CN113978706A - Power-on self-test logic control method for control box of fly-by-wire brake system of airplane - Google Patents
Power-on self-test logic control method for control box of fly-by-wire brake system of airplane Download PDFInfo
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- CN113978706A CN113978706A CN202110957721.1A CN202110957721A CN113978706A CN 113978706 A CN113978706 A CN 113978706A CN 202110957721 A CN202110957721 A CN 202110957721A CN 113978706 A CN113978706 A CN 113978706A
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000001514 detection method Methods 0.000 description 6
- 230000007547 defect Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012913 prioritisation Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
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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
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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
- B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
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- 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 power-on self-test logic control method for a control box of an airplane telex brake system, which comprises the steps of initializing the control box of the airplane telex brake system, judging power-on self-test and grounding protection priority logic according to the use condition of the airplane telex brake system, determining the time of power-on BIT, setting power-on self-test time, power-on self-test output pressure time and power-on BIT output self-test current of the airplane telex brake system for power-on BIT determination, carrying out power-on BIT and outputting corresponding brake pressure. The invention eliminates the problem that the airplane lands under pressure due to brake system output brake pressure caused by grounding protection power-on self-test in the landing process of the airplane; thereby improving the reliability of the brake system and eliminating the accident signs in the landing process of the airplane.
Description
Technical Field
The invention belongs to the technical field of an airplane fly-by-wire brake system, and particularly relates to a power-on self-test logic control method for a control box.
Background
The fly-by-wire brake is an advanced airplane brake technology, has multiple functions, and not only has an anti-skid function, but also has an inter-wheel protection function, a ground protection function, built-in detection (BIT) and the like; meanwhile, the airplane needs to be electrified for self-inspection when being electrified, the health state of the brake system needs to be monitored, and decision information is provided for a driver to operate the brake system in time.
In the prior art, the sequence of grounding protection and power-on self-test (power-on BIT) is not considered, and the power-on self-test outputs large brake pressure for a long time, so that the serious consequences of the fact that the power-on BIT of an airplane is grounded with a brake and a tire is broken can be caused; in addition, repeated power-up of the BIT can cause cumulative fatigue damage to the structural integrity of the cylinder block of the brake device.
The application number is 201610905297.5, a method for protecting an aircraft anti-skid brake system by power-on self-test is used for overcoming 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-test threshold is adopted, and the application does not relate to the problems of power-on self-test and ground protection priority logic order and power-on BIT time and output brake pressure.
The application number is 201711389035.9 'power-on self-checking method for an aircraft anti-skid brake system', in order to prevent a servo valve from outputting a large pressure signal to a cylinder base in the power-on self-checking process and prolong the service life of the cylinder base, the detection current of the servo valve in the power-on self-checking process is reduced from 10mA to 5mA, and therefore the brake pressure output to the cylinder base in the power-on self-checking process is reduced from 10MPa to below 5MPa, the pressure impact on the cylinder base is reduced, and the purpose of prolonging the service life of the cylinder base is achieved. The application does not address the issue of power-up BIT and ground protection priority logic order.
The 'power-on self-detection method of the electric brake' with the application number of 201510155353.3 is used for avoiding the problem of insufficient research on power-on self-detection, carrying out power-on self-detection on elements which are easy to damage of a brake system, and detecting and positioning fault elements in time by detecting the most elements within limited detection times as far as possible before the system runs. However, this application does not address the issue of power-on self-test and ground protection prioritization, nor the issue of power-on BIT time and magnitude of output brake pressure.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a power-on self-test logic control method for an airplane telex brake system control box. The invention eliminates the problem that the airplane lands under pressure due to brake system output brake pressure caused by grounding protection power-on self-test in the landing process of the airplane; thereby improving the reliability of the brake system and eliminating the accident signs in the landing process of the airplane.
