CN108146622A - The aircraft brake-by-wire system and brake method switched using self-actuating brake - Google Patents
The aircraft brake-by-wire system and brake method switched using self-actuating brake Download PDFInfo
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- CN108146622A CN108146622A CN201711272393.1A CN201711272393A CN108146622A CN 108146622 A CN108146622 A CN 108146622A CN 201711272393 A CN201711272393 A CN 201711272393A CN 108146622 A CN108146622 A CN 108146622A
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000000203 mixture Substances 0.000 claims abstract description 9
- 239000003921 oil Substances 0.000 claims description 40
- 239000012208 gear oil Substances 0.000 claims description 11
- 230000008569 process Effects 0.000 claims description 10
- 239000007788 liquid Substances 0.000 claims description 8
- 230000005611 electricity Effects 0.000 claims description 6
- 239000010720 hydraulic oil Substances 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 4
- 230000001771 impaired effect Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 2
- 230000008901 benefit Effects 0.000 abstract description 2
- 238000013024 troubleshooting Methods 0.000 description 4
- 230000032258 transport Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
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Classifications
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- 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
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- 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
- B60T13/00—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems
- B60T13/74—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Regulating Braking Force (AREA)
Abstract
A kind of aircraft brake-by-wire system and brake method switched using self-actuating brake.Brake instruction transducer, control box, electrohydraulic servo valve and velocity sensor form conventional brake system.The antiskid control system of control box, electrohydraulic servo valve and velocity sensor composition routine.Self-actuating brake switchs K or the first self-actuating brake switch K1 and the second self-actuating brake switch K2, electrohydraulic servo valve, flow controller, check valve, velocity sensor and control box composition autobrake system.The present invention brakes with the 75 125% of normal braking system maximum brake pressure, the excess speed of self-actuating brake initial hydraulic pressure is inhibited to rise with throttling set or by control box, fully it is conducive to the available combination torque of runway to greatest extent, distance of landing run 35% or so is shortened in more conventional brake, it has ensured and has taken off landing safety, airfield runway utilization rate and equipment utilization rate are improved, economic, society and military benefit are apparent.
Description
Technical field
The present invention relates to a kind of airplane wheel brake-by-wire systems, are specifically related to a kind of winged with self-actuating brake ability
Machine brake-by-wire system.
Background technology
Airplane wheel brake system is the composition part of modern aircraft take-off and landing device, is to take off, alighting run and ground
The basic guarantee equipment of face taxiing control safe operation to shorten ground run distance after ensureing aircraft landing, stops aircraft as early as possible
Stop and, while prevent quick-fried tire of stopping.Experimental study and use show under certain condition, effectively to contract using self-actuating brake
Short aircraft landing ground run distance.Self-actuating brake is also that people expect always, to mitigate driver at the landing safety-critical moment
Load.At present, general aircraft does not have self-actuating brake ability, includes needing to drive using the aircraft of brake-by-wire, when brake
Member tramples brake pedal or control brake lever always, to manipulate brake valve or brake instruction transducer, only Boeing, Air Passenger etc.
Some types such as B737-700, A320 are furnished with autobrake system, by the different horizontal self-actuating brakes of the rate of deceleration.Foreign countries are this certainly
Dynamic brake system includes the attachmentes such as self-actuating brake selecting switch, self-actuating brake control box, self-actuating brake servo valve.Before taking off
Driver will be manipulated outside self-actuating brake selecting switch setting self-actuating brake gear, undercarriage, spoiler, throttle lever position etc. one
Sequence of states logic must fully meet defined state logic, and autobrake system is in armed armed state, aircraft
Autobrake system could start operation when land or suspension are taken off.This self-actuating brake design configurations are complicated, and failure is multiple, troubleshooting
Positioning difficulty is big, and use reliability is low, and a variety of logical relations have even caused security risk, convenient reliable therefore, it is necessary to release
Autobrake system, meet using technical security requirement and the needs of air duty, ground crew.
In the innovation and creation application No. is 201610902427.X, it is a kind of anti-improper using the winged of emergency brake to disclose
Machine brake-by-wire system；In the innovation and creation application No. is 201610876509.1, a kind of brake instruction direct controlled type is disclosed
Aircraft brake-by-wire system；In the innovation and creation application No. is 201610436991.7, disclosing one kind can select to stop
The brake-by-wire system of the aircraft single-wheel double-brake of vehicle mode；It is public in the innovation and creation application No. is 201610436552.6
A kind of Flight By Wire brake system that can select brake mode is opened；Application No. is 201610436698.0 innovation and creation
In, disclose a kind of optional Flight By Wire brake system of aircraft single-wheel double-brake；Application No. is 201610436553.0
In innovation and creation, a kind of airplane wheel Flight By Wire brake system that can select brake modes is disclosed；Application No. is
In 201310070226.4 innovation and creation, a kind of aircraft brake-by-wire system is disclosed, these published aircraft fax are stopped
Vehicle system is all without automatic brake functions.
