CN105836112B - A kind of type aircraft hydraulic brake system - Google Patents
A kind of type aircraft hydraulic brake system Download PDFInfo
- Publication number
- CN105836112B CN105836112B CN201610384666.0A CN201610384666A CN105836112B CN 105836112 B CN105836112 B CN 105836112B CN 201610384666 A CN201610384666 A CN 201610384666A CN 105836112 B CN105836112 B CN 105836112B
- Authority
- CN
- China
- Prior art keywords
- brake
- hose
- lock
- cock
- sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T11/00—Transmitting braking action from initiating means to ultimate brake actuator without power assistance or drive or where such assistance or drive is irrelevant
- B60T11/10—Transmitting braking action from initiating means to ultimate brake actuator without power assistance or drive or where such assistance or drive is irrelevant transmitting by fluid means, e.g. hydraulic
- B60T11/24—Single initiating means operating on more than one circuit, e.g. dual circuits
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/171—Detecting parameters used in the regulation; Measuring values used in the regulation
Abstract
The present invention discloses a kind of type aircraft hydraulic brake system, for no hydraulic power source brake system, including brake sensor, the first hose, the second hose, lock-up cock, conduit and brake gear, brake sensor is attached separately to the both sides of airplane tread device, is driven by brake pedal；Brake sensor is connected by the first hose with lock-up cock one end pipe nipple；Lock-up cock other end pipe nipple is sequentially connected by conduit and the second hose, brake gear.Second hose is installed on close to brake gear one end；According to brake pedal stroke, brake sensor exports the brake pressure that is corresponding to it, and is transmitted to brake gear, realizes aircraft taxi brake or turning.It manipulates brake pedal and establishes pressure, then manipulate lock-up cock, keep the pressure between brake gear and lock-up cock, realize aircraft shutdown brake.Type aircraft hydraulic brake system disclosed by the invention has the characteristics that light-weight, installation space is small, maintenance is simple, reliability is high.
Description
Technical field
The invention belongs to aircraft brake control technology fields, and in particular to a kind of type aircraft hydraulic brake system.
Background technology
Brake system is the system of relationship Flight Safety, and in flight course, brake system, which ensures, to be taken off
With the safety in ground taxi stage when landing, such as brake system cisco unity malfunction, then aircraft safety and flight are directly influenced
The life security of member.Hydraulic brake system includes brake control section and for laminate section（That is hydraulic power source）, for pressure pressure generally by
The hydraulic pump of power drives provides on aircraft engine or machine, once aircraft engine or hydraulic pump failure, brake system is by nothing
Method works.Therefore, at least one pressure source and 1 backup pressure source be generally set in plane hydraulic system, brake system weight,
Installation space, maintenance workload all increase therewith.
Invention content
In order to solve the above technical problems, the present invention provides a kind of type aircraft hydraulic brake system, set using no hydraulic power source
Meter, eliminates the attachmentes such as pressure accumulation bottle or hydraulic pump, surge flask, improves the reliability of system, saved installation space, subtracted significantly
Light system weight；Brake system pressure, without consuming aircraft engine or other energy again, alleviates hair by manually establishing
The load of motivation.
The technical issues of in order to solve the present invention, the present invention is achieved by the following technical solutions：A kind of type aircraft
Hydraulic brake system for no hydraulic power source brake system, is opened including brake sensor 1, the first hose 21, the second hose 22, locking
It closes 3, conduit 4 and brake gear 5, the brake sensor 1 is attached separately to the both sides of airplane tread device, by the brake on pedal
Pedal-driven；The brake sensor 1 is connected by first hose 21 with one end pipe nipple of the lock-up cock 3；Institute
The other end pipe nipple for stating lock-up cock 3 is sequentially connected by the conduit 4 and the second hose 22, brake gear 5；Described second
Hose 22 is installed on close to 5 one end of brake gear；During aircraft taxi, when manipulating left and right both sides brake pedal, brake system
System one closed system of internal composition, according to the stroke of brake pedal, the brake sensor 1 exports the brake pressure that is corresponding to it
Power is transmitted to brake gear 5 by the first hose 21, lock-up cock 3,4 and second hose 22 of conduit, realizes that aircraft taxi is stopped
Vehicle；By controlling the size of left and right both sides brake pressure, aircraft taxi brake or turning are realized；The lock-up cock 3 is installed on
On cockpit floor, manipulate brake pedal brake system is made to establish pressure, then manipulate the lock-up cock 3, keep brake gear 5 with
Pressure between lock-up cock 3 realizes aircraft shutdown brake.