The technical scheme adopted by the invention for solving the technical problem comprises the following steps:
step 1: initializing a control box of an airplane fly-by-wire brake system;
step 2: judging the power-on self-test and grounding protection priority logic according to the using condition of the fly-by-wire brake system of the airplane, and determining the power-on BIT at the following time:
(1) when the aircraft is in the air and the undercarriage is not put in place, electrifying BIT;
(2) when the airplane is on the ground and the wheel speed of the airplane is less than 25Km/h, electrifying BIT;
(3) when the front wheel load of the airplane is in a non-bearing state, and the left main undercarriage and the right main undercarriage are both put down in place, the power-on BIT is not carried out;
(4) when the speed of the airplane wheel of the airplane is more than or equal to 25Km/h, the power-on BIT is not carried out;
(5) when the ground protection of the airplane fails and the airplane is in the process of deceleration, the power-on BIT is not carried out when the speed is higher than 60 Km/h;
(6) when the airplane is stopped and the brake signal is effective, the power-on BIT is not carried out;
(7) when the braking instruction of the airplane is larger than 2.5V, the power-on BIT is not carried out;
(8) when the electric transmission braking system of the airplane is not electrified, the power-on BIT is not carried out;
(9) when the airplane grounding protection is effective, the power-on BIT is not carried out;
and step 3: and (3) setting the power-on self-test time, the power-on self-test output pressure time and the power-on BIT output self-test current of the airplane telex brake system for the condition that the BIT needs to be powered on in the step (2), carrying out power-on BIT and outputting corresponding brake pressure.
Furthermore, the power-on self-test time of the fly-by-wire brake system is 3s, the power-on self-test output pressure time is 0.2s, and the power-on BIT outputs the self-test current of 7 mA; under the conditions of the three parameters, the brake pressure output when the BIT is electrified is 2 Mpa.
The invention has the following beneficial effects:
the invention determines the power-on self-check time, the self-check duration, the self-check current and the self-check output brake pressure of the airplane brake system by judging the power-on self-check and grounding protection priority logic, solves the problem that the airplane landing with brake is caused by the large output brake pressure due to the power-off restart of the brake system in the airplane grounding protection or in the braking process of the airplane brake system, and eliminates the problem that the airplane lands with brake due to the output brake pressure of the brake system caused by the power-on self-check of the grounding protection in the airplane landing process; thereby improving the reliability of the brake system and eliminating the accident signs in the landing process of the airplane.
Drawings
FIG. 1 is a block diagram of the method of the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
The method aims to solve the defects that the prior art does not relate to the problems of power-on self-test and grounding protection priority logic sequence, and does not relate to the problems of power-on BIT time and output brake pressure. The invention provides a control box power-on self-test logic and a control method thereof, and the control method determines the priority logic order of power-on self-test and ground protection, power-on BIT time and output brake pressure based on an electric transmission anti-skid brake system.
As shown in fig. 1, a method for controlling a power-on self-test logic of a control box of a fly-by-wire brake system of an aircraft includes the following steps:
step 1: initializing a control box of an airplane fly-by-wire brake system;
step 2: judging the power-on self-test and grounding protection priority logic according to the using condition of the fly-by-wire brake system of the airplane, and determining the power-on BIT at the following time:
(1) when the aircraft is in the air and the undercarriage is not put in place, electrifying BIT;
(2) when the airplane is on the ground, the airplane wheels slide at a low speed, the speed of the airplane wheels is less than 25Km/h, and power-on BIT is carried out;
(3) when the front wheel load of the airplane is in a non-bearing state, and the left main undercarriage and the right main undercarriage are both put down in place, the power-on BIT is not carried out;
(4) when the speed of the airplane wheel of the airplane is more than or equal to 25Km/h, the power-on BIT is not carried out;
(5) when the ground protection of the airplane fails and the airplane is in the process of high-speed and medium-speed deceleration, the power-on BIT is not carried out;
(6) when the airplane is stopped and the brake signal is effective, the power-on BIT is not carried out;
(7) when the braking instruction of the airplane is larger than 2.5V, the power-on BIT is not carried out;
(8) when the electric transmission braking system of the airplane is not electrified, the power-on BIT is not carried out;
(9) when the airplane grounding protection is effective, the power-on BIT is not carried out;
and step 3: and (3) setting the power-on self-test time, the power-on self-test output pressure time and the power-on BIT output self-test current of the airplane telex brake system for the condition that the BIT needs to be powered on in the step (2), carrying out power-on BIT and outputting corresponding brake pressure.