In the innovation and creation application No. is 201610906014.9, a kind of airplane inertial for ensuring emergency brake is disclosed
Anti-skid brake system (ABS)；In the innovation and creation application No. is 201610589061.5, a kind of aircraft brake anti-sliding control is disclosed
Method and airplane brake system；In the innovation and creation application No. is 201610436904.8, disclose a kind of for aircraft list
The double-brake system of wheel brake；In the innovation and creation application No. is 201610436272.5, disclose a kind of based on brake pressure
Power selects to slide the airplane wheel brake system of brake；In the innovation and creation application No. is 201610436700.4, disclose
One kind can select aircraft brake pattern brake system；In the innovation and creation application No. is 201510151374.8, disclose
A kind of aircraft normal braking system with take-off line braking ability；Application No. is 201510152621.6 innovation and creation
In, disclose a kind of airplane hydraulic pressure brake system；In the innovation and creation application No. is 201510152590.4, one kind is disclosed
Aircraft normal braking system；In the innovation and creation application No. is 201310070307.4, disclose a kind of mixed type aeroplane and stop
Vehicle system and its control method；In the innovation and creation application No. is 201210053825.0, a kind of anti-skidding brake of aircraft is disclosed
Vehicle control and control method, these published airplane brake systems are all without automatic brake functions.
Invention content
Self-actuating brake design configurations are complicated, failure is multiple, troubleshooting positioning difficulty is big to overcome existing for existing brake system,
Use reliability is low, and a variety of logical relations of level-one even cause the deficiency of security risk, and the present invention proposes a kind of using certainly
The aircraft brake-by-wire system and brake method of dynamic brake switch.
The aircraft brake-by-wire system proposed by the present invention switched using self-actuating brake includes brake instruction transducer, electro-hydraulic
Servo valve, velocity sensor and control box；Wherein, brake instruction transducer, control box, electrohydraulic servo valve and velocity sensor group
Into conventional brake system.The antiskid control system of control box, electrohydraulic servo valve and velocity sensor composition routine.Its feature exists
In：
I further includes self-actuating brake switch K, flow controller and check valve；When the aircraft brake-by-wire system for level-one from
During dynamic brake system, self-actuating brake switch K is one；When the aircraft brake-by-wire system is two level self-actuating brake
During system, self-actuating brake switch K is two, is that the first self-actuating brake switch K1 and the second self-actuating brake switch respectively
K2。
II self-actuating brake switchs K or the first self-actuating brake switch K1 and the second self-actuating brake switch K2, electrohydraulic servo valve, section
Flow device, check valve, velocity sensor and control box composition autobrake system.And：Self-actuating brake switchs K or the first automatic brake
Stopping switch K1 and the second self-actuating brake switch K2 are installed in cockpit, by driver's manually handle, are connect to control box offer
On-off opens self-stopping enabled electric signal, issues or do not issue the self-actuating brake electricity of electrohydraulic servo valve via control box control
Signal is flowed, electrohydraulic servo valve brake mouth output hydraulic pressure pressure, which carries out self-actuating brake or electrohydraulic servo valve brake mouth oil return, does not have liquid
Pressure pressure exports, and disconnects self-actuating brake.
III autobrake system brakes for level-one or two level brake.
In level-one autobrake system, the negative pole end of self-actuating brake switch K is connected with the electrical input terminal of control box；Electricity
The electrical input terminal of hydraulic servo is connected with the electrical defeated place end of the control box；The brake mouth and flow controller of electrohydraulic servo valve
Oil inlet connects；The oil outlet of the flow controller and the brake gear oil inlet pipeline connection of brake machine wheel.One of check valve
Hydraulic interface is connected on the pipeline between the electrohydraulic servo valve and flow controller, another hydraulic interface connection of the check valve
On pipeline between the flow controller and the brake gear oil inlet of brake machine wheel, so as to which the check valve is connected in parallel on flow controller
On the pipeline of both ends；The opening direction of check valve is opposite with the running of hydraulic power oil direction for transporting to wheel brake.
In two level autobrake system, the negative pole end of the first self-actuating brake switch K1 and the second self-actuating brake switch K2's
Negative pole end connects respectively with each electrical input terminal of control box.The brake mouth of electrohydraulic servo valve is connected with the oil inlet of flow controller；
The oil outlet of the flow controller and the brake gear oil inlet pipeline connection of brake machine wheel.The hydraulic interface connection of check valve
On pipeline between the electrohydraulic servo valve and flow controller, another hydraulic interface of the check valve is connected to the flow controller
On pipeline between the brake gear oil inlet of brake machine wheel, so as to which the check valve is connected in parallel on the pipeline of flow controller both ends；
The opening direction of check valve transports to the running of hydraulic power oil direction of wheel brake backwards.
The flow controller uses orifice restrictors, and multiple restricting orifices by housing and in housing form.Liquid
Pressure oil liquid stream generates fluid resistance through multiple restricting orifices, and the mistake for the initial hydraulic pressure that brakes during self-actuating brake is connected so as to limit
Fast speed rises, and plays the role of the pressure peak that disappears and smoothly rises, avoid undercarriage because brake torque charge it is impaired.
