CN108146622B - Airplane fly-by-wire brake system using automatic brake switch and brake method - Google Patents
Airplane fly-by-wire brake system using automatic brake switch and brake method Download PDFInfo
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- CN108146622B CN108146622B CN201711272393.1A CN201711272393A CN108146622B CN 108146622 B CN108146622 B CN 108146622B CN 201711272393 A CN201711272393 A CN 201711272393A CN 108146622 B CN108146622 B CN 108146622B
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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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Abstract
An airplane fly-by-wire brake system using an automatic brake switch and a brake method. The brake command sensor, the control box, the electro-hydraulic servo valve and the speed sensor form a conventional brake system. The control box, the electro-hydraulic servo valve and the speed sensor form a conventional anti-skid control system. The automatic brake system consists of an automatic brake switch K or a first automatic brake switch K1, a second automatic brake switch K2, an electro-hydraulic servo valve, a restrictor, a one-way valve, a speed sensor and a control box. The invention brakes by 75-125% of the maximum brake pressure of the normal brake system, and inhibits the rapid rise of the initial hydraulic pressure of the automatic brake by the throttling device or the control box, thereby fully benefiting the combination torque provided by the runway to the maximum extent, shortening the landing running distance by about 35% compared with the conventional brake, ensuring the take-off and landing safety of the airplane, improving the utilization rate of the runway of the airport and the utilization rate of equipment, and having obvious economic, social and military benefits.
Description
Technical Field
The invention relates to an airplane wheel fly-by-wire brake system, in particular to an airplane fly-by-wire brake system with automatic braking capability.
Background
The airplane wheel braking system is a constituent part of a modern airplane landing gear, is basic guarantee equipment for safe operation of airplane take-off, landing and running and ground sliding operation, is used for shortening the running distance after the airplane lands, stopping the airplane as soon as possible and preventing tires from being broken off. Test research and use show that the landing and sliding distance of the airplane can be effectively shortened by adopting automatic braking under certain conditions. Automatic braking is also a long-felt desire to reduce the load on the driver at critical moments in landing safety. At present, a common airplane does not have automatic braking capability, and the airplane comprises an airplane adopting telex braking, a driver is required to step on a brake pedal or control a brake handle all the time during braking so as to operate a brake valve or a brake command sensor, only some airplane types such as Boeing, air passenger and the like, such as B737-700 and A320, are provided with automatic braking systems, and the airplane is automatically braked according to different deceleration rate levels. The foreign automatic brake system comprises an automatic brake selection switch, an automatic brake control box, an automatic brake servo valve and other accessories. Except that the pilot needs to operate the automatic brake selection switch to set the automatic brake gear before the takeoff, a series of state logics of the positions of the landing gear, the spoiler, the throttle lever and the like must completely meet the specified state logics, the automatic brake system is in a pre-positioned standby state, and the automatic brake system can be started to operate only when the aircraft lands or stops the takeoff. The automatic brake has the advantages of complex design and configuration, multiple faults, high difficulty in troubleshooting and positioning, low use reliability and potential safety hazards caused by multiple logic relations, so that a convenient and reliable automatic brake system needs to be provided, and the use technical safety requirements and the requirements of air and ground service personnel are met.
In the invention creation with application number 201610902427.X, an airplane fly-by-wire brake system for preventing improper use of emergency brake is disclosed; in the invention creation with the application number of 201610876509.1, an airplane fly-by-wire brake system of a brake instruction direct control type is disclosed; in the invention creation with the application number of 201610436991.7, an electric transmission brake system of airplane single-wheel double-brake capable of selecting a brake mode is disclosed; in the invention of application No. 201610436552.6, a fly-by-wire braking system capable of selecting a braking mode is disclosed; in the invention creation with application number 201610436698.0, an airplane single-wheel double-brake optional fly-by-wire brake system is disclosed; in the invention creation with application number 201610436553.0, an airplane wheel fly-by-wire brake system capable of selecting a braking mode is disclosed; in the invention of application No. 201310070226.4, an airplane telebrake system is disclosed, none of which has an automatic braking function.