Furthermore, the power-on self-test time of the fly-by-wire brake system is 3s, the power-on self-test output pressure time is 0.2s, and the power-on BIT outputs the self-test current of 7 mA; under the conditions of the three parameters, the brake pressure output when the BIT is electrified is 2 Mpa.
Claims (2)
1. A power-on self-test logic control method for a control box of an airplane fly-by-wire brake system is characterized by comprising the following steps:
step 1: initializing a control box of an airplane fly-by-wire brake system;
step 2: judging the power-on self-test and grounding protection priority logic according to the using condition of the fly-by-wire brake system of the airplane, and determining the power-on BIT at the following time:
(1) when the aircraft is in the air and the undercarriage is not put in place, electrifying BIT;
(2) when the airplane is on the ground and the wheel speed of the airplane is less than 25Km/h, electrifying BIT;
(3) when the front wheel load of the airplane is in a non-bearing state, and the left main undercarriage and the right main undercarriage are both put down in place, the power-on BIT is not carried out;
(4) when the speed of the airplane wheel of the airplane is more than or equal to 25Km/h, the power-on BIT is not carried out;
(5) when the ground protection of the airplane fails and the airplane is in the process of deceleration, the power-on BIT is not carried out when the speed is higher than 60 Km/h;
(6) when the airplane is stopped and the brake signal is effective, the power-on BIT is not carried out;
(7) when the braking instruction of the airplane is larger than 2.5V, the power-on BIT is not carried out;
(8) when the electric transmission braking system of the airplane is not electrified, the power-on BIT is not carried out;
(9) when the airplane grounding protection is effective, the power-on BIT is not carried out;
and step 3: and (3) setting the power-on self-test time, the power-on self-test output pressure time and the power-on BIT output self-test current of the airplane telex brake system for the condition that the BIT needs to be powered on in the step (2), carrying out power-on BIT and outputting corresponding brake pressure.
2. The method for controlling the power-on self-test logic of the control box of the fly-by-wire brake system of the airplane as claimed in claim 1, wherein the power-on self-test time of the fly-by-wire brake system is 3s, the output pressure time of the power-on self-test is 0.2s, and the output self-test current of the power-on BIT is 7 mA; under the conditions of the three parameters, the brake pressure output when the BIT is electrified is 2 Mpa.
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 |
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| Publication Number | Publication Date |
|---|---|
| CN113978706A true CN113978706A (en) | 2022-01-28 |
| CN113978706B CN113978706B (en) | 2024-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| 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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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140180505A1 (en) * | 2012-12-21 | 2014-06-26 | Messier-Bugatti-Dowty | Method of managing the braking of an aircraft |
| CN104494815A (en) * | 2014-11-18 | 2015-04-08 | 西安航空制动科技有限公司 | Landing protection method for anti-skid brake system of airplane |
| CN106218871A (en) * | 2016-07-25 | 2016-12-14 | 西安航空制动科技有限公司 | Aircraft brake anti-skid control method and airplane brake system |
| 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 |
| CN113219275A (en) * | 2021-04-13 | 2021-08-06 | 西安子国微科技有限公司 | Brake residual pressure detection system |
-
2021
- 2021-08-18 CN CN202110957721.1A patent/CN113978706B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140180505A1 (en) * | 2012-12-21 | 2014-06-26 | Messier-Bugatti-Dowty | Method of managing the braking of an aircraft |
| CN104494815A (en) * | 2014-11-18 | 2015-04-08 | 西安航空制动科技有限公司 | Landing protection method for anti-skid brake system of airplane |
| CN106218871A (en) * | 2016-07-25 | 2016-12-14 | 西安航空制动科技有限公司 | Aircraft brake anti-skid control method and airplane brake system |
| 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 |
| CN113219275A (en) * | 2021-04-13 | 2021-08-06 | 西安子国微科技有限公司 | Brake residual pressure detection system |
Non-Patent Citations (1)
| Title |
|---|
| 钟亮等: "飞机刹车***接地保护功能研究", 航空精密制造技术, no. 1, pages 43 - 49 * |
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| CN113978706B (en) | 2024-06-18 |
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