CN112731958A - Airborne wheel-borne signal using method based on speed protection - Google Patents
Airborne wheel-borne signal using method based on speed protection Download PDFInfo
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Abstract
The application provides an airborne wheel-borne signal application method based on speed protection, which belongs to the technical field of flight control, and comprises the following steps: determining the ground clearance speeds of the airplanes with different external hanging configurations within the whole takeoff weight range of the airplane; forming a speed protection range of the wheel load signal by the airplane ground clearance, the airplane ground clearance and a hysteresis loop of a preset value; and converting the speed protection range into a standard dynamic pressure range, and performing logic use on the wheel load signal according to the standard dynamic pressure range and the wheel load signal. According to the method, the air-ground state of the airplane is judged by adding the standard dynamic pressure and combining the airborne wheel load signal, so that the judgment reliability can be improved, and the flight safety risk is reduced.
Description
Technical Field
The application belongs to the field of flight control technology, and particularly relates to an airborne wheel-borne signal using method based on speed protection.
Background
The flight state 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 classified 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 is switched by the retraction state of the undercarriage, and the control law of the landing and the sliding is switched by the bearing signal of the airplane wheel. The wheel-mounted signal is used as an important signal for ground-to-air judgment of the airplane control system, influences the functions of control, calibration, test and the like of the system, and has important significance on the safety and reliability of the system.
However, in the prior art, the problem of low reliability judgment of the air-ground state exists when the airplane wheel load signal is simply used for logic control, and the flight safety risk exists.
Disclosure of Invention
It is an object of the present application to provide a method for using an onboard wheel-borne signal based on speed protection to solve or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: an airborne wheel-borne signal use method based on speed protection comprises the following steps:
determining the ground clearance speeds of the airplanes with different external hanging configurations within the whole takeoff weight range of the airplane;
forming a speed protection range of the wheel load signal by the airplane ground clearance, the airplane ground clearance and a hysteresis loop of a preset value;
and converting the speed protection range into a standard dynamic pressure range, and performing logic use on the wheel load signal according to the standard dynamic pressure range and the wheel load signal.
Further, the process of determining the ground clearance speeds of the airplanes with different plug-in configurations based on the whole takeoff weight range of the airplane comprises the following steps:
at the moment when the airplane leaves the ground, an equation set with zero resultant force of the Y axis and zero resultant moment of the Z axis of the airplane under a semi-body coordinate system is constructed, namely:
obtaining a nonlinear equation set:
in the formula: p is engine thrust; alpha is an attack angle; g is the takeoff weight of the airplane; y ispThe distance from the thrust line of the engine to the center of gravity; c. Cy、mzIs the aerodynamic coefficient; s is the wing area; baIs the mean 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;
calculating the ground speed Vmax of the airplane according to the dynamic pressure, namely
ρ is the atmospheric density.
Further, the preset value of the hysteresis loop is (20-30) km/h.
Further, the process of converting the speed protection range into a standard dynamic pressure range includes:
taking the speed protection range as a corrected airspeed Vc, and judging the relation between the corrected airspeed and a sea level standard sound velocity Cn;
when Vc is equal to or less than Cn, Qc equals Pn ((1+0.2(Vc/Cn)2)3.5–1)；
Where Qc is the standard dynamic pressure and Pn is the sea level standard atmospheric pressure.
Further, the logic using comprises: judging whether the airplane is in a ground state or not according to the standard dynamic pressure range and the airplane wheel load signal; and/or judging whether the airplane is in a flying state or not according to the standard dynamic pressure range and the airplane wheel load signal.
According to the method, the air-ground state of the airplane is judged by adding the standard dynamic pressure and combining the airborne wheel load signal, so that the judgment reliability 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 briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic diagram illustrating a method for using an airborne wheel-borne signal based on speed protection according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
Aiming at the situation that in the prior art, only wheel load signals (also called wheel load signals) are adopted in the air ground state of an airplane, so that safety and reliability are not high, the application provides a method for using the wheel load signals based on speed protection, and the requirement for high reliability of the wheel load signals is met.
As shown in fig. 1, the method provided by the present application includes the following steps:
and S1, calculating the ground clearance of the airplanes with different external hanging configurations within the range of covering the whole takeoff weight of the airplane.
Specifically, according to the relevant requirements of the airplane and the engine, the parameters such as the thrust of the engine, the ground clearance attack angle and the like can be obtained.
At the moment of leaving the ground, in a semi-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 system is established, namely:
obtaining a nonlinear equation set after finishing:
wherein, P is engine thrust, 16000kg in the embodiment;
α is an angle of attack, i.e., angle of attack, which in this embodiment is 10 °;
g is the takeoff weight of the airplane, which is 40t in the embodiment;
Ypthe distance from the engine thrust line to the center of gravity (positive for producing a low head moment, in this example-0.3 m;
cy、mzthe aerodynamic coefficients are 1.129 and-0.054 respectively in the embodiment;
s is the wing area, in this embodimentIs 62m2；
baThe mean aerodynamic chord length is 4m in this example;
q is dynamic pressure, 300kg/m in this example2；
ap is the included angle between the engine thrust line and the horizontal datum line of the airplane (the head-up is positive), and is 2 degrees in the embodiment;
the dynamic pressure Q can be obtained through the nonlinear shelter group, and then the dynamic pressure Q is obtained through a formula
The ground clearance speed Vmax can be obtained. Under the parameters of the above embodiment, the ground clearance speed is calculated to be Vmax 340 km/h.
