CN117360769A - Helicopter brake pressure control system and control method - Google Patents
Helicopter brake pressure control system and control method Download PDFInfo
- Publication number
- CN117360769A CN117360769A CN202311320883.XA CN202311320883A CN117360769A CN 117360769 A CN117360769 A CN 117360769A CN 202311320883 A CN202311320883 A CN 202311320883A CN 117360769 A CN117360769 A CN 117360769A
- Authority
- CN
- China
- Prior art keywords
- brake
- sensor
- pressure
- brake command
- servo valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 24
- 239000003921 oil Substances 0.000 claims description 29
- 230000003068 static effect Effects 0.000 claims description 11
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000007792 addition Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
Abstract
The invention relates to the field of anti-skid brake systems of helicopters, in particular to a helicopter brake pressure control system and a control method; the hydraulic brake system comprises a brake instruction sensor, a brake switch, an electrohydraulic pressure servo valve, an electromagnetic hydraulic lock, a hydraulic oil return pipeline, a brake pedal and a hydraulic oil inlet pipeline; and comprises the following steps: s1, determining a micro switch control logic of a brake instruction sensor; s2, determining that a brake command sensor outputs brake command voltage; s3, determining that the brake command sensor outputs brake command voltage; s4, determining the brake pressure output by the electrohydraulic pressure servo valve; the invention solves the problem that the electrohydraulic servo valve cannot be maintained because the control of the brake command sensor on the hydraulic source is not realized in the prior art; even if the electrohydraulic servo valve is blocked in the braking process, the braking system can not release the braking pressure, and the problem of tire burst of the brake machine is easily caused.
Description
Technical Field
The invention relates to the field of anti-skid brake systems of helicopters, in particular to a helicopter brake pressure control system and a control method.
Background
The prior art digital electric brake system technology is widely used in aircraft anti-skid brake systems, and a schematic block diagram of a typical digital electric anti-skid brake system is shown in fig. 1. The system consists of a brake instruction sensor 1, a brake control box 11, an electrohydraulic pressure servo valve 3, an electromagnetic hydraulic lock 4, a hydraulic oil return pipeline 5, a brake pedal 6, a brake switch 2 and a hydraulic oil inlet pipeline 7, and realizes the braking function of an airplane;
the brake instruction sensor 1 is an accessory of the digital electric brake system of the aircraft, the brake instruction sensor 1 is hinged with the brake pedal 6, the pilot steps on the brake pedal to drive the brake instruction sensor bracket to move, the brake instruction sensor 1 outputs a direct-current voltage signal which is in direct proportion to the stroke, namely a brake instruction signal, to the brake control box 11, the brake control box 11 outputs a lock control signal of the electromagnetic hydraulic lock 4, meanwhile, the brake control box 11 outputs a valve current signal to the electrohydraulic pressure servo valve 4, and the electrohydraulic pressure servo valve 4 outputs brake pressure which is in direct proportion to the valve current to brake. The brake switch 2 is disconnected, so that the aim of cutting off the anti-skid brake system of the aircraft is fulfilled;
the invention creation of the publication No. CN106394525A discloses a brake instruction direct control type aircraft electric brake system, which comprises a brake instruction sensor, a brake control valve, a brake control box and a speed sensor; the brake command voltage signal sent by the brake command sensor does not pass through the brake control box and directly reaches the brake control valve, and the brake control valve is directly controlled to brake the aircraft electric brake control system; the brake command voltage signal output by the brake command sensor is directly transmitted to a brake control valve, namely an electrohydraulic servo valve, and the electrohydraulic servo valve outputs hydraulic brake pressure in direct proportion to the brake command electric signal to brake. When the wheel of the brake is slipped or locked, the brake control box sends an anti-slip valve current signal with the opposite direction to the brake command current to the brake control valve so as to reduce the valve current of the brake control valve, thereby reducing the brake pressure, relieving the slipping or locking of the wheel and avoiding the tire burst;
the prior art mentions that the brake command electric signal sent by the brake command sensor directly controls the brake control valve, and the electrohydraulic servo valve outputs brake pressure in direct proportion to the brake command electric signal; however, the control requirement of the brake command sensor on the electromagnetic hydraulic lock is not described in the invention, and the control of the brake command sensor on the hydraulic source is not realized, if the electrohydraulic servo valve fails, the hydraulic source cannot be disconnected through the electromagnetic hydraulic lock, so that the electrohydraulic servo valve cannot be maintained; if the electrohydraulic servo valve is blocked in the braking process, the braking system can not release the braking pressure, and the tire burst of the brake machine is easy to cause; has serious potential safety hazard.
