CN113978706B - Power-on self-checking logic control method for control box of electric brake system of airplane - Google Patents
Power-on self-checking logic control method for control box of electric brake system of airplane Download PDFInfo
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- CN113978706B CN113978706B CN202110957721.1A CN202110957721A CN113978706B CN 113978706 B CN113978706 B CN 113978706B CN 202110957721 A CN202110957721 A CN 202110957721A CN 113978706 B CN113978706 B CN 113978706B
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- power
- self
- bit
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- checking
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- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000001514 detection method Methods 0.000 claims description 9
- 208000024891 symptom Diseases 0.000 abstract description 3
- 230000007547 defect Effects 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012913 prioritisation Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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
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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
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/18—Safety devices; Monitoring
- B60T17/22—Devices for monitoring or checking brake systems; Signal devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
- B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
-
- 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
- B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Regulating Braking Force (AREA)
- Valves And Accessory Devices For Braking Systems (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a control method for power-on self-checking logic of an aircraft electric brake system control box, which comprises the steps of initializing the aircraft electric brake system control box, judging power-on self-checking and grounding protection priority logic according to the service condition of the aircraft electric brake system, determining the time of power-on BIT, setting the power-on self-checking time, power-on self-checking output pressure time and power-on BIT output self-checking current of the aircraft electric brake system according to the condition of the aircraft electric brake system, and outputting corresponding brake pressure. The invention eliminates the problem that the brake system outputs brake pressure due to the ground protection power-on self-test in the aircraft landing process, so that the aircraft landes under pressure; thereby improving the reliability of the braking system and eliminating the accident symptoms in the landing process of the aircraft.
Description
Technical Field
The invention belongs to the technical field of aircraft electric brake systems, and particularly relates to a control box power-on self-checking logic control method.
Background
The electric brake is an advanced aircraft brake technology, has multiple functions, not only has an anti-skid function, but also has an inter-wheel protection function, a ground protection function, an in-aircraft detection (BIT) function and the like; meanwhile, the aircraft is electrified to carry out self-checking, the health state of the brake system is required to be monitored, and the brake system is operated by a driver to provide decision information in time.
In the prior art, the sequence of grounding protection and power-on self-checking (power-on BIT) is not considered, and the power-on self-checking outputs large brake pressure for a long time, so that the serious consequences of landing of the aircraft with the power-on BIT and the brake and tire burst before grounding can be possibly caused; in addition, repeated power-up BIT can cause cumulative fatigue damage to the structural integrity of the brake cylinder block.
The application number 201610905297.5 is "a power-on self-checking protection method for an aircraft anti-skid braking system", in order to overcome the defects of rising false alarm rate and low reliability in the prior art, a method for presetting parameters and setting a power-on self-checking threshold is adopted, and the application does not relate to the problem of power-on self-checking and ground protection priority logic sequence, and also does not relate to the problem of power-on BIT time and output braking pressure.
The application number 201711389035.9 is "a power-on self-checking method of an aircraft anti-skid brake system", in order to avoid that a servo valve outputs a large pressure signal to a cylinder seat in the power-on self-checking process, the service life of the cylinder seat is prolonged, and the detection current of the servo valve in the power-on self-checking process is reduced from 10mA to 5mA, so that the brake pressure output to the cylinder seat in the power-on self-checking process is reduced from 10MPa to below 5MPa, the pressure impact on the cylinder seat is reduced, and the service life of the cylinder seat is prolonged. But the application does not address the issue of power BIT and ground protection prioritization.