And S2, forming a speed protection range value of the wheel load signal by the airplane ground clearance, the airplane ground clearance and a hysteresis loop of a preset value.
Wherein the preset value of the hysteresis loop is 20-30 km/h.
And selecting the maximum ground clearance Vmax as 340km/h according to the obtained ground clearance calculation result, and designing a hysteresis loop of 20 km/h.
S3, converting the corrected airspeed into dynamic pressure by taking the ground clearance as the corrected airspeed, and taking the dynamic pressure as the input quantity of the airplane wheel bearing signal logic judgment;
when Vc is less than or equal to Cn, qc/Pn is [1+0.2(Vc/Cn)2]3.5–1
In the formula: vc is corrected airspeed, and the unit is kilometer per hour (km/h);
cn is the standard sound velocity at sea level (1225.0584 km/h);
pn is sea level standard atmospheric pressure (101.325 kPa).
Through the formula, the corresponding standard dynamic pressure is respectively 5569Pa and 6258Pa by calculating the corrected airspeed at 340km/h and 360 km/h.
And finally, forming the use logic of the airplane wheel bearing signal based on speed protection together with the standard dynamic pressure and the airplane wheel bearing signal obtained based on the process.
Wherein, the logic of use can judge the ground state of the airplane or the air state of the airplane. For example, when the off-ground state of the airplane is judged, on the basis of adopting the airplane wheel to bear the signals, the standard dynamic pressure is added to comprehensively judge whether the airplane is in the off-ground state, and compared with the method of judging by singly using the airplane wheel to bear the signals, the judgment result is more accurate.
The airplane wheel bearing signal using method based on speed protection is typical in structure, simple in tuning parameter and easy to design, reliability of airplane wheel bearing state to air state judgment can be greatly improved, and flight safety risks are reduced.
Finally, there is also provided in the present application a computer device comprising: one or more processors; 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 as in any one of the above.
An embodiment of the present application further provides a computer-readable storage medium storing a computer program, which when executed by a processor implements the method as described in any one of the above.
It should be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, various steps, methods, apparatuses or modules may be implemented by 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, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
It will be understood by those skilled in the art that all or part of the steps carried by the method for implementing the above embodiments may be implemented by hardware related to instructions of a program, which may be stored in a computer readable storage medium, and when the program is executed, the program includes one or a combination of the steps of the method embodiments.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within 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 (7)
1. An airborne wheel-borne signal use method based on speed protection is characterized by comprising the following steps:
determining the ground clearance speeds of the airplanes with different external hanging configurations within the whole takeoff weight range of the airplane;
forming a speed protection range of the wheel load signal by the airplane ground clearance, the airplane ground clearance and a hysteresis loop of a preset value;
and converting the speed protection range into a standard dynamic pressure range, and performing logic use on the wheel load signal according to the standard dynamic pressure range and the wheel load signal.
2. The method for using the airborne wheel-borne signal based on the speed protection as claimed in claim 1, wherein the process of determining the ground-off speed of the aircraft with different plug-in configurations based on the whole takeoff weight range of the aircraft comprises the following steps:
at the moment when the airplane leaves the ground, an equation set with zero resultant force of the Y axis and zero resultant moment of the Z axis of the airplane under a semi-body coordinate system is constructed, namely:
obtaining a nonlinear equation set:
in the formula: p is engine thrust; alpha is an attack angle; g is the takeoff weight of the airplane; y ispThe distance from the thrust line of the engine to the center of gravity; c. Cy、mzIs the aerodynamic coefficient; s is the wing area; baIs the mean 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;
calculating the ground speed Vmax of the airplane according to the dynamic pressure, namely
ρ is the atmospheric density.
3. The use method of the airborne wheel-borne signals based on the speed protection as claimed in claim 1, wherein the predetermined value of the hysteresis loop is (20-30) km/h.
4. The method for using the onboard wheel-borne signals based on the speed protection as claimed in claim 1, wherein the process of converting the speed protection range into a standard dynamic pressure range comprises the following steps:
taking the speed protection range as a corrected airspeed Vc, and judging the relation between the corrected airspeed and a sea level standard sound velocity Cn;
when Vc is equal to or less than Cn, Qc equals Pn ((1+0.2(Vc/Cn)2)3.5–1)；
Where Qc is the standard dynamic pressure and Pn is the sea level standard atmospheric pressure.
5. The method of using an onboard wheel-borne signal based on speed protection according to claim 1, wherein the logic using comprises:
judging whether the airplane is in a ground state or not according to the standard dynamic pressure range and the airplane wheel load signal; and/or
And judging whether the airplane is in a flying state or not according to the standard dynamic pressure range and the airplane wheel load signal.
6. A computer device, comprising:
one or more processors;
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 1-5.
7. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the method according to any one of claims 1 to 5.
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Cited By (2)
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| CN113867395A (en) * | 2021-10-21 | 2021-12-31 | 四川腾盾科技有限公司 | Monitoring method and system for take-off wheel of unmanned aerial vehicle and storage medium |
| CN113955086A (en) * | 2021-11-03 | 2022-01-21 | 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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