Disclosure of Invention
The invention aims to provide a helicopter brake pressure control system and a control method for solving the technical problems.
In order to achieve the above object, the present invention provides the following technical solutions;
a helicopter brake pressure control system comprises a brake instruction sensor, a brake switch, an electrohydraulic pressure servo valve, an electromagnetic hydraulic lock, a hydraulic oil return pipeline, a brake pedal and a hydraulic oil inlet pipeline; the mounting bracket of the brake instruction sensor is connected with the brake pedal; the braking instruction sensor controls the electromagnetic hydraulic lock and the electrohydraulic pressure servo valve to realize helicopter braking;
the input port of the electromagnetic hydraulic lock is communicated with the hydraulic oil inlet pipeline, and the working oil port of the electromagnetic hydraulic lock is communicated with the input oil port of the electrohydraulic pressure servo valve; the working oil port of the electrohydraulic pressure servo valve is communicated with the brake port of the brake device of the brake wheel, and the oil return port of the electrohydraulic pressure servo valve is communicated with the oil tank; the electromagnetic hydraulic lock oil return port is communicated with the oil tank through a hydraulic oil return pipeline;
further, the input end of the brake switch is connected with the VDC power supply end; the input end of the micro switch in the brake instruction sensor is connected with the output end of the brake switch; the output end of the micro switch in the instruction sensor is connected with the input end of the electromagnetic coil of the electromagnetic hydraulic lock; the output end of the electromagnetic coil of the electromagnetic hydraulic lock is connected with the ground;
a helicopter brake pressure control system and a control method are applied to the system, and comprise the following steps:
s1, determining a micro-switch control logic of a brake instruction sensor, and judging the state of the micro-switch; the brake instruction sensor comprises a free travel, a working travel and a total travel; when the brake command sensor is in idle stroke, the micro switch is disconnected to enable the electromagnetic hydraulic lock to be closed and the aircraft brake system to disconnect a hydraulic source, so that the normal brake function of the aircraft is lost; when the working stroke of the brake command sensor is larger than the idle stroke and smaller than the total stroke, the micro switch is connected with the electromagnetic hydraulic lock to unlock, the hydraulic source of the aircraft brake system is connected, and the brake system has a normal brake function; determining a brake command sensor micro-switch control logic through a formula A:
s is the state of a micro switch of a brake instruction sensor; 1, a micro switch is turned on; 0 is the disconnection of the microswitch; l (L) S Is the working stroke of a brake command sensor; l (L) SO Is the idle stroke of the brake command sensor;
s2, determining that a brake command sensor outputs brake command voltage; when the working stroke of the brake command sensor is idle stroke, the brake command sensor outputs idle stroke voltage V SO The method comprises the steps of carrying out a first treatment on the surface of the When the working stroke of the brake command sensor is larger than the idle stroke but smaller than the total stroke, the brake command sensor outputs a brake command voltage V S The method comprises the steps of carrying out a first treatment on the surface of the The brake command sensor outputs a brake command voltage V S In direct proportion to the working stroke of the brake command sensor, the brake command voltage V S The relation between the brake command sensor and the working stroke of the brake command sensor is specifically shown in a formula B:
V S is a brake command voltage; v (V) SO Is the idle stroke voltage of the brake command sensor; k (K) 1 The brake command voltage and the travel gain;
s3, determining the output valve current of the brake command sensor; the brake command sensor outputs brake command voltage to a V-I conversion circuit in the product to output valve current I F With brake command voltage V S Proportional to the ratio. Brake command voltage V S And valve current I F The relationship is shown in formula C:
I F is valve current; i FO Is the static valve current; k (K) 2 Is the valve current-voltage gain;
s4, determining the brake pressure output by the electrohydraulic pressure servo valve; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation;
when the brake command sensor is idle stroke, the idle stroke voltage of the brake command sensor is V SO The static valve current output by the anti-skid brake control box is I FO The braking pressure output by the electrohydraulic pressure servo valve is the oil return pressure P of the anti-skid braking system O The method comprises the steps of carrying out a first treatment on the surface of the When the brake command sensor is in the working stroke, the voltage V of the brake command sensor S Output valve current I of anti-skid brake control box F The electrohydraulic pressure servo valve outputs brake pressure P and valve current I F Proportional to the ratio;