The application number 201510155353.3 is 'a power-on self-detection method of the electric brake', in order to avoid the problem of insufficient research on the power-on self-detection, the power-on self-detection is carried out on the components which are easy to damage of a brake system, and the components which are most detected in limited detection times before the system operates are used for timely detecting and positioning fault components. However, the application does not address the issues of power-on self-test and ground protection priority logic sequences, nor the issues of power-on BIT time and output brake pressure.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a control method for power-on self-checking logic of an aircraft electric brake system control box, which comprises the steps of initializing the aircraft electric brake system control box, judging power-on self-checking and grounding protection priority logic according to the use condition of the aircraft electric brake system, determining the time of power-on BIT, setting the power-on self-checking time, the power-on self-checking output pressure time and the power-on BIT output self-checking current of the aircraft electric brake system, carrying out power-on BIT, and outputting corresponding brake pressure. The invention eliminates the problem that the brake system outputs brake pressure due to the ground protection power-on self-test in the aircraft landing process, so that the aircraft landes under pressure; thereby improving the reliability of the braking system and eliminating the accident symptoms in the landing process of the aircraft.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
step 1: initializing an aircraft electric brake system control box;
Step 2: according to the service condition of the electric brake system of the airplane, the power-on self-detection and grounding protection priority logic is judged, and the power-on BIT is determined as follows:
(1) When the aircraft is in the air, the landing gear is not put in place, and the BIT is electrified;
(2) When the aircraft is on the ground, the wheel speed of the aircraft is less than 25Km/h, and power-on BIT is performed;
(3) When the front wheel load of the aircraft is in a non-bearing state, the left main landing gear and the right main landing gear are all put down in place, and no BIT is powered on;
(4) When the speed of the airplane wheel is greater than or equal to 25Km/h, the BIT is not electrified;
(5) When the ground protection of the airplane fails, the airplane is in the deceleration process, and the BIT is not electrified when the speed is greater than 60 Km/h;
(6) When the aircraft stop brake signal is effective, the power-on BIT is not performed;
(7) When the aircraft braking instruction is greater than 2.5V, the BIT is not electrified;
(8) When the aircraft electric brake system is not electrified, the BIT is not electrified;
(9) When the ground protection of the airplane is effective, the BIT is not electrified;
Step 3: and (2) setting the power-on self-checking time, the power-on self-checking output pressure time and the power-on BIT output self-checking current of the electric brake system of the aircraft for determining the condition of the power-on BIT in the step (2), carrying out the power-on BIT, and outputting the corresponding brake pressure.
Further, the power-on self-checking time of the aircraft electric brake system is 3s, the power-on self-checking output pressure time is 0.2s, and the power-on BIT output self-checking current is 7mA; under the conditions of the three parameters, the output brake pressure is 2Mpa when the BIT is electrified.
The beneficial effects of the invention are as follows:
According to the invention, by judging the power-on self-checking and grounding protection priority logic, the power-on self-checking time and the self-checking duration of the aircraft braking system are determined, the self-checking current and the self-checking output braking pressure solve the problems that the aircraft braking system is powered off and restarted in the process of grounding protection or braking of the aircraft, the output braking pressure is high, the aircraft lands with the brake, and the problem that the braking system outputs the braking pressure due to the power-on self-checking of the grounding protection in the process of landing the aircraft, so that the aircraft lands with the pressure is solved; thereby improving the reliability of the braking system and eliminating the accident symptoms in the landing process of the aircraft.
Drawings
FIG. 1 is a block diagram of the method of the present invention.
Detailed Description
The invention will be further described with reference to the drawings and examples.
In order to solve the problem that the prior art does not relate to the power-on self-checking and ground protection priority logic sequence, the defects of the problem that the power-on BIT time and the output brake pressure are not related are overcome. The invention provides a control box power-on self-checking logic and a control method thereof, and determines a control method of a power-on self-checking and grounding protection priority logic sequence, power-on BIT time and output brake pressure based on a power-on anti-skid brake system.
As shown in fig. 1, a method for controlling power-on self-checking logic of an aircraft electric brake system control box comprises the following steps:
step 1: initializing an aircraft electric brake system control box;
Step 2: according to the service condition of the electric brake system of the airplane, the power-on self-detection and grounding protection priority logic is judged, and the power-on BIT is determined as follows:
(1) When the aircraft is in the air, the landing gear is not put in place, and the BIT is electrified;
(2) When the aircraft is on the ground, the aircraft wheels slide at a low speed, the wheel speed of the aircraft wheels is less than 25Km/h, and the BIT is electrified;
(3) When the front wheel load of the aircraft is in a non-bearing state, the left main landing gear and the right main landing gear are all put down in place, and no BIT is powered on;
(4) When the speed of the airplane wheel is greater than or equal to 25Km/h, the BIT is not electrified;
(5) When the ground protection of the aircraft fails, the aircraft is in a high-speed and medium-speed deceleration process, and the power-on BIT is not performed;
(6) When the aircraft stop brake signal is effective, the power-on BIT is not performed;
(7) When the aircraft braking instruction is greater than 2.5V, the BIT is not electrified;
(8) When the aircraft electric brake system is not electrified, the BIT is not electrified;
(9) When the ground protection of the airplane is effective, the BIT is not electrified;
Step 3: and (2) setting the power-on self-checking time, the power-on self-checking output pressure time and the power-on BIT output self-checking current of the electric brake system of the aircraft for determining the condition of the power-on BIT in the step (2), carrying out the power-on BIT, and outputting the corresponding brake pressure.