The electrohydraulic servo valve is postiive gain valve, and hydraulic pressure output pressure is directly proportional to control input current signal.
The brake process of aircraft brake-by-wire system proposed by the present invention that is switched using self-actuating brake is：
Step 1, self-actuating brake rank and self-actuating brake pressure are set；
When self-actuating brake rank is level-one, self-actuating brake pressure value is normal braking system maximum brake pressure
100%, self-actuating brake pressure is 10MPa；
When self-actuating brake rank is two level, wherein first order self-actuating brake pressure value is stopped for normal braking system maximum
Vehicle pressure 100%, self-actuating brake pressure are 10MPa；Self-actuating brake pressure value in the second level brakes for normal braking system maximum
The 125% of pressure, self-actuating brake pressure are 12.5MPa；
Step 2, self-actuating brake is connected；When aircraft landing reaches brake speed, manual closing switch implements aircraft brake；
When self-actuating brake rank is level-one, self-actuating brake switchs the contact closure of K, so as to be sent out automatically to control box 3
The enabled electric signal of brake.
When self-actuating brake rank is two level, the first self-actuating brake switchs K1 and the second self-actuating brake switch K2 is corresponding respectively
Self-stopping rank and self-stopping pressure：First self-actuating brake switchs the automatic brake of K1 or the second self-actuating brake switch K2
Stopping switch contact closure can implement aircraft self-actuating brake so as to send out self-actuating brake to control box and enable electric signal.
Step 3, self-actuating brake is disconnected；
When self-actuating brake rank is level-one, aircraft landing, which is slided to run, to be stopped or reaches low speed slide speed, makes self-actuating brake
The self-actuating brake switch contact for switching K disconnects, and enables electric signal so as to disconnect self-actuating brake, releases aircraft self-actuating brake.
When self-actuating brake rank is two level, aircraft landing, which is slided to run, to be stopped or reaches low speed slide speed, makes first automatically
The self-actuating brake switch contact of brake switch K1 or the second self-actuating brake switch K2 disconnect, and telecommunications is enabled so as to disconnect self-actuating brake
Number, release aircraft self-actuating brake.
In automatic braking process, skid if there is brake machine wheel, by by electrohydraulic servo valve, velocity sensor and control
Box processed forms electronic anti-breaking brake control system and implements anti-sliding control.
The present invention relies on existing aircraft fax normal braking system, increases convenient reliable autobrake system parallel,
Self-actuating brake is switched on or switched off with the manual switch for being placed in cockpit, anti-slip control is carried out with the anti-sliding control part of normal braking system
System, is braked with the 75-125% of normal braking system maximum brake pressure, inhibits automatic with throttling set or by control box
The excess speed of brake initial hydraulic pressure rises.
In the present invention, self-actuating brake is level-one or two level.For setting two level self-actuating brake, two self-actuating brake switches are mutual
Reprimand is connected, i.e., one switch is closed, another switch can not achieve closure and connect circuit, and a switch is controlled by another and opens
It closes；A corresponding level-one brake pressure is opened in self-actuating brake.
Each automatic brake switch is mounted in cockpit；Self-actuating brake switch is implemented electrical by cable with control box
Connection；Self-actuating brake switch is controlled to control box offer by driver's manually handle and is switched on or switched off self-stopping enabled electricity
Signal issues or does not issue the self-actuating brake current signal of electrohydraulic servo valve, electrohydraulic servo valve brake mouth via control box control
Output hydraulic pressure pressure, which carries out self-actuating brake or electrohydraulic servo valve brake mouth oil return, does not have hydraulic pressure output, disconnects self-actuating brake.
After self-actuating brake manual switch disconnects, self-actuating brake pressure releases, driver can be transferred to normal braking；It is normal to stop
Che Shi, driver jam on the sleeve that brake pedal manipulates brake instruction transducer, make brake instruction transducer output is corresponding to stop
For vehicle command voltage signal to control box, control box generates corresponding brake control electric current signal to electrohydraulic servo valve, electro-hydraulic by this
Servo valve exports corresponding brake pressure, transports to brake machine wheel and brakes；Driver jams on brake pedal, and to get over overline Cheng Yue big,
The brake instruction voltage signal of brake instruction transducer output is bigger, and the brake control electric current signal that control box generates is bigger, by
The brake pressure of electrohydraulic servo valve output is bigger, and braking strength is higher, and brake machine wheel is slowed down faster.
