CN112249309A - Airplane fault safety brake control system - Google Patents
Airplane fault safety brake control system Download PDFInfo
- Publication number
- CN112249309A CN112249309A CN202011038242.1A CN202011038242A CN112249309A CN 112249309 A CN112249309 A CN 112249309A CN 202011038242 A CN202011038242 A CN 202011038242A CN 112249309 A CN112249309 A CN 112249309A
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- Prior art keywords
- brake control
- airplane
- control valve
- current
- unit
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
-
- 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
- B60T7/00—Brake-action initiating means
- B60T7/12—Brake-action initiating means for automatic initiation; for initiation not subject to will of driver or passenger
- B60T7/22—Brake-action initiating means for automatic initiation; for initiation not subject to will of driver or passenger initiated by contact of vehicle, e.g. bumper, with an external object, e.g. another vehicle, or by means of contactless obstacle detectors mounted on the vehicle
Abstract
The invention discloses an airplane fault safety brake control system which comprises an information acquisition unit, a data processing unit, a simulation processing unit, an automatic brake control unit, an automatic brake execution unit and a brake control valve. The invention presets the type of the barrier, a first threshold value and a second threshold value by setting a dynamic brake control unit, an automatic brake execution unit and a brake control valve, wherein the second threshold value is larger than the first threshold value; and if the obstacle is identified and the instantaneous speed of the airplane is greater than the second threshold value, the automatic brake control unit is started to drive the brake control valve to perform high-pressure automatic braking, so that braking under different pressures is performed on the obstacle at different speeds, and the safety performance is improved.
Description
Technical Field
The invention relates to the technical field of brake control systems, in particular to an airplane fault safety brake control system.
Background
The aircraft brake control system is used as an important airborne device, the safety of an aircraft can be seriously influenced if the brake system can normally work, the automatic brake system can complete the deceleration of the aircraft without manually applying brake operation in the processes of takeoff and landing, and the automatic brake system automatically adjusts the brake pressure to ensure that the aircraft decelerates at a constant deceleration rate in the process of landing of the aircraft, so that the comfort of passengers and passengers in the process of landing can be obviously improved, the workload of a driver can be reduced, and the danger possibly caused by improper brake operation of the driver can be avoided, therefore, the technology is widely applied to the existing military and civil aircraft.
Aircraft brake control system is as important airborne equipment, whether brake system can normally work will seriously influence aircraft safety, at present, aircraft brake control system, mostly adopt one set of hydraulic source to supply pressure, the wheel respectively sets up a brake control valve about, respectively set up an electromagnetism hydraulic lock at the control valve front end, in case the case jamming appears in the brake control valve, the electromagnetism hydraulic lock can not get back to the oil tank with brake system oil feed, the system will take the brake landing and drag the child, the danger of the tire burst of stopping can appear in the aircraft, seriously influence aircraft safety in utilization.
Although an airplane failure-safety brake control system disclosed in patent number Ca201320049409.3 appears in the prior art, when a valve core of a brake control valve has a clamping stagnation failure, the brake system can be in a brake releasing state, so that the problem that the airplane is braked and burst due to the fact that the system lands with brakes and drags tires is solved. The landing safety of the airplane is improved. But it cannot automatically judge the obstacle and perform brake control of different pressures.
Disclosure of Invention
The invention aims to solve the problems and provides an aircraft fail-safe brake control system.
In order to achieve the purpose, the invention adopts the following technical scheme:
an aircraft failure safety brake control system comprises an information acquisition unit, a data processing unit, a simulation processing unit, an automatic brake control unit, an automatic brake execution unit and a brake control valve;
the information acquisition unit acquires the current airplane speed and the distance between the current airplane speed and the obstacle;
the data processing unit calculates the relative distance and the relative speed between the current airplane and the obstacle by using the current airplane speed of the signal acquisition unit and the distance between the current airplane and the obstacle;
the automatic brake control unit establishes an airplane longitudinal inverse model and a prediction model according to the relative distance and relative speed information obtained by the data processing unit, adopts a prediction control strategy to make prediction judgment according to the current information, controls the current airplane brake state, predicts the state in a plurality of periods and corrects the current input based on the prediction judgment;
the signal output by the automatic brake control unit is sent to the brake control valve, so that the brake pressure information can be changed into an executable instruction, the pressure of the brake control valve is changed, and the airplane is braked;
the simulation processing unit can run an airplane model, a barrier model and a brake control valve model in real time and can calculate the current running state, the flight speed and the deceleration rate of the airplane in real time.