the electrohydraulic pressure servo valve outputs brake pressure P and valve current I of anti-skid brake control box F The relationship is shown in formula D:
p electrohydraulic pressure servo valve outputs brake pressure, P O Oil return pressure of the anti-skid braking system;
further, the brake command voltage determined in S2: when the brake command sensor is in working strokeAt the time, the brake command sensor is at idle stroke voltage +.> When the working stroke of the brake command sensor is +.>At the time of braking command voltage +.>
Furthermore, under the condition that a brake pedal is not used, a micro switch in the brake command sensor is disconnected, an electromagnetic hydraulic lock tube is locked, and a brake system cuts off a hydraulic oil source; the brake command sensor is at an initial position, and the brake command outputs static valve current to enable the electrohydraulic pressure servo valve to output oil return pressure of a brake system, so that normal braking function of the aircraft is lost;
further, after the brake pedal is used, when the working stroke of the brake command sensor is larger than the idle stroke and smaller than the total stroke, the micro switch is turned on, the electromagnetic hydraulic lock is unlocked, the hydraulic source of the aircraft brake system is turned on, and the hydraulic oil source of the brake system is turned on for pressure supply; in the working stroke of the brake command sensor, the brake command outputs valve current, so that the output brake pressure of the electrohydraulic pressure servo valve is controlled in proportion to the stroke of the brake command sensor;
further, after the brake pedal is used, when the working stroke of the brake command sensor is larger than the maximum working stroke, the output valve current of the brake command sensor is constant maximum valve current, and the electrohydraulic pressure servo valve outputs maximum brake pressure; the braking system has a normal braking function;
compared with the prior art, the invention has the following beneficial effects:
according to the invention, the micro switch and the voltage-current conversion module are added in the brake command sensor, so that the on-off control of the electromagnetic hydraulic lock of the helicopter brake system controlled by the brake command sensor is realized, and the electrohydraulic pressure servo valve outputs brake pressure control; the hydraulic servo valve solves the problem that in the prior art, the control of a brake command sensor on a hydraulic source is not realized, so that the electrohydraulic servo valve cannot be maintained; even if the electrohydraulic servo valve is blocked in the braking process, the braking system can not release the braking pressure, and the problem of tire burst of the brake machine is easily caused.
Drawings
FIG. 1 is a schematic block diagram of a prior art digital electric brake system;
FIG. 2 is a system schematic block diagram of the present invention;
reference numerals: the hydraulic brake system comprises a brake instruction sensor 1, a brake switch 2, an electrohydraulic pressure servo valve 3, an electromagnetic hydraulic lock 4, a hydraulic oil return pipeline 5, a brake pedal 6 and a hydraulic oil inlet pipeline 7.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Referring to fig. 2, a system for controlling braking pressure of a helicopter by a braking instruction sensor is shown, wherein the braking instruction sensor 1, a braking switch 2, an electrohydraulic pressure servo valve 3, an electromagnetic hydraulic lock 4, a hydraulic oil return pipeline 5, a braking pedal 6 and a hydraulic oil inlet pipeline 7; the brake finger electromagnetic hydraulic lock 4 and the electrohydraulic pressure servo valve 3 realize helicopter braking;
the electromagnetic hydraulic lock 4 enables the mounting bracket of the sensor 1 to be connected with the brake pedal 6; an input port controlled by the brake command sensor 1 is communicated with a hydraulic oil inlet pipeline 7, and a working oil port of the electromagnetic hydraulic lock 4 is communicated with an input oil port of the electrohydraulic pressure servo valve 3; the working oil port of the electrohydraulic pressure servo valve 3 is communicated with the brake port of a brake device of a brake wheel, and the oil return port of the electrohydraulic pressure servo valve 3 is communicated with an oil tank; the oil return port of the electromagnetic hydraulic lock 4 is communicated with an oil tank through a hydraulic oil return pipeline 5.
Further, the input end of the brake switch 2 is connected with a 28VDC power end; the input end of a micro switch in the brake instruction sensor 1 is connected with the output end of a brake switch 2; the output end of the micro switch in the instruction sensor 1 is connected with the input end of the electromagnetic coil of the electromagnetic hydraulic lock 4; the output end of the electromagnetic coil of the electromagnetic hydraulic lock 4 is connected with the ground.