The present invention improves and has expanded normal braking system operation range of choice, is conducive to give full play to brake system and dive
Power shortens distance of landing run, as early as possible brake grounding machine, Safe withdrawing runway；Due to there is no complex logic relationship and composition, have
It is the features such as rational in infrastructure feasible, using flexible is convenient, reliability is high, occurred frequently, complicated without failure existing for some existing civil aircrafts
The problems such as logical relation implicit security accident potential and difficult troubleshooting, even if there is brake failure, also allows for searching troubleshooting, as long as
Driver, which stretches out one's hand, pulls a lower switch, you can operation self-actuating brake firmly touches on the brake pedal, significantly always without driver's both feet
Mitigate driver and slide the of deciding importance body ＆ mind load of race in aircraft landing, so as to the steady Aircraft of operating the rudder of the behaviour that concentrates one's energy
To；Self-actuating brake rank and self-actuating brake pressure setting proposed by the present invention meets aircraft actual use situation, meanwhile, automatically
The brake torque that brake pressure generates will not damage undercarriage intensity, and can fully be provided conducive to runway to greatest extent
Combination torque, therefore in the case where using self-stopping brake modes it is more conventional brake shorten distance of landing run 35% or so,
It has ensured and has taken off landing safety, improve airfield runway utilization rate and equipment utilization rate, economic, society and military benefit are bright
It is aobvious.
The present invention, which can solve existing aircraft normal braking system, does not have the deficiency of self-actuating brake ability, and overcomes civil aircraft
Self-actuating brake there are the problem of, meet people's self-stopping expectation to aircraft for a long time.
Description of the drawings
Attached drawing 1 is the structure diagram that the present invention has the self-stopping brake system of level-one；
Attached drawing 2 is the structure diagram that the present invention has the self-stopping brake system of level-one.In figure：
1. brake instruction transducer；2. electrohydraulic servo valve；3. control box；4. velocity sensor；5. brake machine wheel；It is 6. unidirectional
Valve；7. flow controller；K. self-actuating brake switchs；K1. the first self-actuating brake switchs；K2. the second self-actuating brake switchs.
Specific embodiment
Embodiment 1
Referring to Fig. 1.Modern aircraft nose-gear wheel generally not strap brake, equipped with stopping on the wheel of two main landing gears
Vehicle device.Two aircraft main landing gears are typically placed symmetrically in airframe both sides.The present embodiment is with one of main landing gear
And for one wheel of installation, illustrate the aircraft fax hydraulic brake system with self-actuating brake ability.
The present embodiment is level-one self-actuating brake；Self-actuating brake antiskid valve is made using shared antiskid valve with electrohydraulic servo valve
Antiskid valve.
In the present embodiment, brake instruction transducer 1, control box 3, electrohydraulic servo valve 2 and velocity sensor 4 form conventional
Brake system.Control box 3, electrohydraulic servo valve 2 and velocity sensor 4 form conventional antiskid control system.
The present embodiment is a kind of aircraft fax hydraulic brake system with self-actuating brake ability, including：Brake instruction passes
Sensor 1, control box 3, electrohydraulic servo valve 2, self-actuating brake switch K, flow controller 7, check valve 6 and velocity sensor 4.Wherein：From
Dynamic brake switch K is mounted in cockpit；Self-actuating brake switch K implements electrically to couple by cable with control box 3；Self-actuating brake
K is switched by driver's manually handle, is switched on or switched off self-stopping enabled electric signal to the offer of control box 3, via control box 3
The self-actuating brake current signal of electrohydraulic servo valve 2 is issued or is not issued in control, electrohydraulic servo valve 2 brake mouth output hydraulic pressure pressure into
Row self-actuating brake or the brake mouth oil return of electrohydraulic servo valve 2 do not have hydraulic pressure output, disconnect self-actuating brake.
Self-actuating brake switch K, electrohydraulic servo valve 2, flow controller 7, check valve 6, velocity sensor 4 and the composition of control box 3 are certainly
Dynamic brake system.Electrohydraulic servo valve 2, velocity sensor 4 and control box 3 are to share attachment, for anti-sliding control.
In the autobrake system, flow controller 7 has two hydraulic interfaces, is oil inlet and oil outlet respectively.Automatically
The negative pole end of brake switch K is connected with the electrical input terminal of control box 3；The electrical input terminal of electrohydraulic servo valve 2 and the control
The electrical defeated place end connection of box 3；The brake mouth of electrohydraulic servo valve 2 is connected with the oil inlet of flow controller 7；The flow controller 7 goes out
Hydraulic fluid port and the brake gear oil inlet pipeline connection of brake machine wheel 5.One hydraulic interface of check valve 6 is connected to described electro-hydraulic watch
It takes on the pipeline between valve 2 and flow controller 7, another hydraulic interface of the check valve 6 is connected to the flow controller and braking machine
On pipeline between the brake gear oil inlet of wheel 5, so as to which the check valve is connected in parallel on 7 both ends pipeline of flow controller；Check valve 6
Opening direction it is opposite with the running of hydraulic power oil direction for transporting to wheel brake.
The flow controller 7 uses orifice restrictors, and multiple restricting orifices by housing and in housing form.Liquid
Pressure oil liquid stream generates fluid resistance through multiple restricting orifices, and the mistake for the initial hydraulic pressure that brakes during self-actuating brake is connected so as to limit
Fast speed rises, and plays the role of the pressure peak that disappears and smoothly rises, avoid undercarriage because brake torque charge it is impaired.