In the invention creation with application number 201610906014.9, an aircraft inertia antiskid brake system ensuring emergency braking is disclosed; in the invention creation with application number 201610589061.5, an airplane brake antiskid control method and an airplane brake system are disclosed; in the invention creation with application number 201610436904.8, a dual brake system for airplane single wheel brake is disclosed; in the invention of application No. 201610436272.5, an aircraft wheel braking system for selecting taxi brakes based on brake pressure is disclosed; in the invention of application No. 201610436700.4, a brake system capable of selecting an airplane brake mode is disclosed; in the invention creation with application number 201510151374.8, an aircraft normal braking system with the flying lead braking capability is disclosed; in the invention with application number 201510152621.6, an aircraft hydraulic brake system is disclosed; in the invention with application number 201510152590.4, a normal braking system of an airplane is disclosed; in the invention creation with application number 201310070307.4, a hybrid aircraft brake system and a control method thereof are disclosed; in the invention creation with the application number of 201210053825.0, an airplane antiskid brake control system and a control method are disclosed, and the airplane brake systems disclosed do not have an automatic brake function.
Disclosure of Invention
The invention provides an airplane telex brake system using an automatic brake switch and a brake method, aiming at overcoming the defects of complex automatic brake design configuration, multiple faults, high troubleshooting positioning difficulty, low use reliability and potential safety hazard caused by multiple first-level logic relations existing in the conventional brake system.
The invention provides an airplane telex brake system using an automatic brake switch, which comprises a brake command sensor, an electro-hydraulic servo valve, a speed sensor and a control box, wherein the electro-hydraulic servo valve is connected with the brake command sensor; the brake command sensor, the control box, the electro-hydraulic servo valve and the speed sensor form a conventional brake system. The control box, the electro-hydraulic servo valve and the speed sensor form a conventional anti-skid control system. The method is characterized in that:
the I also comprises an automatic brake switch K, a restrictor and a one-way valve; when the fly-by-wire brake system of the airplane is a primary automatic brake system, one automatic brake switch K is arranged; when the fly-by-wire brake system of the airplane is a two-stage automatic brake system, two automatic brake switches K are provided, namely a first automatic brake switch K1 and a second automatic brake switch K2.
II, an automatic brake system is formed by the automatic brake switch K or the first automatic brake switch K1, the second automatic brake switch K2, the electro-hydraulic servo valve, the throttler, the one-way valve, the speed sensor and the control box. And: the automatic brake switch K or the first automatic brake switch K1 and the second automatic brake switch K2 are installed in the cockpit, are manually operated by a driver, provide enabling electric signals for switching on or off the automatic brake for the control box, control automatic brake current signals sent or not sent to the electro-hydraulic servo valve through the control box, and the electro-hydraulic servo valve brake port outputs hydraulic pressure to carry out automatic brake or the electro-hydraulic servo valve brake port returns oil without hydraulic pressure output to disconnect the automatic brake.
And III, the automatic braking system is a primary brake or a secondary brake.
In the first-stage automatic brake system, the negative end of an automatic brake switch K is communicated with the electrical input end of a control box; the electric input end of the electro-hydraulic servo valve is communicated with the electric output end of the control box; a brake port of the electro-hydraulic servo valve is communicated with an oil inlet of the restrictor; and an oil outlet of the throttler is communicated with an oil inlet pipeline of a brake device of the brake wheel. One hydraulic interface of the one-way valve is connected to a pipeline between the electro-hydraulic servo valve and the throttler, and the other hydraulic interface of the one-way valve is connected to a pipeline between the throttler and an oil inlet of a brake device of a brake wheel, so that the one-way valve is connected to pipelines at two ends of the throttler in parallel; the opening direction of the one-way valve is opposite to the flowing direction of hydraulic oil which is transmitted to the airplane wheel brake device.
In the two-stage automatic brake system, the negative terminal of the first automatic brake switch K1 and the negative terminal of the second automatic brake switch K2 are respectively communicated with the electrical input terminals of the control box. A brake port of the electro-hydraulic servo valve is communicated with an oil inlet of the restrictor; and an oil outlet of the throttler is communicated with an oil inlet pipeline of a brake device of the brake wheel. One hydraulic interface of the one-way valve is connected to a pipeline between the electro-hydraulic servo valve and the throttler, and the other hydraulic interface of the one-way valve is connected to a pipeline between the throttler and an oil inlet of a brake device of a brake wheel, so that the one-way valve is connected to pipelines at two ends of the throttler in parallel; the opening direction of the one-way valve is back to the flowing direction of the hydraulic oil which is conveyed to the airplane wheel brake device.