In the embodiment, a valve control signal of the brake command sensor 1 is a direct current signal in direct proportion to a stroke, and a valve control signal output end of the brake command sensor 1 is connected with a pressure control signal input end of the electrohydraulic pressure servo valve 3; the output end of the pressure control signal of the electrohydraulic pressure servo valve 3 is connected with the ground.
The brake command sensor 1 controls the electromagnetic hydraulic lock 4, and the hydraulic source is controlled by the brake command sensor through the connection or disconnection of a micro switch in the electromagnetic hydraulic lock 4, so that the input pressure control of a brake system is realized; the brake command sensor 1 outputs a direct current signal in direct proportion to the stroke, and the electrohydraulic pressure servo valve 3 outputs brake pressure control.
When a pilot steps on a brake pedal 6 to drive a bracket of the brake instruction sensor 1 to move, the micro switch is connected, the brake instruction sensor 1 outputs a lock control signal to be connected with an electromagnetic coil of the electromagnetic hydraulic lock 4, and the electromagnetic hydraulic lock 4 is unlocked and connected with a hydraulic source; meanwhile, the brake command sensor 1 outputs a direct current signal (valve current) in direct proportion to the stroke to the electrohydraulic servo valve 3, and the electrohydraulic servo valve 3 outputs brake pressure in direct proportion to the valve current to brake.
When an aircraft operator does not step on a brake pedal, the brake pedal and the brake instruction sensor 1 are in an initial position, a micro switch on the brake instruction sensor 1 is disconnected, a lock control signal output by the brake instruction sensor 1 disappears, an electromagnetic coil of the electromagnetic hydraulic lock 4 is powered off, and the electromagnetic hydraulic lock 4 is closed and a hydraulic source is disconnected; meanwhile, the brake command sensor 1 outputs a static direct current signal which is in direct proportion to the stroke to the electrohydraulic pressure servo valve 3, the electrohydraulic pressure servo valve 3 outputs zero brake pressure, and the brake system outputs zero brake pressure.
A method for controlling the braking pressure of a helicopter by a braking instruction sensor is applied to the system and comprises the following steps:
s1, determining a micro-switch control logic of a brake instruction sensor, and judging the state of the micro-switch; the brake instruction sensor comprises a free travel, a working travel and a total travel; when the brake command sensor is in idle stroke, the micro switch is disconnected to enable the electromagnetic hydraulic lock to be closed and the aircraft brake system to disconnect a hydraulic source, so that the normal brake function of the aircraft is lost; when the working stroke of the brake command sensor is larger than the idle stroke and smaller than the total stroke, the micro switch is connected with the electromagnetic hydraulic lock to unlock, the hydraulic source of the aircraft brake system is connected, and the brake system has a normal brake function; determining a brake command sensor micro-switch control logic through a formula A:
s is the state of a micro switch of a brake instruction sensor; 1, a micro switch is turned on; 0 is the disconnection of the microswitch; l (L) S Is the working stroke of a brake command sensor; l (L) SO Is the idle stroke of the brake command sensor;
s2, determining that a brake command sensor outputs brake command voltage; when the working stroke of the brake command sensor is idle stroke, the brake command sensor outputs idle stroke voltage V SO The method comprises the steps of carrying out a first treatment on the surface of the When the working stroke of the brake command sensor is larger than the idle stroke but smaller than the total stroke, the brake command sensor outputs a brake command voltage V S The method comprises the steps of carrying out a first treatment on the surface of the The brake command sensor outputs a brake command voltage V S In direct proportion to the working stroke of the brake command sensor, the brake command voltage V S The relation between the brake command sensor and the working stroke of the brake command sensor is specifically shown in a formula B:
V S is a brake command voltage; v (V) SO Is the idle stroke voltage of the brake command sensor; k (K) 1 The brake command voltage and the travel gain;
when brake instruction sensorTravel inDuring the time, the brake command sensor idle stroke voltageWhen the working stroke of the brake command sensor is +.> When braking command voltage
S3, determining the output valve current of the brake command sensor; the brake command sensor outputs brake command voltage to a V-I conversion circuit in the product to output valve current I F With brake command voltage V S Proportional to the ratio. Brake command voltage V S And valve current I F The relationship is shown in formula C:
I F is valve current; i FO Is the static valve current; k (K) 2 Is the valve current-voltage gain;
s4, determining the brake pressure output by the electrohydraulic pressure servo valve; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation;