Preferably, the 1 inside setting shoe cream room of brake sensor, eliminates special fuel reserve tank, it is empty to have saved installation
Between, alleviate system weight.
Compared with prior art, the advantageous effect that obtains of the present invention is：
A kind of type aircraft hydraulic brake system disclosed by the invention, have it is light-weight, installation space is small, maintenance is simple,
The features such as reliability is high.On the basis of reduction aircraft weight is fully considered, according to the structure space state of aircraft, using aneroid
Potential source designs, and disclosure satisfy that aircraft slides the functions such as brake, aircraft turn, shutdown brake in ground taxi；Fly meeting
On the basis of machine requirement, the attachmentes such as pressure accumulation bottle or hydraulic pump, surge flask are eliminated, greatly reduce the weight of brake system
Amount, reduces aircraft manufacturing and maintenance cost, and facilitate the installation and removal of system, ensure that tieing up for airplane brake system
Shield property and functional reliability.
A kind of type aircraft hydraulic brake system disclosed by the invention, mainly solves several big technical problems：1. brake system
System is designed using no hydraulic power source, is eliminated the attachmentes such as pressure accumulation bottle or hydraulic pump, surge flask, is improved the reliability of system, is saved
Installation space, significantly reduces system weight；2. brake system pressure is by manually establishing, without consuming aircraft engine again
Or other energy, alleviate the load of engine；3. brake system Fuel Tanking Unit is integrated in brake sensor, installation has been saved
Space alleviates system weight.
Description of the drawings
Fig. 1 is schematic structural view of the invention.
Reference numeral：1st, brake sensor；21st, the first hose；22nd, the second hose；3rd, lock-up cock；4th, conduit；5th, it stops
Vehicle device.
Specific embodiment
Below in conjunction with the accompanying drawings, embodiment is described in detail.
Referring to attached drawing 1, a kind of type aircraft hydraulic brake system, for no hydraulic power source brake system, including brake sensor
1st, the first hose 21, the second hose 22, lock-up cock 3, conduit 4 and brake gear 5, the brake sensor 1 are attached separately to fly
The both sides of machine pedal device drive by the brake pedal on pedal；The brake sensor 1 passes through first hose 21 and institute
One end pipe nipple for stating lock-up cock 3 is connected；The other end pipe nipple of the lock-up cock 3 is soft by the conduit 4 and second
Pipe 22, brake gear 5 are sequentially connected；Second hose 22 is installed on to be adopted between 5 one end of brake gear, each connector
It is tightly connected with thread forms；During aircraft taxi, when manipulating left and right both sides brake pedal, formed inside brake system
One closed system, according to the stroke of brake pedal, the brake sensor 1 exports the brake pressure that is corresponding to it, by first
Hose 21, lock-up cock 3,4 and second hose 22 of conduit are transmitted to brake gear 5, realize aircraft taxi brake；Pass through control
The size of left and right both sides brake pressure realizes aircraft taxi brake or turning；The lock-up cock 3 is installed on cockpit floor,
Manipulating brake pedal makes brake system establish pressure, then manipulate the lock-up cock 3, you can brake gear 5 is kept to be opened with locking
The pressure between 3 is closed, lasting brake can be realized without Constant manipulation brake pedal, realize aircraft shutdown brake, then manipulate
Lock-up cock 3 can then release shutdown brake.
Further, the 1 inside setting shoe cream room of brake sensor, eliminates special fuel reserve tank, has saved installation
Space alleviates system weight.
A kind of type aircraft hydraulic brake system disclosed by the invention, have it is light-weight, installation space is small, maintenance is simple,
The features such as reliability is high.On the basis of reduction aircraft weight is fully considered, according to the structure space state of aircraft, using aneroid
Potential source designs, and disclosure satisfy that aircraft slides the functions such as brake, aircraft turn, shutdown brake in ground taxi, flies meeting
On the basis of machine requirement, the attachmentes such as pressure accumulation bottle or hydraulic pump, surge flask are eliminated, greatly reduce the weight of brake system
Amount, reduces aircraft manufacturing and maintenance cost, and facilitate the installation and removal of system, ensure that tieing up for airplane brake system
Shield property and functional reliability.
Listed above is only one of specific embodiments of the present invention.It is clear that the invention is not restricted to above example, may be used also
With there are many similar reshapings.What those of ordinary skill in the art directly can export or associate from present disclosure
All deformations, are considered as invention which is intended to be protected.