The throttle adopts a hole plate throttle and consists of a shell and a plurality of throttle hole plates arranged in the shell. Hydraulic oil flows through the plurality of throttle orifice plates to generate fluid resistance, so that the over-fast rising of the initial brake hydraulic pressure is limited when the automatic brake is switched on, the effect of smooth rising of pressure peak elimination is achieved, and the damage of the landing gear due to the brake moment spike is avoided.
The electro-hydraulic servo valve is a positive gain valve, and the hydraulic output pressure is in direct proportion to the control input current signal.
The braking process of the airplane fly-by-wire braking system using the automatic brake switch provided by the invention is as follows:
when the automatic braking level is one level, the automatic braking pressure is 100% of the maximum braking pressure of the normal braking system, and the automatic braking pressure is 10 MPa;
when the automatic braking level is two levels, the first level automatic braking pressure value is 100% of the maximum braking pressure of the normal braking system, and the automatic braking pressure is 10 MPa; the second-stage automatic braking pressure value is 125% of the maximum braking pressure of a normal braking system, and the automatic braking pressure is 12.5 MPa;
when the automatic braking level is one level, the contact of the automatic brake switch K is closed, thereby sending an automatic brake enable electric signal to the control box 3.
When the automatic braking level is two-level, the first automatic brake switch K1 and the second automatic brake switch K2 correspond to the automatic braking level and the automatic braking pressure respectively: the automatic brake switch contact of the first automatic brake switch K1 or the second automatic brake switch K2 is closed, so that the airplane automatic brake can be implemented by sending an automatic brake enabling electric signal to the control box.
when the automatic brake level is one level, the airplane stops landing and sliding or reaches a low-speed sliding speed, so that the contact of the automatic brake switch K is disconnected, the automatic brake enabling electric signal is disconnected, and the automatic brake of the airplane is released.
When the automatic brake level is two-stage, the airplane stops landing and runs or reaches a low-speed sliding speed, so that the contact of the automatic brake switch of the first automatic brake switch K1 or the second automatic brake switch K2 is disconnected, the automatic brake enabling electric signal is disconnected, and the automatic brake of the airplane is released.
In the automatic braking process, if the wheel of the brake skids, an electronic antiskid braking control system consisting of an electro-hydraulic servo valve, a speed sensor and a control box implements antiskid control.
The invention relies on the prior airplane telex normal braking system, a convenient and reliable automatic braking system is added in parallel, a manual switch arranged in a cockpit is used for switching on or switching off the automatic braking, an anti-skid control part of the normal braking system is used for anti-skid control, the normal braking system is used for braking at 75-125% of the maximum braking pressure, and a throttling device or a control box is used for inhibiting the excessive speed rise of the initial hydraulic pressure of the automatic braking.
In the invention, the automatic braking is a first-level or a second-level. For setting a secondary automatic brake, two automatic brake switches are mutually exclusive switched on, namely one switch is closed, the other switch cannot realize the switching-on circuit, and one switch is controlled by the other switch; the automatic brake is opened with a corresponding primary brake pressure.
Each automatic brake switch is arranged in the cockpit; the automatic brake switch is electrically connected with the control box through a cable; the automatic brake switch is manually operated by a driver, controls to provide an enabling electric signal for switching on or off the automatic brake for the control box, controls an automatic brake current signal sent to or not sent to the electro-hydraulic servo valve through the control box, outputs hydraulic pressure at a brake port of the electro-hydraulic servo valve to carry out automatic brake, or outputs no hydraulic pressure at an oil return port of the electro-hydraulic servo valve to switch off the automatic brake.
After the automatic brake manual switch is switched off, the automatic brake pressure is relieved, and a driver can shift to normal brake; when the vehicle is normally braked, a driver steps on a brake pedal to operate a sleeve of a brake command sensor, so that the brake command sensor outputs a corresponding brake command voltage signal to a control box, the control box generates a corresponding brake control current signal to an electro-hydraulic servo valve, and the electro-hydraulic servo valve outputs a corresponding brake pressure to be transmitted to a brake wheel for braking; the more the driver steps on the brake pedal, the larger the stroke is, the larger the brake command voltage signal output by the brake command sensor is, the larger the brake control current signal generated by the control box is, the larger the brake pressure output by the electro-hydraulic servo valve is, the higher the brake intensity is, and the faster the brake wheel decelerates.
