Method for determining maximum hinge moment of aileron of transport aircraft

Abstract

The present application belongs to the technical field of aircraft operation and control. Provided is a method for determining the maximum hinge moment of ailerons of a transport aircraft. The method comprises the following steps: determining a hinge moment calculation formula for ailerons of a transport aircraft; determining an aircraft speed when the maximum hinge moment of the ailerons occurs, and, on the basis of the aircraft speed, determining calculation parameters corresponding to the maximum hinge moment of the ailerons, the calculation parameters comprising aileron deflection and aircraft angle-of-attack; and, on the basis of the hinge moment calculation formula for ailerons and the calculation parameters, obtaining the maximum hinge moment of the ailerons. The method in the present application can perform rapid calculation only by obtaining the aircraft speed, aircraft angle-of-attack and aileron deflection corresponding to the maximum hinge moment of the ailerons, can rapidly obtain the maximum hinge moment of the ailerons without performing full-envelope and full-configuration hinge moment calculation, is suitable for determining the maximum hinge moment of ailerons during an aircraft schematic design phase, and achieves high accuracy of results.

Description

A method for determining the maximum hinge torque of ailerons in transport aircraft Technical Field

[0001] The present application relates to the field of aircraft operation control, and in particular to a method for determining the maximum hinge torque of ailerons of transport aircraft. Background Art

[0002] The maximum hinge torque is an important design input for aircraft flight control systems. The maximum hinge torque of each control surface has a significant impact on the design of the control surface actuator. It not only determines the weight and size of the actuator, but also affects the layout of the actuator in the aircraft. Therefore, determining the maximum hinge torque is a crucial task in aircraft design.

[0003] Typically, determining the maximum hinge torque for the aileron requires combining aerodynamic numerical calculations or hinge torque coefficients obtained from wind tunnel testing. This involves performing extensive calculations of the hinge torque for various configurations and maneuvers within the aircraft's full flight envelope, and then selecting a maximum hinge torque value based on the calculated results. However, this calculation method is relatively complex, requiring design input for the control surface limit curves and flight envelope, as well as complete data on the hinge torque coefficients. During the aircraft design phase, control surface limit curves had not yet been designed, and no hinge torque wind tunnel testing had been conducted. Consequently, a comprehensive and detailed understanding of the hinge torque coefficients was lacking. Therefore, it was crucial to quickly and accurately determine the maximum hinge torque during the aircraft design phase.

[0004] Summary of the Invention

[0005] The purpose of the present application is to provide a method for determining the maximum hinge moment of ailerons of a transport aircraft, so as to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a method for determining the maximum hinge torque of ailerons of a transport aircraft, the method comprising the following steps:

[0007] Determine a calculation formula for the aileron hinge moment of the transport aircraft;

[0008] determining an aircraft speed when a maximum aileron hinge moment occurs, and determining calculation parameters corresponding to the maximum aileron hinge moment based on the aircraft speed, the calculation parameters including aileron deflection and aircraft angle of attack;

[0009] The maximum aileron hinge moment is obtained according to the aileron hinge moment calculation formula and the calculation parameters.

[0010] In a preferred embodiment of the present application, the aileron hinge moment calculation formula of the transport aircraft is: M h =C h (ɑ、δα)qS δα b δα

[0011] Where: M h is the aileron hinge moment;

[0012] C h is the aileron hinge moment coefficient, which is the aircraft angle of attack ɑ and aileron deflection δ α function;

[0013] q is the speed pressure;

[0014] S δα is the aileron reference area;

[0015] b δα is the aileron reference length.

[0016] In a preferred embodiment of the present application, the dive speed is selected as the aircraft speed corresponding to the maximum hinge moment of the aileron.

[0017] In a preferred embodiment of the present application, 1 / 3 of the maximum positive deflection of the aileron at low speed is selected as the aileron deflection corresponding to the maximum hinge moment of the aileron.

[0018] In a preferred embodiment of the present application, the maneuvering angle of attack at a predetermined overload state at a dive speed is selected as the aircraft angle of attack corresponding to the maximum hinge moment of the aileron.