Optionally, the information acquisition unit includes one or more of a camera, a millimeter wave radar, and an infrared sensor.
Optionally, the system is implemented by:
the method comprises the following steps: the method comprises the following steps that an airplane operator starts an information acquisition unit through a central maintenance system, and real-time monitoring is achieved through one or more of a camera, a millimeter wave radar and an infrared sensor;
step two: the data processing unit monitors the data sent by the information acquisition unit in real time, monitors the automatic brake control unit, the automatic brake execution unit and the brake control valve, judges whether the units are in a fault state or not, and sends fault information of a brake system of an airplane operator if one unit is in a fault state;
step three: if the automatic brake control unit, the automatic brake execution unit and the brake control valve have no faults, sending no faults of the brake system to an aircraft operator;
step four; the simulation processing unit calculates the current running state, the flight speed and the airplane deceleration rate in real time according to the current airplane system brake pressure signal, the airplane model, the obstacle model and the brake control valve model;
step five; presetting the type of an obstacle, a first threshold value and a second threshold value, wherein the second threshold value is larger than the first threshold value, and starting an automatic brake control unit to drive a brake control valve to perform small-pressure automatic braking when the obstacle is identified and the instantaneous speed of the airplane is larger than the first threshold value;
step six; and if the obstacle is identified and the instantaneous speed of the airplane is greater than the second threshold value, starting the automatic braking control unit to drive the braking control valve to perform high-pressure automatic braking.
Optionally, the method for identifying the aircraft longitudinal inverse model comprises: searching for an optimal neural network structure, weight and threshold by adopting an ant colony optimization neural network, identifying and establishing an airplane longitudinal inverse model according to a neural network system, and taking the current relative airplane speed and relative distance as input and the pressure of a brake control valve as output; the current relative airplane speed and the current relative distance obtained by one or more measured information of a camera, a millimeter wave radar and an infrared sensor through a data processing module are used for obtaining braking force by installing a pressure sensor at a brake control valve, obtaining input and output, and establishing a longitudinal model nonlinear system as described below:
y(t)＝F[y(t-1),...y(t-a),u(t-d),....u(t-d-b)]
representing a two-input single-output nonlinear dynamical system, b and a representing the order of input u and output y, respectively, d being the time lag of the nonlinear system, and F (-) representing a continuous nonlinear function unknown to be identified.
The invention has the following advantages:
the invention can monitor the flight state of the airplane by arranging the information acquisition unit, the data processing unit and the simulation processing unit, and can calculate the current running state, the flight speed and the airplane deceleration rate in real time according to the current airplane system brake pressure signal, the airplane model, the obstacle model and the brake control valve model.
The invention presets the type of the barrier, a first threshold value and a second threshold value by setting a dynamic brake control unit, an automatic brake execution unit and a brake control valve, wherein the second threshold value is larger than the first threshold value; and if the obstacle is identified and the instantaneous speed of the airplane is greater than the second threshold value, the automatic brake control unit is started to drive the brake control valve to perform high-pressure automatic braking, so that braking under different pressures is performed on the obstacle at different speeds, and the safety performance is improved.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments.
An aircraft failure safety brake control system comprises an information acquisition unit, a data processing unit, a simulation processing unit, an automatic brake control unit, an automatic brake execution unit and a brake control valve.
The information acquisition unit acquires the current airplane speed and the distance between the current airplane speed and the obstacle.
The information acquisition unit comprises one or more of a camera, a millimeter wave radar and an infrared sensor.