The invention perfects and expands the operation selection range of the normal brake system, is beneficial to giving full play to the potential of the brake system, shortens the landing and sliding distance, stops the airplane as soon as possible, and safely exits the runway; the automatic brake system has the advantages that the automatic brake system is free of complex logic relations and components, reasonable and feasible in structure, flexible and convenient to use, high in reliability and the like, and has no problems that faults are high, safety accident potential and troubleshooting are hidden in complex logic relations, and the like existing in some existing civil aircrafts; the automatic braking level and the automatic braking pressure are set according to the actual use condition of the airplane, meanwhile, the braking torque generated by the automatic braking pressure does not damage the strength of the landing gear, and the combined torque provided by the runway is fully beneficial to the maximum extent, so that the landing sliding distance is shortened by about 35% in a braking mode using the automatic braking compared with the conventional braking, the takeoff and landing safety of the airplane is guaranteed, the utilization rate of the runway and the utilization rate of equipment of the airport are improved, and the economic, social and military benefits are obvious.
The invention can solve the defect that the conventional normal braking system of the airplane has no automatic braking capability, overcomes the problems of automatic braking of a civil airplane and meets the long-term expectation of people on automatic braking of the airplane.
Drawings
FIG. 1 is a schematic structural view of a brake system having a one-stage automatic brake according to the present invention;
FIG. 2 is a schematic structural diagram of a braking system with one-stage automatic braking according to the present invention. In the figure:
1. a brake command sensor; 2. an electro-hydraulic servo valve; 3. a control box; 4. a speed sensor; 5. braking the airplane wheel; 6. a one-way valve; 7. a restrictor; K. an automatic brake switch; K1. a first automatic brake switch; K2. and a second automatic brake switch.
Detailed Description
Example 1
See fig. 1. Modern aircraft nose landing gear wheels are generally not provided with brakes, and braking devices are arranged on the wheels of the two main landing gears. The two main landing gears of an aircraft are usually arranged symmetrically on both sides of the fuselage of the aircraft. The present embodiment illustrates an airplane electric hydraulic braking system with automatic braking capability, using one of the main landing gears and one of the wheels mounted.
The embodiment is a first-level automatic brake; the automatic braking antiskid valve adopts a shared antiskid valve, and an electro-hydraulic servo valve is used as the antiskid valve.
In this embodiment, the brake command sensor 1, the control box 3, the electro-hydraulic servo valve 2, and the speed sensor 4 constitute a conventional brake system. The control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional anti-skid control system.
This embodiment is an airplane telex hydraulic braking system with automatic braking ability, includes: the brake control system comprises a brake command sensor 1, a control box 3, an electro-hydraulic servo valve 2, an automatic brake switch K, a restrictor 7, a one-way valve 6 and a speed sensor 4. Wherein: the automatic brake switch K is arranged in the cockpit; the automatic brake switch K is electrically connected with the control box 3 through a cable; the automatic brake switch K is manually operated by a driver, provides an enabling electric signal for switching on or off the automatic brake for the control box 3, controls an automatic brake current signal sent or not sent to the electro-hydraulic servo valve 2 through the control box 3, and outputs hydraulic pressure at a brake port of the electro-hydraulic servo valve 2 to carry out the automatic brake or outputs no hydraulic pressure at a brake port of the electro-hydraulic servo valve 2 when the oil returns, thereby switching off the automatic brake.
The automatic brake switch K, the electro-hydraulic servo valve 2, the throttler 7, the one-way valve 6, the speed sensor 4 and the control box 3 form an automatic brake system. The electro-hydraulic servo valve 2, the speed sensor 4 and the control box 3 are common accessories for anti-slip control.
