CN112731958B - Method for using wheel bearing signal based on speed protection - Google Patents
Method for using wheel bearing signal based on speed protection Download PDFInfo
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- CN112731958B CN112731958B CN202011382985.0A CN202011382985A CN112731958B CN 112731958 B CN112731958 B CN 112731958B CN 202011382985 A CN202011382985 A CN 202011382985A CN 112731958 B CN112731958 B CN 112731958B
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- G—PHYSICS
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- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
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Abstract
The application provides a method for using a wheel bearing signal based on speed protection, which belongs to the technical field of flight control and comprises the following steps: determining the ground leaving speeds of the aircraft with different external hanging configurations in the whole take-off weight range of the aircraft; forming a speed protection range of the wheel load signal by using the aircraft ground leaving speed and a hysteresis loop link of the aircraft ground leaving speed and a preset value; and converting the speed protection range into a standard dynamic pressure range, and carrying out logic use of the wheel load signal according to the standard dynamic pressure range and the wheel load signal. According to the method, the aircraft air-ground state is judged by adding the standard dynamic pressure and combining the airborne wheel load signals, so that the reliability of judgment can be improved, and the flight safety risk is reduced.
Description
Technical Field
The application belongs to the field of flight control, and particularly relates to a method for using a wheel bearing signal based on speed protection.
Background
The flight status of an aircraft is generally divided into: the control laws corresponding to the air flight state, the take-off and landing flight state and the ground running state are also divided into an air flight control law, a take-off and landing flight control law and a ground running control law. The control law of the air and the landing gear is switched through the landing gear retraction state, and the control law of the landing gear and the running control law are switched through the machine wheel bearing signals. The wheel-mounted signal is used as an important signal for ground-air judgment of an aircraft control system, influences functions of control, calibration, test and the like of the system, and the safety reliability of the system is of great significance.
However, in the prior art, the problem of low reliability judgment of the air-ground state exists in the simple logic control by using the wheel-mounted signal of the airplane, and the flight safety risk exists.
Disclosure of Invention
It is an object of the present application to provide a method of using a wheel-bearing signal based on speed protection to solve or mitigate at least one problem in the background art.
The technical scheme of the application is as follows: a method for using a wheel-carried signal based on speed protection, comprising:
determining the ground leaving speeds of the aircraft with different external hanging configurations in the whole take-off weight range of the aircraft;
forming a speed protection range of the wheel load signal by using the aircraft ground leaving speed and a hysteresis loop link of the aircraft ground leaving speed and a preset value;
and converting the speed protection range into a standard dynamic pressure range, and carrying out logic use of the wheel load signal according to the standard dynamic pressure range and the wheel load signal.
Further, the process of determining the ground leaving speed of the aircraft in different plug-in configurations based on the total take-off weight range of the aircraft comprises the following steps:
at the moment of aircraft off the ground, constructing an equation set with zero resultant force of the Y axis and Z axis resultant moment of the aircraft under a semi-airframe coordinate system, namely:
obtaining a nonlinear equation set:
wherein: p is the engine thrust; alpha is the angle of attack; g is the aircraft takeoff weight; y is Y p Is the thrust line of the engineDistance to center of gravity; c y 、m z Is the aerodynamic coefficient; s is the area of the wing; b a Is the average aerodynamic chord length; q is dynamic pressure; ap is the included angle between the thrust line of the engine and the horizontal datum line of the airplane;
obtaining the aircraft ground leaving speed Vmax according to the dynamic pressure calculation, namelyρ is the atmospheric density.
Further, the preset value of the hysteresis loop link is (20-30) km/h.
Further, the process of converting the speed protection range into the standard dynamic pressure range includes:
judging the relation between the corrected airspeed and the sea level standard sound velocity Cn by taking the speed protection range as the corrected airspeed Vc;
when Vc is less than or equal to Cn, qc=pn ((1+0.2) (Vc/Cn) 2 ) 3.5 –1)；
Wherein Qc is a standard dynamic pressure and Pn is a sea level standard atmospheric pressure.