The data processing unit calculates the relative distance and the relative speed between the current airplane and the obstacle by using the current airplane speed of the signal acquisition unit and the distance between the current airplane and the obstacle;
the automatic brake control unit establishes an airplane longitudinal inverse model and a prediction model according to the relative distance and relative speed information obtained by the data processing unit, adopts a prediction control strategy to make prediction judgment according to the current information, controls the current airplane brake state, predicts the state in a plurality of periods and corrects the current input based on the prediction judgment.
The method for identifying the longitudinal inverse model of the airplane comprises the following steps: searching for an optimal neural network structure, weight and threshold by adopting an ant colony optimization neural network, identifying and establishing an airplane longitudinal inverse model according to a neural network system, and taking the current relative airplane speed and relative distance as input and the pressure of a brake control valve as output; the current relative airplane speed and the current relative distance obtained by one or more measured information of a camera, a millimeter wave radar and an infrared sensor through a data processing module are used for obtaining braking force by installing a pressure sensor at a brake control valve, obtaining input and output, and establishing a longitudinal model nonlinear system as described below:
y(t)＝F[y(t-1),...y(t-a),u(t-d),....u(t-d-b)]
representing a two-input single-output nonlinear dynamical system, b and a representing the order of input u and output y, respectively, d being the time lag of the nonlinear system, and F (-) representing a continuous nonlinear function unknown to be identified.
The signal output by the automatic brake control unit is sent to the brake control valve, so that the brake pressure information can be changed into an executable instruction, the pressure of the brake control valve is changed, and the airplane is braked;
the simulation processing unit can run an airplane model, a barrier model and a brake control valve model in real time and can calculate the current running state, the flight speed and the deceleration rate of the airplane in real time.
The system is realized by the following modes:
the method comprises the following steps: the method comprises the following steps that an airplane operator starts an information acquisition unit through a central maintenance system, and real-time monitoring is achieved through one or more of a camera, a millimeter wave radar and an infrared sensor;
step two: the data processing unit monitors the data sent by the information acquisition unit in real time, monitors the automatic brake control unit, the automatic brake execution unit and the brake control valve, judges whether the units are in a fault state or not, and sends fault information of a brake system of an airplane operator if one unit is in a fault state;
step three: if the automatic brake control unit, the automatic brake execution unit and the brake control valve have no faults, sending no faults of the brake system to an aircraft operator;
step four; the simulation processing unit calculates the current running state, the flight speed and the airplane deceleration rate in real time according to the current airplane system brake pressure signal, the airplane model, the obstacle model and the brake control valve model;
step five; presetting the type of an obstacle, a first threshold value and a second threshold value, wherein the second threshold value is larger than the first threshold value, and starting an automatic brake control unit to drive a brake control valve to perform small-pressure automatic braking when the obstacle is identified and the instantaneous speed of the airplane is larger than the first threshold value;
step six; and if the obstacle is identified and the instantaneous speed of the airplane is greater than the second threshold value, starting the automatic braking control unit to drive the braking control valve to perform high-pressure automatic braking.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention. In the present invention, unless otherwise specifically stated or limited, the terms "cover", "fitted", "attached", "fixed", "distributed", and the like are to be understood in a broad sense, and may be, for example, fixedly attached, detachably attached, or integrated; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Claims (4)
1. An aircraft failure safety brake control system is characterized by comprising an information acquisition unit, a data processing unit, a simulation processing unit, an automatic brake control unit, an automatic brake execution unit and a brake control valve;
the information acquisition unit acquires the current airplane speed and the distance between the current airplane speed and the obstacle;
the data processing unit calculates the relative distance and the relative speed between the current airplane and the obstacle by using the current airplane speed of the signal acquisition unit and the distance between the current airplane and the obstacle;
the automatic brake control unit establishes an airplane longitudinal inverse model and a prediction model according to the relative distance and relative speed information obtained by the data processing unit, adopts a prediction control strategy to make prediction judgment according to the current information, controls the current airplane brake state, predicts the state in a plurality of periods and corrects the current input based on the prediction judgment;
the signal output by the automatic brake control unit is sent to the brake control valve, so that the brake pressure information can be changed into an executable instruction, the pressure of the brake control valve is changed, and the airplane is braked;
the simulation processing unit can run an airplane model, a barrier model and a brake control valve model in real time and can calculate the current running state, the flight speed and the deceleration rate of the airplane in real time.