In the automatic braking system, the throttler 7 is provided with two hydraulic interfaces which are an oil inlet and an oil outlet respectively. The negative end of the automatic brake switch K is communicated with the electrical input end of the control box 3; the electric input end of the electro-hydraulic servo valve 2 is communicated with the electric output end of the control box 3; a brake port of the electro-hydraulic servo valve 2 is communicated with an oil inlet of the restrictor 7; and an oil outlet of the throttler 7 is communicated with an oil inlet pipeline of a brake device of the brake wheel 5. One hydraulic interface of the one-way valve 6 is connected to a pipeline between the electro-hydraulic servo valve 2 and the restrictor 7, and the other hydraulic interface of the one-way valve 6 is connected to a pipeline between the restrictor and an oil inlet of a brake device of the brake wheel 5, so that the one-way valve is connected to pipelines at two ends of the restrictor 7 in parallel; the check valve 6 is opened in the opposite direction to the flow of hydraulic oil to the wheel brake device.
The restrictor 7 adopts a orifice restrictor and consists of a shell and a plurality of orifice plates arranged in the shell. Hydraulic oil flows through the plurality of throttle orifice plates to generate fluid resistance, so that the over-fast rising of the initial brake hydraulic pressure is limited when the automatic brake is switched on, the effect of smooth rising of pressure peak elimination is achieved, and the damage of the landing gear due to the brake moment spike is avoided.
The one-way valve 6 is a ball valve. The check valve 6 is used for closing the check valve 6 during automatic braking, hydraulic oil from the upstream is blocked from passing through, and the hydraulic oil can only flow through the throttler 7 to be led to a braking device of the brake wheel 5; when the brake is released by the antiskid control of the automatic brake, the one-way valve 6 is opened, so that a bypass is provided for the return of hydraulic oil of the brake device of the brake wheel 5, and the hydraulic oil from the downstream can be returned by the one-way valve 6 without passing through the throttler 7, thereby accelerating the return speed and improving the antiskid control response of the automatic brake system.
The automatic brake switch K is a toggle switch. The automatic brake switch K is arranged in an automatic brake instruction input control circuit of the control box 3 or in an automatic brake current circuit which is output to the electro-hydraulic servo valve 2 by the control box 3, and controls to switch on or off an automatic brake current signal of the electro-hydraulic servo valve 2, and the automatic brake switch K sends an enabling electric signal to be implemented according to the prior art. The automatic brake switch K is arranged in the automatic brake circuit, and when the automatic brake switch K is operated to be closed, the automatic brake current is output to the electro-hydraulic servo valve 2 to carry out automatic braking, and the electro-hydraulic servo valve 2 outputs corresponding hydraulic brake pressure; when the automatic brake switch K is operated to be switched off, the automatic brake current cannot be output to the electro-hydraulic servo valve 2, and the electro-hydraulic servo valve 2 does not output hydraulic brake pressure.
In order to ensure the safe and reliable operation of the system, the electro-hydraulic servo valve 2 is provided with a hydraulic lock, and when braking, the electro-hydraulic servo valve firstly receives an unlocking electric signal sent by the control box 3 so as to connect the supply pressure of the electro-hydraulic servo valve 2 for supplying oil.
The detection of the speed of the airplane wheel is completed by an accessory of an airplane wheel speed sensor 4, and the sliding state of the airplane wheel is monitored; the antiskid control is completed by the control box 3; the electro-hydraulic servo valve 2 responds to a control current signal of the control box and outputs and adjusts the brake pressure transmitted to the brake wheel 5; the automatic braking is performed by the driver manually operating an automatic brake switch K.
The brake command sensor 1 is arranged below a bottom plate of a cockpit, is controlled by a driver to output a required brake command voltage signal, and then a control box 3 controls an electro-hydraulic servo valve 2 to output a required hydraulic brake pressure.
The maximum hydraulic pressure of the normal brake output of the brake command sensor 1 for operating the brake in the embodiment is 10 MPa.
The electro-hydraulic servo valve 2 is a positive gain valve, and the hydraulic output pressure is proportional to the control input current signal. The electro-hydraulic servo valve 2 has one electrical connection and three hydraulic connections. The three hydraulic interfaces are respectively an oil inlet, a brake port and an oil return port; wherein the oil inlet is connected with an oil inlet pipeline of a pressure supply source of the brake system; the brake port is connected with an oil inlet pipeline of a brake device of the brake wheel 5 through a flow restrictor 7; the oil return port is connected with an aircraft oil return pipeline. The electric interface is electrically connected with the control box 3 through a cable and receives braking and anti-skid control current signals sent by the control box 3.
