CN117390899B - Method for determining maximum hinge moment of aileron of transport aircraft - Google Patents
Method for determining maximum hinge moment of aileron of transport aircraft Download PDFInfo
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Abstract
The application provides a method for determining the maximum hinge moment of an aileron of a transport aircraft, which belongs to the technical field of aircraft operation control, and comprises the following steps: determining an aileron hinge moment calculation formula of the transport aircraft; determining the aircraft speed when the maximum hinge moment of the aileron occurs, and determining the calculation parameters corresponding to the maximum hinge moment of the aileron according to the aircraft speed, wherein the calculation parameters comprise the aileron deflection and the aircraft attack angle; and obtaining the maximum aileron hinge moment according to the aileron hinge moment calculation formula and the calculation parameters. The method can be used for quickly calculating the aircraft speed, the aircraft attack angle and the aileron deflection corresponding to the maximum aileron hinge moment, and can quickly obtain the maximum aileron hinge moment under the condition of not calculating the full-envelope full-configuration hinge moment.
Description
Technical Field
The application belongs to the field of airplane operation control, and particularly relates to a method for determining a maximum hinge moment of an aileron of a transport airplane.
Background
The maximum hinge moment is an important design input for the design of an aircraft flight control system, the magnitude of the maximum hinge moment of each control surface has a great influence on the design of the control surface actuator, the weight and the size of the actuator are determined, and the arrangement scheme of the actuator in the aircraft is also influenced, so that the determination of the maximum hinge moment is an important work in the aircraft design.
The determination of the maximum hinge moment of the aileron generally needs to combine the hinge moment coefficient obtained by pneumatic digital calculation or wind tunnel test, and a maximum hinge moment value is screened according to the calculation result by carrying out a large amount of calculation on the hinge moment of each configuration under the full flight envelope of the aircraft in different maneuver. However, the calculation method is complex, the design input of the control surface deflection limiting curve and the flight envelope is required, all data of the hinge moment coefficient is also required, the control surface deflection limiting curve is not designed in the design stage of the airplane scheme, and the hinge moment wind tunnel test is not developed, so that the comprehensive and detailed hinge moment coefficient is lacking, and then the method for quickly acquiring the accurate maximum hinge moment in the design stage of the airplane scheme is very necessary.
Disclosure of Invention
It is an object of the present application to provide a method for determining a maximum hinge moment for an aileron of a transportation aircraft, which solves or mitigates at least one of the problems of the background art.
The technical scheme of the application is as follows: a method of determining a maximum hinge moment for an aileron of a transport aircraft, the method comprising the steps of:
determining an aileron hinge moment calculation formula of the transport aircraft;
determining the aircraft speed when the maximum hinge moment of the aileron occurs, and determining the calculation parameters corresponding to the maximum hinge moment of the aileron according to the aircraft speed, wherein the calculation parameters comprise the aileron deflection and the aircraft attack angle;
and obtaining the maximum aileron hinge moment according to the aileron hinge moment calculation formula and the calculation parameters.
In a preferred embodiment of the present application, the aileron hinge moment calculation formula of the transport aircraft is:
wherein: m is M h Is the aileron hinge moment;
C h is the moment coefficient of the aileron hinge, which is the attack angle alpha and the aileron of the airplaneDegree of camber delta α Is a function of (2);
q is rapid pressing;
S δ α is the aileron reference area;
b δ α reference length for aileron.
In a preferred embodiment of the present application, the nose down speed is selected as the aircraft speed corresponding to the maximum hinge moment of the aileron.
In the preferred embodiment of the application, 1/3 of the low-speed maximum positive deflection of the aileron is selected as the aileron deflection corresponding to the maximum hinge moment of the aileron.
In a preferred embodiment of the present application, the angle of attack of the aircraft corresponding to the maximum hinge moment of the aileron is selected as the maneuver angle of attack for the predetermined overload state of the nose down speed.
In a preferred embodiment of the present application, the maneuver angle of attack is chosen to be 4 degrees.
