A braking system, comprising:

The emergency brake valve (2) is connected with a hydraulic source; the hydraulic source provides hydraulic energy for the emergency brake valve (2);

The brake device (4) is connected with the emergency brake valve (2);

emergent brake lever (7), with emergent brake valve (2) electrical connection, during its rotation, emergent brake valve (2) correspond the corresponding hydraulic pressure of output, and this hydraulic pressure drive brake equipment (4) are contradicted with aircraft wheel (5), and it is right to so realize the emergent brake of aircraft wheel (5).

2. The braking system of claim 1,

The emergency brake device is characterized by further comprising an angular displacement sensor (8) connected with the emergency brake handle (7) and used for detecting the angular displacement of the emergency brake handle (7).

3. The braking system of claim 1,

Further comprising:

The shutdown brake valve (3) is connected with the brake device (4) and the hydraulic source; the hydraulic source provides hydraulic energy for the stop brake valve (3);

and the shutdown brake selection switch (9) is electrically connected with the shutdown brake valve (3), when the shutdown brake valve (3) is opened, the shutdown brake valve (3) outputs hydraulic pressure, and the hydraulic pressure drives the brake device (4) to be collided with the airplane wheel (5), so that the shutdown brake of the airplane wheel (5) is realized.

4. The braking system of claim 3,

The hydraulic source comprises a local energy component (1), is connected with the emergency brake valve (2) and the shutdown brake valve (3), and provides hydraulic energy for the emergency brake valve (2) and the shutdown brake valve (3).

5. The braking system of claim 4,

The hydraulic source also comprises a brake pressure accumulator (6) which is connected with the emergency brake valve (2) and the shutdown brake valve (3);

The brake system has:

In a normal working state, the local energy component (1) provides hydraulic energy for the emergency brake valve (2) and the shutdown brake valve (3);

and in a standby working state, the brake pressure accumulator (6) provides hydraulic energy for the emergency brake valve (2) and the shutdown brake valve (3).

6. an aircraft having a braking system as claimed in any one of claims 1 to 5.

Technical Field

the application belongs to the technical field of aircraft brake control, and particularly relates to a brake system.

background

currently, an airplane usually uses a mechanical push-pull steel cable to realize emergency/stop braking of the airplane, and the braking system can realize corresponding emergency/stop braking functions, which usually needs to arrange a longer push-pull steel cable, increases the weight of the airplane, greatly occupies limited precious space on the airplane, increases the tension of the airplane space, and is particularly significant when applied to a wider airplane.

The present application is made in view of the above drawbacks of the prior art.

Disclosure of Invention

it is an object of the present application to provide a braking system that overcomes or alleviates at least one of the disadvantages of the prior art.

The technical scheme of the application is as follows:

One aspect provides a braking system, including:

The emergency brake valve is connected with the hydraulic source; the hydraulic source provides hydraulic energy for the emergency brake valve;

The brake device is connected with the emergency brake valve;

the emergency brake handle is electrically connected with the emergency brake valve, when the emergency brake handle rotates, the emergency brake valve correspondingly outputs corresponding hydraulic pressure, and the hydraulic pressure drives the brake device to be abutted against airplane wheels, so that emergency braking of the airplane wheels is realized.

According to at least one embodiment of the application, the emergency brake system further comprises an angular displacement sensor connected with the emergency brake handle and used for detecting the angular displacement of the emergency brake handle.

According to at least one embodiment of the present application, further comprising:

the shutdown brake valve is connected with the brake device and the hydraulic source; the hydraulic source provides hydraulic energy for the shutdown brake valve;

the shutdown brake selection switch is electrically connected with the shutdown brake valve, when the shutdown brake selection switch is opened, the shutdown brake valve outputs hydraulic pressure, and the hydraulic pressure drives the brake device to be abutted against the airplane wheels, so that the shutdown brake of the airplane wheels is realized.

According to at least one embodiment of this application, the hydraulic pressure source includes local energy source subassembly, with emergent brake valve, stop brake valve and be connected, provides the hydraulic pressure energy for emergent brake valve, stop brake valve.

According to at least one embodiment of the application, the hydraulic source further comprises a brake pressure accumulator connected with the emergency brake valve and the shutdown brake valve;

the brake system has:

In a normal working state, the local energy component provides hydraulic energy for the emergency brake valve and the shutdown brake valve;

And in a standby working state, the brake pressure accumulator provides hydraulic energy for the emergency brake valve and the shutdown brake valve.

another aspect provides an aircraft having any of the above braking systems.

Drawings

FIG. 1 is a schematic view of a braking system according to an embodiment of the present disclosure;

wherein:

1-local energy component, 2-emergency brake valve, 3-stop brake valve, 4-brake device, 5-airplane wheel, 6-brake pressure accumulator, 7-emergency brake handle, 8-angular displacement sensor and 9-stop brake switch.

Detailed Description

the present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.