The control box 3 is arranged in the main landing gear cabin and is powered by a power supply system on the airplane; the control box 3 has units of braking, anti-skid control, fault detection and the like, and has functions of braking, anti-skid control, fault detection and the like; the input end of an electrical interface of the control box 3 is respectively connected with the brake command sensor 1 and the airplane wheel speed sensor 4 through shielded insulated wires; the output end of the electrical interface of the control box 3 is connected with the electrical interface of the electro-hydraulic servo valve 2 through a shielding insulated lead;
the input end of the electrical interface of the control box 3 is also electrically connected with an automatic brake switch K;
therefore, the control box 3 receives the brake command signal sent by the brake command sensor 1 and also receives the automatic brake command signal sent by the automatic brake switch K; when an automatic braking instruction signal of the automatic braking switch K appears, a braking instruction signal sent by the braking instruction sensor 1 is invalid; namely, the enabling signal sent by the automatic brake switch K takes precedence; this arrangement can be achieved using existing techniques;
the wheel speed sensor 4 is arranged on the brake wheel and rotates with the brake wheel through mechanical transmission. The speed sensor 4 has an electrical interface electrically connected to the control box 3 by a cable.
The embodiment also provides an automatic braking method of the fly-by-wire hydraulic braking system with automatic braking capability, which comprises the following specific processes:
In the automatic braking process, if the brake wheel 5 slips, an electronic anti-skid brake control system consisting of the electro-hydraulic servo valve 2, the speed sensor 4 and the control box 3 implements anti-skid control.
In this embodiment, the driver manually pulls the handle of the automatic brake switch K to disconnect the contact of the automatic brake switch K, so as to disconnect the automatic brake enabling electric signal and release the automatic brake of the airplane.
In the automatic braking process, if normal braking of stepping on the brake is required, a driver only needs to manually turn off the automatic brake switch K, and the automatic brake of the airplane can be released.
The embodiment is provided with a first-level automatic brake, and the airplane landing and running brake suggests a preferred automatic brake mode to shorten the landing and running distance.
Example 2
See fig. 2. The embodiment is an airplane electric transmission hydraulic braking system with automatic braking capability, and is different from the technical scheme of the embodiment 1 in that the airplane electric transmission hydraulic braking system is a two-stage automatic brake.
The embodiment comprises a brake command sensor 1, a control box 3, an electro-hydraulic servo valve 2, a first automatic brake switch K1, a second automatic brake switch K2, a throttle 7, a one-way valve 6 and a speed sensor 4. The brake command sensor 1, the control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional brake system. The control box 3, the electro-hydraulic servo valve 2 and the speed sensor 4 form a conventional anti-skid control system. The automatic brake switch K, the electro-hydraulic servo valve 2, the throttler 7, the one-way valve 6, the speed sensor 4 and the control box 3 form an automatic brake system. The electro-hydraulic servo valve 2, the speed sensor 4 and the control box 3 are common accessories for anti-slip control.
The first automatic brake switch K1 and the second automatic brake switch K2 are arranged in the cockpit; the first automatic brake switch K1 and the second automatic brake switch K2 are electrically connected with the control box 3 through cables; the first automatic brake switch K1 and the second automatic brake switch K2 are manually operated by a driver, control is provided for the control box 3 to switch on or off an enabling electric signal of the automatic brake, the control box 3 controls an automatic brake current signal sent or not sent to the electro-hydraulic servo valve 2, the electro-hydraulic servo valve 2 outputs hydraulic pressure at a brake port to carry out automatic brake, or the electro-hydraulic servo valve 2 does not output hydraulic pressure at a brake port to return oil, and the automatic brake is switched off.
In the automatic brake system, the negative end of the first automatic brake switch K1 and the negative end of the second automatic brake switch K2 are respectively communicated with the electrical input ends of the control box 3. A brake port of the electro-hydraulic servo valve 2 is communicated with an oil inlet of the restrictor 7; and an oil outlet of the throttler 7 is communicated with an oil inlet pipeline of a brake device of the brake wheel 5. One hydraulic interface of the one-way valve 6 is connected to a pipeline between the electro-hydraulic servo valve 2 and the restrictor 7, and the other hydraulic interface of the one-way valve 6 is connected to a pipeline between the restrictor and an oil inlet of a brake device of the brake wheel 5, so that the one-way valve is connected to pipelines at two ends of the restrictor 7 in parallel; the opening direction of the check valve 6 is opposite to the flow direction of the hydraulic oil supplied to the wheel brake device.