The method for determining the maximum hinge moment of the aileron of the transport aircraft can be used for carrying out quick calculation only by obtaining the aircraft speed when the maximum hinge moment of the aileron occurs and the corresponding aircraft attack angle and aileron deflection, and can be used for quickly obtaining the maximum hinge moment of the aileron under the condition of not carrying out calculation of the full envelope curve and the full configuration hinge moment.
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 a method for determining a maximum hinge moment of an aileron of a transport aircraft.
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.
In order to overcome the defect that the maximum hinge moment of the aileron cannot be obtained rapidly and accurately under the condition of lacking a lot of inputs in the scheme stage of the airplane, the application provides a rapid determination method for the maximum hinge moment of the aileron of the transportation type airplane, and the maximum hinge moment of the aileron is rapidly given under the condition of not carrying out calculation of the full-envelope full-configuration hinge moment.
As shown in fig. 1, the method for quickly determining the maximum hinge moment of the aileron of the transport airplane provided by the application comprises the following steps:
step one, determining an aileron hinge moment calculation formula of a transport airplane, wherein the aileron hinge moment calculation formula is as follows:
wherein: m is M h Is the aileron hinge moment;
C h is the moment coefficient of the aileron hinge, which is the aircraft attack angle alpha and aileron deflection delta α Is a function of (2);
qis quick-pressing;
S δ α is the aileron reference area;
b δ α is the aileron reference length (or average chord length).
And step two, determining the airplane speed when the maximum hinge moment of the aileron occurs, and determining the calculation parameters corresponding to the maximum hinge moment of the aileron according to the airplane speed, wherein the calculation parameters comprise the flap deflection and the airplane attack angle.
The rate of change of the aileron hinge moment coefficient with aircraft angle of attack and aileron deflection is negative. The maximum hinge moment coefficient of the aileron of the airplane can be obtained through analysis when the aileron of each configuration is deflected downwards and the attack angle is maximum. Since transport aircraft are typically maximally overloaded with 2.5g (g gravitational acceleration), the flap maximum hinge moment occurs during conditions that produce 2.5g of overload pull-up and rapid roll, since the angle of attack required by the aircraft is at its greatest in each flight regime.
The maximum value of the aileron hinge moment appears in the state that the airplane is in a cruising configuration, and the corresponding airplane speed when the maximum aileron hinge moment occurs is the dive speed V D I.e. the maximum speed point that the aircraft may have, the aileron deflection angle is limited by the control surface deflection, but thereafter the velocity increases more rapidly with increasing velocity, eventually leading to an increase in hinge moment.
The calculation of the maximum hinge moment is generally combined with each typical weight, each airplane configuration and different speed altitude envelopes, the attack angle is the attack angle when the overload maneuver is large, the aileron is the deflection limiting maximum positive deflection along with the speed change, the formula is used for carrying out mass calculation, and then a maximum hinge moment value is screened out from the calculation result.
The aileron deflection limiting curve is that the maximum deflection angle of the aileron is reduced along with the increase of the speed, and the maximum deflection of the aileron is a fixed value at low speed. According to model experience, at the dive speed V D The corresponding aileron deflection is 1/3 of the low-speed maximum aileron deflection.
Because the attack angle is large when the overload is large under the maximum weight, the maximum weight is selected, and the diving speed V is calculated according to model experience D The angle of attack is about 4 ° when a large overload of 2.5g is maneuvered.
To sum up, the aircraft speed at which the maximum hinge moment of the aileron occurs in the present application is the dive speed V D The corresponding calculation parameters comprise that the aileron deflection is 1/3 of the low-speed maximum aileron deflection, and the attack angle is selected as the diving speed V D The maneuver attack angle at a large overload of 2.5 g. In a preferred embodiment of the present application, the maneuver angle of attack is chosen to be 4 °.
And thirdly, calculating the corresponding aileron maximum hinge moment according to an aileron hinge moment calculation formula and the calculation parameters (the maneuvering attack angle and 1/3 of the aileron low-speed maximum positive deflection) corresponding to the aileron maximum hinge moment determined in the process.