Further, the logic use includes: judging whether the aircraft is in a ground state according to the standard dynamic pressure range and the wheel-mounted signal of the aircraft wheel; and/or judging whether the aircraft is in a flight state according to the standard dynamic pressure range and the wheel load signal.
According to the method, the aircraft air-ground state is judged by adding the standard dynamic pressure and combining the airborne wheel load signals, so that the reliability of judgment can be improved, and the flight safety risk is reduced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic diagram of an on-board signal using method based on speed protection.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
Aiming at the situation that the safety and reliability of the aircraft air-ground state are low only by adopting an aircraft wheel carrying signal (also called an aircraft wheel carrying signal), the application provides a speed protection-based aircraft wheel carrying signal using method, which meets the requirement on the high reliability of the aircraft wheel carrying signal.
As shown in fig. 1, the method provided by the present application includes the following steps:
s1, calculating the ground leaving speeds of the aircraft with different external hanging configurations in a range covering the whole take-off weight of the aircraft.
Specifically, according to the related requirements of the aircraft and the engine, the values of parameters such as the thrust of the engine, the angle of attack from the ground and the like can be obtained.
At the moment of the aircraft leaving the ground, in a half-body coordinate system, the resultant force of the Y axis is 0, and the resultant moment of the Z axis is zero, so that an equation set is established, namely:
and (3) obtaining a nonlinear equation set after finishing:
wherein P is engine thrust, in this example 16000kg;
alpha is the angle of attack, i.e., the angle of attack, 10 in this embodiment;
g is the aircraft takeoff weight, 40t in this embodiment;
Y p the distance from the engine thrust line to the center of gravity (positive to produce low head torque, -0.3m in this embodiment;
c y 、m z for aerodynamic coefficients, 1.129 and-0.054 in this embodiment, respectively;
s is the wing area, 62m in this embodiment 2 ；
b a For the average aerodynamic chord length, 4m in this example;
q is dynamicThe pressure is 300kg/m in this example 2 ；
ap is the angle (positive head-up) between the thrust line of the engine and the horizontal reference line of the aircraft, which is 2 ° in this embodiment;
the dynamic pressure Q can be obtained by the nonlinear square cabin group, and then the formula is adoptedThe ground clearance Vmax can be obtained. Under the above embodiment parameters, the calculated ground clearance is vmax=340 km/h.
S2, forming a speed protection range value of the wheel load signal by using the aircraft ground leaving speed, the hysteresis loop of the aircraft ground leaving speed and a preset value.
Wherein, the preset value of the hysteresis loop link is 20-30 km/h.
And selecting the maximum ground leaving speed Vmax=340 km/h according to the obtained ground leaving speed calculation result, and designing a hysteresis loop of 20 km/h.
S3, taking the ground clearance speed as a corrected airspeed, converting the corrected airspeed into dynamic pressure, and taking the dynamic pressure as an input quantity for logically judging a bearing signal of the wheel;
when Vc is less than or equal to Cn, qc/Pn= [1+0.2 (Vc/Cn) 2 ] 3.5 –1
Wherein: vc is corrected airspeed in kilometers per hour (km/h);
cn is sea level standard sound velocity (1225.0584 km/h);
pn is sea level normal atmospheric pressure (101.325 kPa).
Through the formula, corresponding standard dynamic pressures are calculated to be 5569Pa and 6258Pa respectively according to the corrected airspeeds of 340km/h and 360 km/h.
Finally, the standard dynamic pressure and the wheel-carrying signal obtained based on the above process together form the use logic of the wheel-carrying signal based on speed protection.
The logic may be used to determine whether the aircraft is off-ground or in-air. For example, when judging the ground leaving state of the aircraft, on the basis of adopting the wheel bearing signals, standard dynamic pressure is added to comprehensively judge whether the aircraft is in the ground leaving state, and compared with the mode of singly using the wheel bearing signals for judging, the judgment result is more accurate.