Further, the power-on self-checking time of the aircraft electric brake system is 3s, the power-on self-checking output pressure time is 0.2s, and the power-on BIT output self-checking current is 7mA; under the conditions of the three parameters, the output brake pressure is 2Mpa when the BIT is electrified.
Claims (2)
1. The power-on self-checking logic control method for the control box of the electric brake system of the airplane is characterized by comprising the following steps of:
step 1: initializing an aircraft electric brake system control box;
Step 2: according to the service condition of the electric brake system of the airplane, the power-on self-detection and grounding protection priority logic is judged, and the power-on BIT is determined as follows:
(1) When the aircraft is in the air, the landing gear is not put in place, and the BIT is electrified;
(2) When the aircraft is on the ground, the wheel speed of the aircraft is less than 25Km/h, and power-on BIT is performed;
(3) When the front wheel load of the aircraft is in a non-bearing state, the left main landing gear and the right main landing gear are all put down in place, and no BIT is powered on;
(4) When the speed of the airplane wheel is greater than or equal to 25Km/h, the BIT is not electrified;
(5) When the ground protection of the airplane fails, the airplane is in the deceleration process, and the BIT is not electrified when the speed is greater than 60 Km/h;
(6) When the aircraft stop brake signal is effective, the power-on BIT is not performed;
(7) When the aircraft braking instruction is greater than 2.5V, the BIT is not electrified;
(8) When the aircraft electric brake system is not electrified, the BIT is not electrified;
(9) When the ground protection of the airplane is effective, the BIT is not electrified;
Step 3: and (2) setting the power-on self-checking time, the power-on self-checking output pressure time and the power-on BIT output self-checking current of the electric brake system of the aircraft for determining the condition of the power-on BIT in the step (2), carrying out the power-on BIT, and outputting the corresponding brake pressure.
2. The method for controlling power-on self-checking logic of an aircraft electric brake system control box according to claim 1, wherein the power-on self-checking time of the aircraft electric brake system is 3s, the power-on self-checking output pressure time is 0.2s, and the power-on BIT output self-checking current is 7mA; under the conditions of the three parameters, the output brake pressure is 2Mpa when the BIT is electrified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110957721.1A CN113978706B (en) | 2021-08-18 | 2021-08-18 | Power-on self-checking logic control method for control box of electric brake system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110957721.1A CN113978706B (en) | 2021-08-18 | 2021-08-18 | Power-on self-checking logic control method for control box of electric brake system of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113978706A CN113978706A (en) | 2022-01-28 |
| CN113978706B true CN113978706B (en) | 2024-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110957721.1A Active CN113978706B (en) | 2021-08-18 | 2021-08-18 | Power-on self-checking logic control method for control box of electric brake system of airplane |
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| Country | Link |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394881A (en) * | 2016-10-18 | 2017-02-15 | 西安航空制动科技有限公司 | Power-on self-test protection method for anti-skid brake system of airplane |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3000003B1 (en) * | 2012-12-21 | 2016-12-23 | Messier Bugatti Dowty | METHOD FOR BRAKING AN AIRCRAFT |
| CN104494815B (en) * | 2014-11-18 | 2016-06-01 | 西安航空制动科技有限公司 | A kind of Aircraft Anti-skid Break Control lands protection method |
| CN106218871B (en) * | 2016-07-25 | 2018-08-07 | 西安航空制动科技有限公司 | Aircraft brake anti-skid control method and airplane brake system |
| CN113219275A (en) * | 2021-04-13 | 2021-08-06 | 西安子国微科技有限公司 | Brake residual pressure detection system |
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2021
- 2021-08-18 CN CN202110957721.1A patent/CN113978706B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106394881A (en) * | 2016-10-18 | 2017-02-15 | 西安航空制动科技有限公司 | Power-on self-test protection method for anti-skid brake system of airplane |
Non-Patent Citations (1)
| Title |
|---|
| 飞机刹车***接地保护功能研究;钟亮等;航空精密制造技术(第1期);43-49 * |
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| CN113978706A (en) | 2022-01-28 |
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