The aircraft speed (dive speed V) at which the maximum hinge moment determined in step two occurs is calculated by the calculation formula in step one D ) The corresponding maneuvering attack angle and 1/3 of the low-speed maximum positive deflection of the aileron can calculate the aileron hinge moment, and the hinge moment is the maximum aileronLarge hinge moment.
For example, in this embodiment of the present application, a fast calculation of the maximum hinge moment of the aileron is required in a scheme stage of a certain transportation aircraft, and the method for fast calculating the maximum hinge moment of the aileron is adopted, and known calculation parameters are as follows:
and selecting the aircraft diving speed of 600km/h as an aircraft speed state corresponding to the maximum hinge moment of the aileron. Selecting the dive speed V D The maneuvering attack angle at the time of 2.5g of large overload is taken as the attack angle at the time of calculating the maximum hinge moment of the aileron, the maneuvering attack angle is taken as 4 degrees, and 1/3 of the low-speed maximum positive deflection of the aileron is selected as the limit positive deflection of the aileron of the airplane at 30 degrees, namely, 10 degrees is taken as the aileron deflection at the time of calculating the maximum hinge moment of the aileron.
And carrying the maneuvering attack angle of 4 degrees and the aileron deflection of 10 degrees of the known calculation parameters into the hinge moment coefficient data according to a formula, and solving the corresponding aileron hinge moment coefficient to be-0.13. The aircraft aileron reference areaS δα 1.4m 2 Aileron reference length (average chord)b δα The hinge moment is-1548 N.m after being carried into a formula to calculate and is 0.5m, and the hinge moment is the maximum hinge moment of the aileron.
The method for quickly determining the maximum hinge moment of the aileron of the transport aircraft can quickly calculate only by obtaining the aircraft speed, the aircraft attack angle and the aileron deflection corresponding to the maximum hinge moment of the aileron, can quickly obtain the maximum hinge moment of the aileron under the condition of not calculating the full-envelope full-configuration hinge moment, is suitable for determining the maximum hinge moment of the aileron in the design stage of an aircraft scheme, and has higher result accuracy.
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 (5)
1. A method for determining a maximum hinge moment for an aileron of a transport aircraft, the method comprising the steps of:
determining an aileron hinge moment calculation formula of the transport aircraft, wherein the aileron hinge moment calculation formula of the transport aircraft is as follows:
M h ＝C h (α、δ a )qS δa b δa
wherein: m is M h Is the aileron hinge moment;
C h is the moment coefficient of the aileron hinge, which is the aircraft attack angle alpha and aileron deflection delta a Is a function of (2);
q is rapid pressing;
S δa is the aileron reference area;
b δa reference length for aileron;
determining the aircraft speed when the maximum hinge moment of the aileron occurs, and determining the calculation parameters corresponding to the maximum hinge moment of the aileron according to the aircraft speed, wherein the calculation parameters comprise the aileron deflection and the aircraft attack angle;
and obtaining the maximum aileron hinge moment according to the aileron hinge moment calculation formula and the calculation parameters.
2. A method of determining the maximum hinge moment of an aileron of a transport aircraft as in claim 1, wherein the dive speed is selected as the aircraft speed corresponding to the maximum hinge moment of the aileron.
3. A method of determining the maximum hinge moment of an aileron of a transport aircraft as claimed in claim 2, wherein 1/3 of the maximum positive deviation of the aileron at low speed is selected as the aileron deviation in the calculated parameters.
4. A method of determining the maximum hinge moment for a transport aircraft aileron as in claim 3, wherein the angle of incidence of the aircraft in the calculated parameter is selected as the angle of incidence for the nose down speed at a predetermined overload condition.
5. A method of determining the maximum hinge moment for a transportation aircraft aileron as in claim 4, wherein the maneuver angle of attack is selected to be 4 degrees.
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| RU2018107190A3 (en) * | 2018-02-26 | 2019-08-26 | ||
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| US20200410147A1 (en) * | 2019-06-28 | 2020-12-31 | Viettel Group | Aerodynamic derivatives calculation method for flight vehicle |
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