The check valve 6 uses ball valve.The effect of check valve 6 is that check valve 6 is closed in self-actuating brake, is stopped from upper
The hydraulic oil liquid that trip comes passes through, and hydraulic oil liquid can only flow through the brake gear that flow controller 7 leads to brake machine wheel 5；In self-actuating brake
Check valve 6 is opened when anti-sliding control gets off the brakes, and the brake gear hydraulic oil oil return for brake machine wheel 5 provides a bypass, make from
The hydraulic oil that downstream is come, to accelerate oil return speed, can improve autobrake system without flow controller 7 and by 6 oil return of check valve
The response of anti-sliding control.
The self-actuating brake switch K is Bar-pulling type switch.Self-actuating brake switch K is placed in the autobrake instruction of control box 3
In input control circuit or be placed in control box 3 and export in the self-actuating brake current circuit to electrohydraulic servo valve 2, control connect or
The self-actuating brake current signal of electrohydraulic servo valve 2 is disconnected, self-actuating brake switch K sends out enabled electric signal to be implemented by the prior art.
Self-actuating brake switch K is placed in self-actuating brake circuit, is manipulated self-actuating brake switch K and is closed, is then exported automatically to electrohydraulic servo valve 2
The electric current that brakes carries out self-actuating brake, and electrohydraulic servo valve 2 exports corresponding water brake pressure；Self-actuating brake switch K is manipulated to disconnect,
Cannot then electrohydraulic servo valve 2 be given to export self-actuating brake electric current, electrohydraulic servo valve 2 does not have water brake pressure output.
For safeguards system safe and reliable operation, electrohydraulic servo valve 2 carries hydraulic lock, and when brake receives control box 3 and sends out first
The electric signal of the unlocking come, to connect the pressure supply coming oil of electrohydraulic servo valve 2.
Wheel velocity measuring is completed by 4 attachment of wheel spin-up transducer, monitors the sliding mode of wheel；Anti-sliding control is by controlling
Box 3 processed is completed；The brake pressure of brake machine wheel 5 is transported in the control electric current signal of 2 response control box of electrohydraulic servo valve, output and adjusting
Power；Self-actuating brake is carried out by driver's manually handle self-actuating brake switch K.
Brake instruction transducer 1 is mounted on cockpit floor in the following, being manipulated by driver to it, the brake needed for control output
Vehicle command voltage signal, then electrohydraulic servo valve 2 is controlled to export required water brake pressure by control box 3.
It is 10MPa that the present embodiment, which manipulates 1 normal braking of brake instruction transducer output maximum hydraulic pressure pressure,.
Electrohydraulic servo valve 2 is postiive gain valve, and hydraulic pressure output pressure is directly proportional to control input current signal.Electrohydraulic servo valve
Electric interfaces and three hydraulic interfaces there are one 2.Three hydraulic interfaces are respectively oil inlet, brake mouth and oil return opening；
Oil inlet therein carrys out oil pipe line with brake system pressure source and couples；Brake brake gear of the mouth through flow controller 7 Yu brake machine wheel 5
Oil inlet pipeline couples；Oil return opening couples with aircraft oil return line.The electric interfaces implement electricity by cable and control box 3
Gas couples, and receives brake, anti-sliding control current signal that control box 3 is sent.
Control box 3 is mounted in main landing gear compartment, by power supply system power supply on aircraft；Control box 3 has brake, anti-slip control
The units such as system, fault detect have the function of brake, anti-sliding control, fault detect etc.；The electric interfaces input terminal point of control box 3
Do not coupled with brake instruction transducer 1, wheel spin-up transducer 4 by shielding insulation conducting wire；The electric interfaces output of control box 3
End is coupled by shielding insulation conducting wire with the electric interfaces of electrohydraulic servo valve 2；
The electric interfaces input terminal of control box 3 also electrically couples with self-actuating brake switch K；
Therefore control box 3 had not only received the brake instruction signal that brake instruction transducer 1 is sent, but also received self-actuating brake switch
The autobrake instruction signal that K is sent；When there is the autobrake instruction signal of self-actuating brake switch K, brake instruction sensing
The brake instruction Signal Fail that device 1 is sent；The enable signal that namely self-actuating brake switch K is sent is preferential；Using the prior art
This arrangement can be realized；
Wheel spin-up transducer 4 is mounted in brake machine wheel, is rotated by machine driving with brake machine wheel.Velocity sensor
Electric interfaces there are one 4, are electrically coupled by cable with control box 3.
The present embodiment also proposed a kind of automatic brake of the aircraft fax hydraulic brake system by self-actuating brake ability
Vehicle method, detailed process are：
Step 1, self-actuating brake rank and self-actuating brake pressure are set；Self-actuating brake rank is set as level-one；Self-actuating brake
Pressure value is normal braking system maximum brake pressure 100%, and in the present embodiment, self-actuating brake pressure is 10MPa；
Step 2, self-actuating brake is connected；When aircraft landing reaches brake speed, manual closing switch implements aircraft brake
Vehicle.The handle of dialling that driver pulls self-actuating brake switch K manually makes self-actuating brake switch K contact closures, so as to be sent out to control box 3
Self-actuating brake enables electric signal, you can implements aircraft self-actuating brake.The aircraft landing brake speed is 280km/h.