The restrictor 7 has two hydraulic interfaces, which are an oil inlet and an oil outlet respectively. The first automatic brake switch K1 and the second automatic brake switch K2 are both toggle switches.
The automatic brake level of this embodiment is the second grade, has two automatic brake switches: a first automatic brake switch K1 and a second automatic brake switch K2. The first automatic brake switch K1 and the second automatic brake switch K2 are mutually exclusive and switched on, namely, one switch is closed, the other switch can not realize a closed switching-on circuit, and one switch is controlled by the other switch; the purpose is to prevent the problem of brake failure caused by abnormal switching of the switching valve due to misoperation of the two automatic brake switches.
The invention also provides a method for implementing secondary braking by using the airplane fly-by-wire hydraulic braking system with automatic braking capability, which comprises the following specific processes:
the driver manually pulls the shifting handle of the first automatic brake switch K1 or the second automatic brake switch K2 to close the operated automatic brake switch contact, so that the airplane can be automatically braked by sending an automatic brake enabling electric signal to the control box 3.
In the automatic braking process, if the brake wheel 5 slips, an electronic anti-slip brake control system consisting of the electro-hydraulic servo valve 2, the speed sensor 4 and the control box 3 implements anti-slip control;
in the automatic braking process, if normal braking of stepping on the brake is required, the automatic brake of the airplane can be released only by manually turning off an automatic brake switch by a driver.
Claims (2)
1. An airplane telex brake system using an automatic brake switch comprises a brake command sensor, an electro-hydraulic servo valve, a speed sensor and a control box; wherein, the brake command sensor, the control box, the electro-hydraulic servo valve and the speed sensor form a conventional brake system; the control box, the electro-hydraulic servo valve and the speed sensor form a conventional anti-skid control system; the method is characterized in that:
the I also comprises an automatic brake switch K, a restrictor and a one-way valve; when the fly-by-wire brake system of the airplane is a primary automatic brake system, one automatic brake switch K is arranged; when the fly-by-wire brake system of the airplane is a secondary automatic brake system, two automatic brake switches K are provided, namely a first automatic brake switch K1 and a second automatic brake switch K2;
II, an automatic brake system is formed by an automatic brake switch K or a first automatic brake switch K1 and a second automatic brake switch K2, an electro-hydraulic servo valve, a restrictor, a one-way valve, a speed sensor and a control box; and: the automatic brake switch K or the first automatic brake switch K1 and the second automatic brake switch K2 are installed in the cockpit, are manually operated by a driver, provide enabling electric signals for switching on or off the automatic brake for the control box, and control automatic brake current signals sent or not sent to the electro-hydraulic servo valve through the control box, the brake port of the electro-hydraulic servo valve outputs hydraulic pressure for automatic brake, or the oil returned by the brake port of the electro-hydraulic servo valve has no hydraulic pressure output, and the automatic brake is switched off;
III, the automatic braking system is a primary brake or a secondary brake;
the throttle adopts a hole plate throttle and consists of a shell and a plurality of throttle hole plates arranged in the shell; hydraulic oil flows through a plurality of throttle orifice plates to generate fluid resistance, so that the excessive speed rise of the initial brake hydraulic pressure is limited when the automatic brake is switched on, the effect of smooth rise of pressure peak elimination is achieved, and damage to the landing gear due to brake moment spikes is avoided;
in the first-stage automatic brake system, the negative end of an automatic brake switch K is communicated with the electrical input end of a control box; the electrical input end of the electro-hydraulic servo valve is communicated with the electrical output end of the control box; a brake port of the electro-hydraulic servo valve is communicated with an oil inlet of the restrictor; an oil outlet of the throttler is communicated with an oil inlet pipeline of a brake device of the brake wheel; one hydraulic interface of the one-way valve is connected to a pipeline between the electro-hydraulic servo valve and the throttler, and the other hydraulic interface of the one-way valve is connected to a pipeline between the throttler and an oil inlet of a brake device of a brake wheel, so that the one-way valve is connected to pipelines at two ends of the throttler in parallel; the opening direction of the one-way valve is opposite to the flowing direction of hydraulic oil conveyed to the airplane wheel brake device;
in the two-stage automatic brake system, the negative end of the first automatic brake switch K1 and the negative end of the second automatic brake switch K2 are respectively communicated with the electrical input ends of the control box; a brake port of the electro-hydraulic servo valve is communicated with an oil inlet of the restrictor; an oil outlet of the throttler is communicated with an oil inlet pipeline of a brake device of the brake wheel; one hydraulic interface of the one-way valve is connected to a pipeline between the electro-hydraulic servo valve and the throttler, and the other hydraulic interface of the one-way valve is connected to a pipeline between the throttler and an oil inlet of a brake device of a brake wheel, so that the one-way valve is connected to pipelines at two ends of the throttler in parallel; the opening direction of the one-way valve is back to the flowing direction of the hydraulic oil which is conveyed to the airplane wheel brake device.