2. The aircraft fail-safe brake control system of claim 1, wherein the information acquisition unit comprises one or more of a camera, a millimeter wave radar, and an infrared sensor.
3. An aircraft fail-safe brake control system according to claim 1, wherein the system is implemented by:
the method comprises the following steps: the method comprises the following steps that an airplane operator starts an information acquisition unit through a central maintenance system, and real-time monitoring is achieved through one or more of a camera, a millimeter wave radar and an infrared sensor;
step two: the data processing unit monitors the data sent by the information acquisition unit in real time, monitors the automatic brake control unit, the automatic brake execution unit and the brake control valve, judges whether the units are in a fault state or not, and sends fault information of a brake system of an airplane operator if one unit is in a fault state;
step three: if the automatic brake control unit, the automatic brake execution unit and the brake control valve have no faults, sending no faults of the brake system to an aircraft operator;
step four; the simulation processing unit calculates the current running state, the flight speed and the airplane deceleration rate in real time according to the current airplane system brake pressure signal, the airplane model, the obstacle model and the brake control valve model;
step five; presetting the type of an obstacle, a first threshold value and a second threshold value, wherein the second threshold value is larger than the first threshold value, and starting an automatic brake control unit to drive a brake control valve to perform small-pressure automatic braking when the obstacle is identified and the instantaneous speed of the airplane is larger than the first threshold value;
step six; and if the obstacle is identified and the instantaneous speed of the airplane is greater than the second threshold value, starting the automatic braking control unit to drive the braking control valve to perform high-pressure automatic braking.
4. The system of claim 1, wherein the method for identifying the longitudinal inverse model of the aircraft comprises: searching for an optimal neural network structure, weight and threshold by adopting an ant colony optimization neural network, identifying and establishing an airplane longitudinal inverse model according to a neural network system, and taking the current relative airplane speed and relative distance as input and the pressure of a brake control valve as output; the current relative airplane speed and the current relative distance obtained by one or more measured information of a camera, a millimeter wave radar and an infrared sensor through a data processing module are used for obtaining braking force by installing a pressure sensor at a brake control valve, obtaining input and output, and establishing a longitudinal model nonlinear system as described below:
y(t)＝F[y(t-1),...y(t-a),u(t-d),....u(t-d-b)]
representing a two-input single-output nonlinear dynamical system, b and a representing the order of input u and output y, respectively, d being the time lag of the nonlinear system, and F (-) representing a continuous nonlinear function unknown to be identified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011038242.1A CN112249309A (en) | 2020-09-28 | 2020-09-28 | Airplane fault safety brake control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011038242.1A CN112249309A (en) | 2020-09-28 | 2020-09-28 | Airplane fault safety brake control system |
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| Publication Number | Publication Date |
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| CN112249309A true CN112249309A (en) | 2021-01-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011038242.1A Pending CN112249309A (en) | 2020-09-28 | 2020-09-28 | Airplane fault safety brake control system |
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| Country | Link |
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| CN (1) | CN112249309A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113050690A (en) * | 2021-03-19 | 2021-06-29 | 西安航空制动科技有限公司 | Airplane ground comprehensive control system and control method |
| CN113697118A (en) * | 2021-10-28 | 2021-11-26 | 西安羚控电子科技有限公司 | Brake system fault processing method and system of fixed-wing unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113050690A (en) * | 2021-03-19 | 2021-06-29 | 西安航空制动科技有限公司 | Airplane ground comprehensive control system and control method |
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| CN113697118A (en) * | 2021-10-28 | 2021-11-26 | 西安羚控电子科技有限公司 | Brake system fault processing method and system of fixed-wing unmanned aerial vehicle |
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Application publication date: 20210122 |