Step 3, self-actuating brake is disconnected；It slides to run when aircraft landing and stops or reach low speed slide speed, disconnect manually automatic
Brake switch releases aircraft self-actuating brake.
It in automatic braking process, skids if there is brake machine wheel 5, by electrohydraulic servo valve 2, velocity sensor 4 and control
Box 3 processed forms electronic anti-breaking brake control system and implements anti-sliding control.
In the present embodiment, the handle of dialling that driver pulls self-actuating brake switch K manually disconnects self-actuating brake switch K contacts,
Electric signal is enabled so as to disconnect self-actuating brake, releases aircraft self-actuating brake.
In automatic braking process, if to switch to the normal braking that foot touches on the brake, driver only needs to disconnect manually automatic
Brake switch K, you can release aircraft self-actuating brake.
The present embodiment sets level-one self-actuating brake, and aircraft landing, which is slided, runs the preferred self-actuating brake mode of brake suggestion, to shorten
Distance of landing run.
Embodiment 2
Referring to Fig. 2.The present embodiment is a kind of aircraft fax hydraulic brake system for having self-actuating brake ability, with embodiment 1
Technical solution the difference lies in the aircraft fax hydraulic brake system of, the present embodiment be two level self-actuating brake.
The present embodiment includes brake instruction transducer 1, control box 3, electrohydraulic servo valve 2, the first self-actuating brake switch K1, the
Two self-actuating brakes switch K2, flow controller 7, check valve 6 and velocity sensor 4.Brake instruction transducer 1 therein, control box 3,
Electrohydraulic servo valve 2 and velocity sensor 4 form conventional brake system.4 groups of control box 3, electrohydraulic servo valve 2 and velocity sensor
Into conventional antiskid control system.Self-actuating brake switch K, electrohydraulic servo valve 2, flow controller 7, check valve 6,4 and of velocity sensor
Control box 3 forms autobrake system.Electrohydraulic servo valve 2, velocity sensor 4 and control box 3 are to share attachment, for anti-slip control
System.
The first self-actuating brake switch K1, the second self-actuating brake switch K2 are mounted in cockpit；First self-actuating brake
Switch K1, the second self-actuating brake switch K2 implement electrically to couple by cable with control box 3；First self-actuating brake switch K1, the
Two self-actuating brakes switch K2 by driver's manually handle, control to the offer of control box 3 and are switched on or switched off self-stopping enabled electricity
Signal, the self-actuating brake current signal for issuing or not issuing electrohydraulic servo valve 2 is controlled via control box 3, and electrohydraulic servo valve 2 brakes
Mouth output hydraulic pressure pressure, which carries out self-actuating brake or the brake mouth oil return of electrohydraulic servo valve 2, does not have hydraulic pressure output, disconnects automatic brake
Vehicle.
In the autobrake system, the negative pole end of the first self-actuating brake switch K1 and the second self-actuating brake switch K2's
Negative pole end connects respectively with each electrical input terminal of control box 3.The brake mouth of electrohydraulic servo valve 2 connects with the oil inlet of flow controller 7
It is logical；The oil outlet of the flow controller 7 and the brake gear oil inlet pipeline connection of brake machine wheel 5.One hydraulic pressure of check valve 6 connects
Mouth is connected on the pipeline between the electrohydraulic servo valve 2 and flow controller 7, another hydraulic interface of the check valve 6 is connected to
On pipeline between the flow controller and the brake gear oil inlet of brake machine wheel 5, so as to which the check valve is connected in parallel on flow controller 7
On the pipeline of both ends；The opening direction of check valve 6 transports to the running of hydraulic power oil direction of wheel brake backwards.
Flow controller 7 has two hydraulic interfaces, is oil inlet and oil outlet respectively.Described first self-actuating brake switch K1,
Second self-actuating brake switch K2 is Bar-pulling type switch.
The present embodiment self-actuating brake rank is two level, there is two self-actuating brake switches：First self-actuating brake switch K1, second
Self-actuating brake switchs K2.First self-actuating brake switchs K1 and the second self-actuating brake switch K2 mutual exclusions are connected, i.e., one switch is closed,
Another switch can not achieve closure and connect circuit, and a switch is controlled by another switch；Such purpose is to prevent from accidentally grasping
Make two self-actuating brakes switch and bring switching valve translation exception and brake failure problem.