when the brake command sensor is idle stroke, the idle stroke voltage of the brake command sensor is V SO The static valve current output by the anti-skid brake control box is I FO The braking pressure output by the electrohydraulic pressure servo valve is the oil return pressure P of the anti-skid braking system O The method comprises the steps of carrying out a first treatment on the surface of the When the brake command sensor is in the working stroke, the voltage V of the brake command sensor S Output valve current I of anti-skid brake control box F The electrohydraulic pressure servo valve outputs brake pressure P and valve current I F Proportional to the ratio;
the electrohydraulic pressure servo valve outputs brake pressure P and valve current I of anti-skid brake control box F The relationship is shown in formula D:
p electrohydraulic pressure servo valve outputs brake pressure, P O Oil return pressure of the anti-skid braking system;
further, the brake command voltage determined in S2: when the brake command sensor is in working strokeAt the time, the brake command sensor is at idle stroke voltage +.> When the working stroke of the brake command sensor is +.>At the time of braking command voltage +.>
The pressure current gain K of the electrohydraulic pressure servo valve 3 ＝0.5667MPa/mA；
When the brake command sensor is working strokeWhen the brake command voltage is +.> The current of the static valve output by the anti-skid brake control box is +.>The output brake pressure of the electrohydraulic pressure servo valve is 1.2MPa;
when the brake command sensor is working strokeWhen the brake command voltage isThe valve current of the anti-skid brake control box is +.> The output brake pressure of the electrohydraulic pressure servo valve is +.>
When the brake command sensor is working strokeWhen the brake command voltage is +.> The current of the output valve of the anti-skid brake control box is +.>The output brake pressure of the electrohydraulic pressure servo valve is +.>
Furthermore, under the condition that a brake pedal is not used, a micro switch in the brake command sensor is disconnected, an electromagnetic hydraulic lock tube is locked, and a brake system cuts off a hydraulic oil source; the brake command sensor is at an initial position, and the brake command outputs static valve current to enable the electrohydraulic pressure servo valve to output oil return pressure of a brake system, so that normal braking function of the aircraft is lost;
further, after the brake pedal is used, when the working stroke of the brake command sensor is larger than the idle stroke and smaller than the total stroke, the micro switch is turned on, the electromagnetic hydraulic lock is unlocked, the hydraulic source of the aircraft brake system is turned on, and the hydraulic oil source of the brake system is turned on for pressure supply; in the working stroke of the brake command sensor, the brake command outputs valve current, so that the output brake pressure of the electrohydraulic pressure servo valve is controlled in proportion to the stroke of the brake command sensor;
further, after the brake pedal is used, when the working stroke of the brake command sensor is larger than the maximum working stroke, the output valve current of the brake command sensor is constant maximum valve current, and the electrohydraulic pressure servo valve outputs maximum brake pressure; the braking system has a normal braking function;
according to the invention, the micro switch and the voltage-current conversion module are added in the brake command sensor, so that the on-off control of the electromagnetic hydraulic lock of the helicopter brake system controlled by the brake command sensor is realized, and the electrohydraulic pressure servo valve outputs brake pressure control; the hydraulic servo valve solves the problem that in the prior art, the control of a brake command sensor on a hydraulic source is not realized, so that the electrohydraulic servo valve cannot be maintained; even if the electrohydraulic servo valve is blocked in the braking process, the braking system can not release the braking pressure, and the problem of tire burst of the brake machine is easily caused.
The specific embodiments described herein are offered by way of example only to illustrate the spirit of the invention. Those skilled in the art may make various modifications or additions to the described embodiments or substitutions thereof without departing from the scope of the invention as defined in the accompanying claims.
Claims (7)
1. The helicopter brake pressure control system is characterized by comprising a brake instruction sensor (1), a brake switch (2), an electrohydraulic pressure servo valve (3), an electromagnetic hydraulic lock (4), a hydraulic oil return pipeline (5), a brake pedal (6) and a hydraulic oil inlet pipeline (7); the mounting bracket of the brake instruction sensor (1) is connected with a brake pedal (6); the brake instruction sensor (1) controls the electromagnetic hydraulic lock (4) and the electrohydraulic pressure servo valve (3) to realize helicopter braking;
an input port of the electromagnetic hydraulic lock (4) is communicated with a hydraulic oil inlet pipeline (7), and a working oil port of the electromagnetic hydraulic lock (4) is communicated with an input oil port of the electrohydraulic pressure servo valve (3); the working oil port of the electrohydraulic pressure servo valve (3) is communicated with the brake port of the brake device of the brake wheel, and the oil return port of the electrohydraulic pressure servo valve (3) is communicated with the oil tank; the oil return port of the electromagnetic hydraulic lock (4) is communicated with the oil tank through a hydraulic oil return pipeline (5).