[0019] In a preferred embodiment of the present application, the maneuvering angle of attack is selected to be 4 degrees.

[0020] The method for determining the maximum hinge torque of the ailerons of transport aircraft proposed in this application only needs to obtain the aircraft speed when the maximum hinge torque of the aileron occurs and the corresponding aircraft angle of attack and aileron deflection to perform a rapid calculation. It can quickly obtain the maximum hinge torque of the aileron without performing full envelope and full configuration hinge torque calculations. This method is suitable for determining the maximum hinge torque of the aileron during the aircraft design stage, and the result has high accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0022] FIG1 is a schematic diagram of a method for determining the maximum hinge torque of ailerons of a transport aircraft according to the present application. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0024] In order to overcome the problem of not being able to quickly and accurately obtain the maximum hinge torque of the aileron due to the lack of many inputs in the aircraft planning stage, this application proposes a method for quickly determining the maximum hinge torque of the aileron of transport aircraft, which quickly gives the maximum hinge torque of the aileron without performing full-envelope and full-configuration hinge torque calculations.

[0025] As shown in FIG1 , the method for quickly determining the maximum hinge moment of ailerons of transport aircraft provided in this application includes the following steps:

[0026] Step 1: Determine the aileron hinge moment calculation formula for transport aircraft. The aileron hinge moment calculation formula is: M h =C h (α、δ α )qS δα b δα

[0027] Where: M h is the aileron hinge moment;

[0028] C h is the aileron hinge moment coefficient, which is the aircraft angle of attack ɑ and aileron deflection δ α function;

[0029] q is the speed pressure;

[0030] S δα is the aileron reference area;

[0031] b δα is the aileron reference length (or mean chord length).

[0032] Step 2: Determine the aircraft speed when the maximum aileron hinge moment occurs, and determine the calculation parameters corresponding to the maximum aileron hinge moment based on the aircraft speed. The calculation parameters include flap deflection and aircraft angle of attack.

[0033] The aileron hinge moment coefficient has a negative rate of change with the aircraft's angle of attack and aileron deflection. Analysis shows that the maximum aileron hinge moment coefficient occurs when the aileron is deflected downward and the angle of attack is maximum in all configurations. Since transport aircraft typically have a maximum overload of 2.5g (g is the acceleration due to gravity), the maximum aileron hinge moment occurs during a 2.5g overload, pull-up, and rapid roll, as the aircraft's required angle of attack is the highest among all flight conditions.

[0034] The maximum aileron hinge moment occurs when the aircraft is in the cruise configuration. The aircraft speed corresponding to the maximum aileron hinge moment is the dive speed V D , that is, the maximum speed point at which the aircraft may reach. Although the aileron deflection angle is limited by the rudder limit, the speed pressure increases larger and faster as the speed increases, eventually leading to an increase in the hinge torque.

[0035] Typically, the maximum hinge torque is calculated based on typical weights, aircraft configurations, and different speed-altitude envelopes. The angle of attack is the angle of attack during high-G maneuvers, and the aileron is the maximum positive deflection that varies with speed. A large number of calculations are performed using the above formula, and then a maximum hinge torque value is selected from the calculation results.

[0036] The aileron limit deflection curve is that the maximum aileron deflection angle decreases as the speed increases, and the maximum aileron deflection is a fixed value at low speed. According to the experience of the model, at the dive speed V D The corresponding aileron deflection is 1 / 3 of the maximum aileron deflection at low speed.

[0037] Since the angle of attack is large during high-overload maneuvers at maximum weight, the maximum weight is selected. Based on model experience, the dive speed V D The angle of attack during high-overload 2.5g maneuvers is approximately 4°.

[0038] In summary, in this application, the aircraft speed when the maximum hinge moment of the aileron occurs is the dive speed V D The corresponding calculation parameters include the aileron deflection is 1 / 3 of the maximum aileron deflection at low speed, the angle of attack is selected as the dive speed V D Maneuvering angle of attack at high overload 2.5g: In the preferred embodiment of the present application, the maneuvering angle of attack is selected to be 4°.