The aircraft fax hydraulic brake system for having self-actuating brake ability described in a kind of present invention also utilization in the place of putting forward implements two level
The method of brake, detailed process are：
Step 1, self-actuating brake rank and self-actuating brake pressure are set；The self-actuating brake rank is two level；Wherein one
Grade self-actuating brake pressure value is normal braking system maximum brake pressure 100%, is 10MPa in the present embodiment；Another grade is certainly
Dynamic brake pressure value is the 125% of normal braking system maximum brake pressure, is 12.5MPa in the present embodiment
Step 2, self-actuating brake is connected；When aircraft landing reaches brake speed, manual closing switch implements aircraft brake；
First self-actuating brake switchs K1 and corresponds to self-stopping rank and self-stopping pressure respectively with the second self-actuating brake switch K2：
First self-actuating brake switch K1 corresponds to 10MPa, and the second self-actuating brake switch K2 corresponds to 12.5MPa；Aircraft landing brake speed is
260km/h.In the aircraft landing brake speed and the aircraft landing brake speed hereinafter,
Driver pulls group handle of the first self-actuating brake switch K1 or the second self-actuating brake switch K2 manually, makes what is operated
Self-actuating brake switch contact is closed, and can implement aircraft self-actuating brake so as to send out self-actuating brake to control box 3 and enable electric signal.
Step 3, self-actuating brake is disconnected；When aircraft landing cunning race stopping or reach low speed slide speed, it is automatic to pull first
The handle of dialling of brake switch K1 or the second self-actuating brake switch K2 disconnect the self-actuating brake switch contact operated, so as to disconnect certainly
The dynamic enabled electric signal of brake, releases aircraft self-actuating brake.
In automatic braking process, skid if there is brake machine wheel 5, by electrohydraulic servo valve 2, velocity sensor 4 and control
Box 3 processed forms electronic anti-breaking brake control system and implements anti-sliding control；
In automatic braking process, if to switch to the normal braking that foot touches on the brake, driver is only needed to disconnect manually automatically
Brake switch can release aircraft self-actuating brake.
Claims (6)
1. a kind of aircraft brake-by-wire system switched using self-actuating brake, including brake instruction transducer, electrohydraulic servo valve, speed
Spend sensor and control box；Wherein, brake instruction transducer, control box, electrohydraulic servo valve and velocity sensor form routine
Brake system；The antiskid control system of control box, electrohydraulic servo valve and velocity sensor composition routine；
It is characterized in that：
I further includes self-actuating brake switch K, flow controller and check valve；When the aircraft brake-by-wire system is level-one automatic brake
During vehicle system, self-actuating brake switch K is one；When the aircraft brake-by-wire system is two level autobrake system
When, self-actuating brake switch K is two, is the first self-actuating brake switch K1 and the second self-actuating brake switch K2 respectively；
II self-actuating brake switchs K or the first self-actuating brake switch K1 and the second self-actuating brake switch K2, electrohydraulic servo valve, throttling
Device, check valve, velocity sensor and control box composition autobrake system；And：Self-actuating brake switchs K or the first self-actuating brake
Switch K1 and the second self-actuating brake switch K2 are installed in cockpit, and by driver's manually handle, connection is provided to control box
Or self-stopping enabled electric signal is disconnected, the self-actuating brake electric current of electrohydraulic servo valve is issued or not issued via control box control
Signal, electrohydraulic servo valve brake mouth output hydraulic pressure pressure, which carries out self-actuating brake or electrohydraulic servo valve brake mouth oil return, does not have hydraulic pressure
Pressure output disconnects self-actuating brake；
III autobrake system brakes for level-one or two level brake.
2. the aircraft brake-by-wire system switched as described in claim 1 using self-actuating brake, which is characterized in that level-one automatic brake
In vehicle system, the negative pole end of self-actuating brake switch K is connected with the electrical input terminal of control box；The electrical input terminal of electrohydraulic servo valve
It is connected with the electrical defeated place end of the control box；The brake mouth of electrohydraulic servo valve is connected with the oil inlet of flow controller；The throttling
The oil outlet of device and the brake gear oil inlet pipeline connection of brake machine wheel；One hydraulic interface of check valve is connected to the electricity
On pipeline between hydraulic servo and flow controller, another hydraulic interface of the check valve is connected to the flow controller and braking machine
On pipeline between the brake gear oil inlet of wheel, so as to which the check valve is connected in parallel on the pipeline of flow controller both ends；Check valve
Opening direction is opposite with the running of hydraulic power oil direction for transporting to wheel brake.
3. the aircraft brake-by-wire system switched as described in claim 1 using self-actuating brake, which is characterized in that automatic in two level
In brake system, the first self-actuating brake switch K1 negative pole end and the second self-actuating brake switch K2 negative pole end respectively with control box
Each electrical input terminal connection；The brake mouth of electrohydraulic servo valve is connected with the oil inlet of flow controller；The oil outlet of the flow controller
With the brake gear oil inlet pipeline connection of brake machine wheel；One hydraulic interface of check valve be connected to the electrohydraulic servo valve with
On pipeline between flow controller, another hydraulic interface of the check valve is connected to the flow controller and the brake of brake machine wheel fills
It puts on the pipeline between oil inlet, so as to which the check valve is connected in parallel on the pipeline of flow controller both ends；The opening square of check valve is supported or opposed
To the running of hydraulic power oil direction for transporting to wheel brake.