2. A helicopter brake pressure control system as claimed in claim 2, wherein the input of said brake switch (2) is connected to a 28VDC power supply; the input end of the micro switch in the brake instruction sensor (1) is connected with the output end of the brake switch (2); the output end of the micro switch in the instruction sensor (1) is connected with the input end of the electromagnetic coil of the electromagnetic hydraulic lock (4); the output end of the electromagnetic coil of the electromagnetic hydraulic lock (4) is connected with the ground.
3. A method for controlling braking pressure of a helicopter, applied to a system according to any one of claims 1-2, characterized by comprising the following steps:
s1, determining a micro-switch control logic of a brake instruction sensor, and judging the state of the micro-switch; determining a brake command sensor micro-switch control logic by the formula (A):
s is the state of a micro switch of a brake instruction sensor; 1, a micro switch is turned on; 0 is the disconnection of the microswitch; l (L) S Is the working stroke of a brake command sensor; l (L) SO Is the idle stroke of the brake command sensor;
s2, determining that a brake command sensor outputs brake command voltage; the brake command sensor outputs a brake command voltage V S In direct proportion to the working stroke of the brake command sensor, the brake command voltage V S The relation between the brake command sensor and the working stroke of the brake command sensor is specifically shown in a formula (B):
V S is a brake command voltage; v (V) SO Is the idle stroke voltage of the brake command sensor; k (K) 1 The brake command voltage and the travel gain;
s3, determining the output valve current of the brake command sensor; the brake command sensor outputs brake command voltage to a V-I conversion circuit in the product to output valve current I F With brake command voltage V S Proportional to the ratio. Brake command voltage V S And valve current I F The relation is shown in formula (C):
I F is valve current; i FO Is the static valve current; k (K) 2 Is the valve current-voltage gain;
s4, determining the brake pressure output by the electrohydraulic pressure servo valve; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation; the brake pressure output by the electrohydraulic pressure servo valve is determined by the valve current of the anti-skid brake control box; the valve current of the anti-skid brake control box and the brake pressure output by the electrohydraulic pressure servo valve form a positive linear relation;
the electrohydraulic pressure servo valve outputs brake pressure P and valve current I of anti-skid brake control box F The relation is shown in formula (D):
wherein: i F Valve current, I FO Static valve current; k (K) 3 The electrohydraulic pressure servo valve pressure current gain; p electrohydraulic pressure servo valve outputs brake pressure, P O Oil return pressure of the anti-skid braking system.
4. A helicopter brake pressure control method as claimed in claim 3, wherein the brake command voltage determined in S2: when the brake command sensor is in working strokeAt the time, the brake command sensor is at idle stroke voltage +.>When the working stroke of the brake command sensor is +.>When braking command voltage
5. A helicopter brake pressure control method as claimed in claim 3 wherein, in the case of no brake pedal, a micro switch in said brake command sensor is turned off, an electromagnetic hydraulic lock tube is locked, and a brake system shuts off a hydraulic oil source; and the brake command sensor is at the initial position, and the brake command outputs static valve current, so that the electrohydraulic pressure servo valve outputs return oil pressure of a brake system, and the normal brake function of the aircraft is lost.
6. A helicopter brake pressure control method according to claim 3, wherein after the brake pedal is used, when the working stroke of the brake command sensor is larger than the idle stroke and smaller than the total stroke, the micro switch is turned on, the electromagnetic hydraulic lock is unlocked, the hydraulic source of the aircraft brake system is turned on, and the hydraulic oil source of the brake system is turned on for pressure supply; and in the working stroke of the brake command sensor, the brake command outputs valve current, so that the output brake pressure of the electrohydraulic pressure servo valve is controlled in proportion to the stroke of the brake command sensor.