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

One aspect provides a braking system, including:

the emergency brake valve 2 is connected with a hydraulic source; the hydraulic source provides hydraulic energy for the emergency brake valve 2;

the brake device 4 is connected with the emergency brake valve 2;

the emergency brake handle 7 is electrically connected with the emergency brake valve 2, when the emergency brake valve 2 rotates, corresponding hydraulic pressure is correspondingly output by the emergency brake valve, and the hydraulic pressure drives the brake device 4 to be abutted against the airplane wheel 5, so that emergency braking of the airplane wheel 5 is realized.

For the brake system disclosed in the above embodiment, as those skilled in the art can easily understand, the emergency brake handle 7 may be installed in the cockpit of the aircraft, and the aircraft driver operates the emergency brake handle 7 to rotate, so as to correspondingly output level values with different amplitudes, so as to correspondingly enable the emergency brake valve 2 to correspondingly output hydraulic pressures with different magnitudes, for this reason, when the aircraft needs emergency braking, the driver operates the emergency brake handle 7 to rotate with a larger amplitude, i.e. to generate a larger angular displacement, and outputs a larger level value to act on the electrically controlled emergency brake valve 2, so as to enable the emergency brake valve 2 to output a larger hydraulic pressure, thereby implementing quick brake on the aircraft wheel 5; when the airplane needs to be slowly braked after landing, a driver operates the emergency brake handle 7 to rotate in a small amplitude, namely, a small angular displacement is generated, a small level value is output to act on the emergency brake valve 2, the emergency brake valve 2 outputs a small hydraulic pressure, and therefore slow braking of the airplane wheel 5 is achieved.

In the brake system, the emergency brake valve 2 is driven by an electrical control and hydraulic system, so that the hydraulic pressure output by the emergency brake valve 2 can be conveniently and quickly controlled and adjusted in a large range, and the hydraulic pressure output by the emergency brake valve 2 can be slowly and continuously changed, so that the braking process is relatively stable; in addition, compared with the existing braking mode of a mechanical push-pull steel cable, the braking system can greatly save the arrangement space on the airplane and reduce the weight of the airplane.

In some optional embodiments, an angular displacement sensor 8 is further included and is connected to the emergency brake handle 7 for detecting the angular displacement of the emergency brake handle 7.

with regard to the braking system disclosed in the above embodiment, it is easily understood by those skilled in the art that the angular displacement sensor 8 is used to detect the angular displacement of the emergency brake handle 7, that is, the rotation amplitude of the emergency brake handle 7 is detected, so that the magnitude of the output level value can be displayed to a certain extent, and the accurate operation by the driver is facilitated.

In some optional embodiments, further comprising:

a stop brake valve 3 connected with the brake device 4 and the hydraulic source; the hydraulic source provides hydraulic energy for the stop brake valve 3;

the stop brake selection switch 9 is electrically connected with the stop brake valve 3, when the stop brake selection switch is opened, the stop brake valve 3 outputs hydraulic pressure, and the hydraulic pressure drives the brake device 4 to be abutted against the airplane wheel 5, so that the stop brake of the airplane wheel 5 is realized.

With regard to the braking system disclosed in the above embodiment, it is easily understood by those skilled in the art that when the parking brake selection switch 9 is turned on, the parking brake valve 3 is controlled to output hydraulic pressure, the hydraulic pressure drives the braking device 4 to park and brake the airplane wheel 5, and the size of the hydraulic pressure is sufficient to drive the braking device 4 to park and brake the airplane wheel 5; when the parking brake selection switch 9 is turned off, the brake device 4 releases the parking brake state to the airplane wheel 5.

In the braking system, the stop braking valve 3 is driven by an electrical control and hydraulic system, can be conveniently and quickly controlled by opening and closing the stop braking selection switch 9, and can still keep the output of hydraulic pressure after the power failure of the airplane, so that the braking device 4 keeps the stop braking state of the airplane wheel 5; in addition, compared with the existing braking mode of a mechanical push-pull steel cable, the braking system can greatly save the arrangement space on the airplane and reduce the weight of the airplane.

in some optional embodiments, the hydraulic source comprises a local energy source assembly 1, which is connected with the emergency brake valve 2 and the stop brake valve 3 to provide hydraulic energy for the emergency brake valve 2 and the stop brake valve 3.

in the above embodiments, the local energy source assembly 1 may comprise, within known limits: the hydraulic brake system comprises an oil tank, an electric pump, a controller and an integrated hydraulic module (comprising a temperature sensor, a pressure sensor, a safety valve, an oil return one-way valve, an oil return filter, an air release safety valve, a bypass valve, an oil adding and oil discharging self-sealing joint and the like), and the hydraulic module provides hydraulic energy for the emergency brake valve 2 and the stop brake valve 3 and can complete functions of power-on self-checking, ground maintenance, oil adding and oil discharging and the like.

In some optional embodiments, the hydraulic pressure source further comprises a brake accumulator 6 connected with the emergency brake valve 2 and the stop brake valve 3;

The brake system has:

in a normal working state, the local energy component 1 provides hydraulic energy for the emergency brake valve 2 and the stop brake valve 3;

And in a standby working state, the brake pressure accumulator 6 provides hydraulic energy for the emergency brake valve 2 and the stop brake valve 3.

Another aspect provides an aircraft having any of the above braking systems.

So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.