[0039] Step 3: The corresponding maximum aileron hinge moment can be calculated based on the aileron hinge moment calculation formula and the calculation parameters corresponding to the maximum aileron hinge moment determined in the above process (maneuvering angle of attack and 1 / 3 of the maximum positive deflection of the aileron at low speed).

[0040] The aircraft speed (dive speed V) when the maximum hinge moment occurs is determined by the calculation formula in step 1 and step 2. D ) and 1 / 3 of the maximum positive deflection of the aileron at low speed can be used to calculate the aileron hinge moment, which is the maximum aileron hinge moment.

[0041] For example, in this embodiment of the present application, a rapid calculation of the maximum hinge moment of the aileron is required at the design stage of a certain transport aircraft. The rapid calculation method of the maximum hinge moment of the aileron proposed in this application is used, and the known calculation parameters are as follows:

[0042] The aircraft dive speed of 600km / h is selected as the aircraft speed state corresponding to the maximum hinge torque of the aileron. D The maneuvering angle of attack at a high overload of 2.5g is used as the angle of attack for calculating the maximum hinge moment of the aileron. The maneuvering angle of attack is 4°. Since the maximum positive deflection of the aileron of this type of aircraft is 30°, 1 / 3 of the maximum positive deflection of the aileron at low speed, that is, 10°, is selected as the aileron deflection for calculating the maximum hinge moment of the aileron.

[0043] According to the formula, the above-mentioned known calculation parameters of the maneuvering angle of attack of 4° and the aileron deflection of 10° are substituted into the hinge moment coefficient data, and the corresponding aileron hinge moment coefficient is obtained to be -0.13. δα 1.4m 2 , aileron reference length (mean chord length) b δɑ The hinge moment is 0.5 m, which is calculated by substituting it into the formula and is -1548 N·m. This hinge moment is the maximum hinge moment of the aileron.

[0044] The method for quickly determining the maximum hinge torque of the ailerons of transport aircraft proposed in this application only needs to obtain the aircraft speed, aircraft angle of attack, and aileron deflection corresponding to the maximum hinge torque of the aileron to perform a rapid calculation. It can quickly obtain the maximum hinge torque of the aileron without performing a full-envelope and full-configuration hinge torque calculation. This method is suitable for determining the maximum hinge torque of the aileron during the aircraft design stage, and the result has high accuracy.

[0045] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for determining the maximum hinge moment of ailerons of transport aircraft, characterized in that: The method comprises the following steps: Determine a calculation formula for the aileron hinge moment of the transport aircraft; Determine the aircraft speed when the maximum hinge moment of the aileron occurs, and determine the calculation parameters corresponding to the maximum hinge moment of the aileron according to the aircraft speed, wherein the calculation parameters include aileron deflection and aircraft angle of attack; The maximum aileron hinge moment is obtained according to the aileron hinge moment calculation formula and the calculation parameters.

2. The method for determining the maximum hinge moment of aileron of a transport aircraft according to claim 1, characterized in that: The calculation formula for the aileron hinge moment of the transport aircraft is: M h =C h (α、δ α )qS δα b δα Where: M h is the aileron hinge moment; C h is the aileron hinge moment coefficient, which is the aircraft angle of attack α and the aileron deflection δ α Function of q is the speed pressure; S δα is the aileron reference area; b δα is the aileron reference length.

3. The method for determining the maximum hinge moment of aileron of a transport aircraft according to claim 2, characterized in that: The dive speed is selected as the aircraft speed at which the maximum hinge moment of the aileron occurs.

4. The method for determining the maximum hinge moment of aileron of a transport aircraft according to claim 3, characterized in that: Select 1 / 3 of the maximum positive deflection of the aileron at low speed as the aileron deflection in the calculation parameters.

5. The method for determining the maximum hinge moment of aileron of a transport aircraft according to claim 4, characterized in that: The maneuvering angle of attack at the predetermined overload state of the dive speed is selected as the aircraft angle of attack in the calculation parameters.

6. The method for determining the maximum hinge moment of aileron of a transport aircraft according to claim 5, characterized in that: The maneuvering angle of attack is selected to be 4 degrees.

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