The speed protection-based wheel bearing signal using method provided by the application is typical in structure, simple in parameter adjustment and easy to design, the reliability of judging the empty ground state of the wheel bearing state can be greatly improved, and the flight safety risk is reduced.
Finally, there is also provided a computer device comprising: one or more processors; a storage means for storing one or more programs; the one or more programs, when executed by the one or more processors, cause the one or more processors to implement the method of any of the preceding claims.
The present embodiments also provide a computer readable storage medium storing a computer program, which when executed by a processor, implements a method as described in any of the above.
It is to be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above-described embodiments, various steps, methods, apparatuses or modules may be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, may be implemented using any one or combination of the following techniques, as is well known in the art: discrete logic circuits having logic gates for implementing logic functions on data signals, application specific integrated circuits having suitable combinational logic gates, programmable Gate Arrays (PGAs), field Programmable Gate Arrays (FPGAs), and the like.
Those of ordinary skill in the art will appreciate that all or a portion of the steps carried out in the method of the above-described embodiments may be implemented by a program to instruct related hardware, where the program may be stored in a computer readable storage medium, and where the program, when executed, includes one or a combination of the steps of the method embodiments.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method for using a wheel-carried signal based on speed protection, comprising:
determining the ground leaving speeds of the aircraft with different external hanging configurations in the whole take-off weight range of the aircraft, wherein the process comprises the following steps of:
at the moment of aircraft off the ground, constructing an equation set with zero resultant force of the Y axis and Z axis resultant moment of the aircraft under a semi-airframe coordinate system, namely:
obtaining a nonlinear equation set:
wherein: p is the engine thrust; alpha is the angle of attack; g is the aircraft takeoff weight; y is Y p Distance from the thrust line of the engine to the center of gravity; c y 、m z Is the aerodynamic coefficient; s is the area of the wing; b a Is the average aerodynamic chord length; q is dynamic pressure; ap is the included angle between the thrust line of the engine and the horizontal datum line of the airplane;
obtaining the aircraft ground leaving speed Vmax according to the dynamic pressure calculation, namelyρ is the atmospheric density;
forming a speed protection range of the wheel load signal of the airplane by using the airplane ground leaving speed and a hysteresis loop link of the airplane ground leaving speed and a preset value;
and converting the speed protection range into a standard dynamic pressure range, and carrying out logic use of the wheel load signal according to the standard dynamic pressure range and the wheel load signal.
2. The method for using a speed protection-based wheel carrier signal according to claim 1, wherein the predetermined value of the hysteresis loop is (20-30) km/h.
3. The method of using a speed protection based wheel-carrying signal according to claim 1, wherein converting the speed protection range to a standard dynamic pressure range comprises:
judging the relation between the corrected airspeed and the sea level standard sound velocity Cn by taking the speed protection range as the corrected airspeed Vc;
when Vc is less than or equal to Cn, qc=pn ((1+0.2) (Vc/Cn) 2 ) 3.5 –1)；
Wherein Qc is a standard dynamic pressure and Pn is a sea level standard atmospheric pressure.
4. The speed protection based wheel-carried signal usage method of claim 1, wherein the logic usage comprises:
judging whether the aircraft is in a ground state according to the standard dynamic pressure range and the wheel-mounted signal of the aircraft wheel; and/or
And judging whether the aircraft is in a flight state according to the standard dynamic pressure range and the wheel-mounted signal of the aircraft wheel.
5. A computer device, comprising:
one or more processors;
a storage means for storing one or more programs;
the one or more programs, when executed by the one or more processors, cause the one or more processors to implement the method of any of claims 1-4.
6. A computer readable storage medium storing a computer program, which when executed by a processor implements the method of any one of claims 1 to 4.
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| CN113867395B (en) * | 2021-10-21 | 2024-05-03 | 四川腾盾科技有限公司 | Unmanned aerial vehicle take-off wheel monitoring method and system and storage medium |
| CN113955086B (en) * | 2021-11-03 | 2023-05-23 | 哈尔滨哈飞航空工业有限责任公司 | Method for judging air-ground state of airplane |
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