4. the aircraft brake-by-wire system switched as described in claim 1 using self-actuating brake, which is characterized in that the throttling
Device uses orifice restrictors, and multiple restricting orifices by housing and in housing form；Hydraulic oil liquid flows through multiple throttlings
Orifice plate generates fluid resistance, and the excess speed of brake initial hydraulic pressure rises when self-actuating brake is connected so as to limit, and plays pressure
Power disappears the effect that peak smoothly rises, avoid undercarriage because brake torque charge it is impaired.
5. the aircraft brake-by-wire system switched as described in claim 1 using self-actuating brake, which is characterized in that described electro-hydraulic to watch
Valve is taken as postiive gain valve, hydraulic pressure output pressure is directly proportional to control input current signal.
6. it is a kind of using the brake method of aircraft brake-by-wire system that self-actuating brake is used to switch described in claim 1, it is special
Sign is that detailed process is：
Step 1, self-actuating brake rank and self-actuating brake pressure are set；
When self-actuating brake rank is level-one, self-actuating brake pressure value is normal braking system maximum brake pressure 100%, from
Dynamic brake pressure is 10MPa；
When self-actuating brake rank is two level, wherein first order self-actuating brake pressure value is normal braking system maximum brake pressure
Power 100%, self-actuating brake pressure are 10MPa；Self-actuating brake pressure value in the second level is normal braking system maximum brake pressure
125%, self-actuating brake pressure be 12.5MPa；
Step 2, self-actuating brake is connected；When aircraft landing reaches brake speed, manual closing switch implements aircraft brake；
When self-actuating brake rank is level-one, self-actuating brake switchs the contact closure of K, so as to send out self-actuating brake to control box 3
Enabled electric signal；
When self-actuating brake rank is two level, the first self-actuating brake switchs K1 and the second self-actuating brake switch K2 is corresponding automatic respectively
The rank of brake and self-stopping pressure：First self-actuating brake switchs K1 or the self-actuating brake of the second self-actuating brake switch K2 is opened
Contact closure is closed, can implement aircraft self-actuating brake so as to send out self-actuating brake to control box and enable electric signal；
Step 3, self-actuating brake is disconnected；
When self-actuating brake rank is level-one, aircraft landing, which is slided to run, to be stopped or reaches low speed slide speed, and self-actuating brake is made to switch K
Self-actuating brake switch contact disconnect, enable electric signal so as to disconnect self-actuating brake, release aircraft self-actuating brake；
When self-actuating brake rank is two level, aircraft landing, which is slided to run, to be stopped or reaches low speed slide speed, makes the first self-actuating brake
The self-actuating brake switch contact for switching K1 or the second self-actuating brake switch K2 disconnects, and electric signal is enabled so as to disconnect self-actuating brake,
Release aircraft self-actuating brake；
In automatic braking process, skid if there is brake machine wheel, by by electrohydraulic servo valve, velocity sensor and control box
It forms electronic anti-breaking brake control system and implements anti-sliding control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711272393.1A CN108146622B (en) | 2017-12-06 | 2017-12-06 | Airplane fly-by-wire brake system using automatic brake switch and brake method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711272393.1A CN108146622B (en) | 2017-12-06 | 2017-12-06 | Airplane fly-by-wire brake system using automatic brake switch and brake method |
Publications (2)
| Publication Number | Publication Date |
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| CN108146622A true CN108146622A (en) | 2018-06-12 |
| CN108146622B CN108146622B (en) | 2021-01-05 |
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| CN201711272393.1A Expired - Fee Related CN108146622B (en) | 2017-12-06 | 2017-12-06 | Airplane fly-by-wire brake system using automatic brake switch and brake method |
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| CN (1) | CN108146622B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115783252A (en) * | 2023-02-08 | 2023-03-14 | 四川腾盾科技有限公司 | Low-cost unmanned aerial vehicle autonomous brake pressure control calculation method |
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| CN107352020A (en) * | 2017-06-29 | 2017-11-17 | 西安航空制动科技有限公司 | A kind of airplane brake system and the control method of quiet brake protection |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB752057A (en) * | 1954-04-20 | 1956-07-04 | Goodyear Tire & Rubber | Automatic anti-skid braking control and lockout control apparatus |
| CN201914232U (en) * | 2010-12-16 | 2011-08-03 | 西安航空制动科技有限公司 | Automatic brake device for airplane |
| CN102180156A (en) * | 2011-04-18 | 2011-09-14 | 中南大学 | Antiskid braking control system for airplane |
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| CN106428533A (en) * | 2016-10-18 | 2017-02-22 | 西安航空制动科技有限公司 | Airplane inertia anti-skid brake system capable of guaranteeing emergency brake |
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| CN115783252A (en) * | 2023-02-08 | 2023-03-14 | 四川腾盾科技有限公司 | Low-cost unmanned aerial vehicle autonomous brake pressure control calculation method |
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