Claims (2)
1. a kind of type aircraft hydraulic brake system, it is characterised in that：The type aircraft hydraulic brake system is no hydraulic power source
Brake system, including brake sensor（1）, the first hose（21）, the second hose（22）, lock-up cock（3）, conduit（4）And brake
Vehicle device（5）, the brake sensor（1）The both sides of airplane tread device are attached separately to, are driven by the brake pedal on pedal；
The brake sensor（1）Pass through first hose（21）With the lock-up cock（3）One end pipe nipple be connected；The lock
Make and break is closed（3）Other end pipe nipple pass through the conduit（4）With the second hose（22）, brake gear（5）It is sequentially connected；It is described
Second hose（22）It is installed on close to brake gear（5）One end；According to the stroke of brake pedal, the brake sensor（1）It is defeated
Go out the brake pressure that is corresponding to it, by the first hose（21）, lock-up cock（3）, conduit（4）And second hose（22）It is transmitted to brake
Vehicle device（5）, realize aircraft taxi brake or turning；The lock-up cock（3）It is installed on cockpit floor, manipulates brake pedal
Brake system is made to establish pressure, then manipulates the lock-up cock（3）, keep brake gear（5）With lock-up cock（3）Between pressure
Power realizes aircraft shutdown brake.
2. a kind of type aircraft hydraulic brake system as described in claim 1, it is characterised in that：The brake sensor（1）
Inside setting shoe cream room.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610384666.0A CN105836112B (en) | 2016-06-02 | 2016-06-02 | A kind of type aircraft hydraulic brake system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610384666.0A CN105836112B (en) | 2016-06-02 | 2016-06-02 | A kind of type aircraft hydraulic brake system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105836112A CN105836112A (en) | 2016-08-10 |
| CN105836112B true CN105836112B (en) | 2018-06-26 |
Family
ID=56595607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610384666.0A Active CN105836112B (en) | 2016-06-02 | 2016-06-02 | A kind of type aircraft hydraulic brake system |
Country Status (1)
| Country | Link |
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| CN (1) | CN105836112B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367527B (en) * | 2018-10-17 | 2021-09-21 | 江西洪都航空工业集团有限责任公司 | Aircraft stop brake limiting mechanism |
| CN110550195A (en) * | 2019-09-03 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | brake system |
| CN110654567A (en) * | 2019-09-23 | 2020-01-07 | 刘金营 | Early education-6 airplane brake efficiency measuring device |
| CN112061382B (en) * | 2020-09-11 | 2022-04-08 | 中航飞机起落架有限责任公司 | Frame formula undercarriage brake hose connection structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1935328A1 (en) * | 1968-07-12 | 1970-01-22 | Staffan Wahlstroem | Hydraulic braking system for vehicles |
| US3756666A (en) * | 1971-06-03 | 1973-09-04 | Teldix Gmbh | Hydraulic brake servo arrangement |
| CN102180156A (en) * | 2011-04-18 | 2011-09-14 | 中南大学 | Antiskid braking control system for airplane |
| CN103803063A (en) * | 2014-01-26 | 2014-05-21 | 北京航空航天大学 | Self-energy feedback type brake apparatus-based airplane braking system and control method thereof |
| CN103963761A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Deceleration rate control-based antiskid braking system and method for airplane |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
| CN203889061U (en) * | 2014-05-13 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Airplane hydraulic coach braking system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101418325B1 (en) * | 2012-03-13 | 2014-07-10 | 주식회사 만도 | Integrated Electronic Hydraulic Brake System |
-
2016
- 2016-06-02 CN CN201610384666.0A patent/CN105836112B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1935328A1 (en) * | 1968-07-12 | 1970-01-22 | Staffan Wahlstroem | Hydraulic braking system for vehicles |
| US3756666A (en) * | 1971-06-03 | 1973-09-04 | Teldix Gmbh | Hydraulic brake servo arrangement |
| CN102180156A (en) * | 2011-04-18 | 2011-09-14 | 中南大学 | Antiskid braking control system for airplane |
| CN103963761A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Deceleration rate control-based antiskid braking system and method for airplane |
| CN103803063A (en) * | 2014-01-26 | 2014-05-21 | 北京航空航天大学 | Self-energy feedback type brake apparatus-based airplane braking system and control method thereof |
| CN203889061U (en) * | 2014-05-13 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Airplane hydraulic coach braking system |
| CN104002784A (en) * | 2014-05-14 | 2014-08-27 | 西安航空制动科技有限公司 | Brake control system of multi-wheel-train brake machine wheel |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105836112A (en) | 2016-08-10 |
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