2. A braking method using the fly-by-wire brake system for aircraft using an automatic brake switch according to claim 1, characterized by comprising the steps of:
step 1, setting an automatic braking grade and an automatic braking pressure;
when the automatic braking level is one level, the automatic braking pressure is 100% of the maximum braking pressure of the normal braking system, and the automatic braking pressure is 10 MPa;
when the automatic braking level is two levels, the first level automatic braking pressure value is 100% of the maximum braking pressure of the normal braking system, and the automatic braking pressure is 10 MPa; the second-stage automatic braking pressure value is 125% of the maximum braking pressure of a normal braking system, and the automatic braking pressure is 12.5 MPa;
step 2, switching on an automatic brake; when the aircraft lands to reach the braking speed, the switch is manually closed to implement aircraft braking;
when the automatic braking level is one level, the contact of the automatic braking switch K is closed, so that an automatic braking enabling electric signal is sent to the control box 3;
when the automatic braking level is two-level, the first automatic brake switch K1 and the second automatic brake switch K2 correspond to the automatic braking level and the automatic braking pressure respectively: the contact of the automatic brake switch of the first automatic brake switch K1 or the second automatic brake switch K2 is closed, so that the airplane can be automatically braked by sending an automatic brake enabling electric signal to the control box;
step 3, disconnecting the automatic brake;
when the automatic brake level is one level, the landing sliding of the airplane stops or the low-speed sliding speed is reached, so that the contact of the automatic brake switch K is disconnected, the automatic brake enabling electric signal is disconnected, and the automatic brake of the airplane is released;
when the automatic brake level is two-stage, the airplane stops landing and sliding or reaches a low-speed sliding speed, so that the contact of the automatic brake switch of the first automatic brake switch K1 or the second automatic brake switch K2 is disconnected, the automatic brake enabling electric signal is disconnected, and the automatic brake of the airplane is released;
in the automatic braking process, if the wheel of the brake skids, an electronic antiskid braking control system consisting of an electro-hydraulic servo valve, a speed sensor and a control box implements antiskid 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 |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711272393.1A 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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| Publication Number | Publication Date |
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| CN108146622A CN108146622A (en) | 2018-06-12 |
| CN108146622B true CN108146622B (en) | 2021-01-05 |
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| US2826278A (en) * | 1954-04-20 | 1958-03-11 | Goodyear Tire & Rubber | Hydraulic apparatus for anti-skid or manual control of brakes with safety lockout of anti-skid control |
| 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 |
| CN102180156B (en) * | 2011-04-18 | 2013-01-09 | 中南大学 | Antiskid braking control system for airplane |
| CN105626602A (en) * | 2016-02-26 | 2016-06-01 | 武汉船用机械有限责任公司 | Control system for anchoring speed of anchor machine |
| CN106081073B (en) * | 2016-06-17 | 2018-03-02 | 西安航空制动科技有限公司 | A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake |
| CN106428533B (en) * | 2016-10-18 | 2018-10-23 | 西安航空制动科技有限公司 | A kind of airplane inertial anti-skid brake system (ABS) ensuring emergency brake |
| CN107352020B (en) * | 2017-06-29 | 2019-11-22 | 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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