7. A helicopter brake pressure control method as claimed in claim 3 wherein said brake command sensor outputs a constant maximum valve current when said brake command sensor has a working stroke greater than a maximum working stroke after the brake pedal is applied, said electrohydraulic pressure servo valve outputs a maximum brake pressure, and said brake system has a normal braking function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311320883.XA CN117360769A (en) | 2023-10-12 | 2023-10-12 | Helicopter brake pressure control system and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311320883.XA CN117360769A (en) | 2023-10-12 | 2023-10-12 | Helicopter brake pressure control system and control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117360769A true CN117360769A (en) | 2024-01-09 |
Family
ID=89397625
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311320883.XA Pending CN117360769A (en) | 2023-10-12 | 2023-10-12 | Helicopter brake pressure control system and control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117360769A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0614805A1 (en) * | 1993-03-08 | 1994-09-14 | Messier Bugatti | Electrohydraulic braking device for the landing gear of a aircraft |
| JP2012183995A (en) * | 2011-03-04 | 2012-09-27 | Messier-Bugatti-Dowty | Hydraulic brake architecture for aircraft for braking at least one wheel of the aircraft |
| CN109533301A (en) * | 2018-12-11 | 2019-03-29 | 中航工业南京伺服控制系统有限公司 | A kind of aircraft brake system |
| CN209051583U (en) * | 2018-10-12 | 2019-07-02 | 西安航空制动科技有限公司 | A kind of emergency brake system can be realized long-range control |
| CN110525405A (en) * | 2019-09-09 | 2019-12-03 | 西安航空制动科技有限公司 | The brake system and design method of hydraulic power source are controlled by brake instruction transducer |
-
2023
- 2023-10-12 CN CN202311320883.XA patent/CN117360769A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0614805A1 (en) * | 1993-03-08 | 1994-09-14 | Messier Bugatti | Electrohydraulic braking device for the landing gear of a aircraft |
| JP2012183995A (en) * | 2011-03-04 | 2012-09-27 | Messier-Bugatti-Dowty | Hydraulic brake architecture for aircraft for braking at least one wheel of the aircraft |
| CN209051583U (en) * | 2018-10-12 | 2019-07-02 | 西安航空制动科技有限公司 | A kind of emergency brake system can be realized long-range control |
| CN109533301A (en) * | 2018-12-11 | 2019-03-29 | 中航工业南京伺服控制系统有限公司 | A kind of aircraft brake system |
| CN110525405A (en) * | 2019-09-09 | 2019-12-03 | 西安航空制动科技有限公司 | The brake system and design method of hydraulic power source are controlled by brake instruction transducer |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111971214B (en) | Hydraulic motor vehicle braking system and method for operating same | |
| CN111971213B (en) | Hydraulic brake system for motor vehicle | |
| CN107804453B (en) | Linear control method for static brake pressure of digital electric transmission anti-skid brake system | |
| CN111954614A (en) | Hydraulic motor vehicle braking system and method for operating same | |
| US3544171A (en) | Anti-skid device for hydraulic brake system | |
| JPH01229755A (en) | Anti-lock control hydraulic brake system | |
| EP0186221B1 (en) | Aircraft wheel brake control system and method | |
| CN104760693B (en) | A kind of inertia anti-skid brake system (ABS) and the determination method of control condition | |
| JPH01136858A (en) | Control method for brake fluid pressure of hydraulic brake device of automobile | |
| CN109305342A (en) | A kind of emergency brake system and its design method of long-range control | |
| CN117360769A (en) | Helicopter brake pressure control system and control method | |
| CN105857281A (en) | Anti-lock braking system (ABS)/anti-skip regulation (ASR) integrated hydraulic system of off-highway mechanical drivedumper | |
| CN106364668B (en) | It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake | |
| CN105438453A (en) | Aircraft static brake and protection system thereof | |
| CN110203379B (en) | Aircraft brake system with air residual pressure warning function and control method | |
| CN218907207U (en) | Mining vehicle braking anti-lock control system | |
| US8777332B2 (en) | Braking control system | |
| US4198102A (en) | Automatic system pressure shut off valve for anti-skid control system | |
| US5282676A (en) | Combined antiskid and traction control electronic brake system | |
| CN110606195B (en) | Airplane emergency braking system and design method thereof | |
| US3552802A (en) | Means for preventing skidding of vehicle wheels | |
| CN209051583U (en) | A kind of emergency brake system can be realized long-range control | |
| CN111038465B (en) | Integrated brake-by-wire system for vehicle and control method | |
| CN107882821A (en) | Dual-way vehicle latch bridge hydraulic system | |
| EP0137915B1 (en) | Fail-safe brake |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |