Method for determining maximum hinge moment of spoiler of transport aircraft

Abstract

The present application relates to the field of aircraft control systems, and, in particular, to a method for determining a maximum hinge moment of a spoiler of a transport aircraft. The method comprises: step 1, determining a flap state and a velocity state corresponding to a maximum hinge moment; step 2, on the basis of the flap state and the velocity state, determining an angle of attack and a spoiler deviation corresponding to the maximum hinge moment; and step 3, acquiring a maximum hinge moment computation model, and inputting the angle of attack and the spoiler deviation into the maximum hinge moment computation model, to compute the maximum hinge moment. The present application provides a method for selecting a corresponding flap state, velocity state, angle of attack, and spoiler deviation when computing the maximum hinge moment of the spoiler, and provides a computation model for quickly computing the maximum hinge moment. The maximum hinge moment of the spoiler can be quickly obtained without computing a hinge moment of a full envelope and full configuration, which is suitable for determining the maximum hinge moment of the spoiler in an aircraft scheme design phase, and the accuracy of the result is high.

Description

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

[0001] The present application relates to the field of aircraft control systems, and in particular to a method for determining the maximum hinge torque of a spoiler of a 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 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 requires combining aerodynamic numerical calculations or hinge torque coefficients obtained from wind tunnel testing. Numerous calculations are performed on the hinge torque for various maneuvers across the aircraft's full flight envelope, and a maximum hinge torque value is selected based on the calculated results. This traditional calculation method is relatively complex, requiring design input for control surface limit curves and the flight envelope, as well as complete data on the hinge torque coefficients. During the aircraft design phase, control surface limit curves have yet to be developed, and no hinge torque wind tunnel testing has been conducted. Consequently, a comprehensive and detailed understanding of the hinge torque coefficients is lacking. Therefore, it is crucial to quickly and accurately determine the maximum hinge torque during the aircraft design phase.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art.

[0005] Summary of the Invention

[0006] The purpose of this application is to provide a method for determining the maximum hinge torque of a spoiler of a transport aircraft to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is:

[0008] A method for determining the maximum hinge moment of a spoiler of a transport aircraft comprises:

[0009] Step 1: determine the flap state and speed state corresponding to the maximum hinge moment;

[0010] Step 2: determining the angle of attack and spoiler deflection corresponding to the maximum hinge moment according to the flap state and the speed state;

[0011] Step 3: Obtain a maximum hinge moment calculation model, input the angle of attack and the spoiler deflection into the maximum hinge moment calculation model, and calculate the maximum hinge moment.

[0012] In at least one embodiment of the present application, in step 1, determining the flap state and speed state corresponding to the maximum hinge moment includes:

[0013] The flap state corresponding to the maximum hinge torque in the spoiler closed state is the landing configuration. In the landing configuration, the speed state corresponding to the maximum hinge torque in the spoiler closed state is the aircraft flap limit speed V FE ;

[0014] The flap state corresponding to the maximum hinge torque in the spoiler open state is the cruise configuration. In the cruise configuration, the speed state corresponding to the maximum hinge torque in the spoiler open state is the aircraft dive speed V D .

[0015] In at least one embodiment of the present application, in step 2, determining the angle of attack corresponding to the maximum hinge moment according to the flap state and the speed state includes:

[0016] In the landing configuration, the angle of attack corresponding to the maximum hinge moment in the spoiler closed state is the aircraft flap limit speed V FE , maneuvering angle of attack at 2.0g overload;

[0017] In the cruise configuration, the angle of attack corresponding to the maximum hinge moment in the spoiler-open state is the aircraft dive speed V D The trim angle of attack at .

[0018] In at least one embodiment of the present application,

[0019] Aircraft flap limit speed V FE , the maneuvering angle of attack at 2.0g overload is 5°;

[0020] Aircraft dive speed V D The trim angle of attack is 0°.

[0021] In at least one embodiment of the present application, in step 2, determining the spoiler deflection corresponding to the maximum hinge moment according to the flap state and the speed state includes:

[0022] In the landing configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler closed state is the spoiler low-speed limit deflection;

[0023] In the cruise configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler-open state is 2 / 3 of the maximum positive deflection of the spoiler at low speed.

[0024] In at least one embodiment of the present application, in step three, obtaining a maximum hinge moment calculation model, inputting the angle of attack and the spoiler deflection into the maximum hinge moment calculation model, and calculating the maximum hinge moment includes:

[0025] Get the maximum hinge moment calculation model:

[0026] Among them, M h is the maximum hinge moment, C h is the spoiler hinge moment coefficient, C h is the angle of attack α and the spoiler deflection δ sp function, q is the velocity pressure, is the reference area of ​​the spoiler, is the reference length of the spoiler;

[0027] Inputting the angle of attack and the spoiler deflection corresponding to the maximum hinge moment in the spoiler closed state into the maximum hinge moment calculation model to calculate the maximum hinge moment in the spoiler closed state;

[0028] The angle of attack and the spoiler deflection corresponding to the maximum hinge moment in the spoiler-open state are input into the maximum hinge moment calculation model to calculate the maximum hinge moment in the spoiler-open state.

[0029] The invention has at least the following beneficial technical effects:

[0030] The method for determining the maximum hinge torque of a spoiler for a transport aircraft disclosed in the present application determines the angle of attack and spoiler deflection corresponding to the maximum hinge torque of the spoiler according to the flap state and the speed state, and quickly calculates the maximum hinge torque through a maximum hinge torque calculation model, with a high degree of accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] FIG1 is a flow chart of a method for determining a maximum hinge torque of a spoiler for a transport aircraft according to one embodiment of the present application. DETAILED DESCRIPTION

[0032] 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. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0033] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0034] The present application is further described in detail below with reference to FIG1 .

[0035] The present application provides a method for determining the maximum hinge torque of a spoiler of a transport aircraft, comprising the following steps:

[0036] Step 1: determine the flap state and speed state corresponding to the maximum hinge moment;

[0037] Step 2: Determine the angle of attack and spoiler deflection corresponding to the maximum hinge moment based on the flap state and speed state;

[0038] Step 3: Obtain a maximum hinge moment calculation model, input the angle of attack and spoiler deflection into the maximum hinge moment calculation model, and calculate the maximum hinge moment.

[0039] In the method for determining the maximum hinge torque of a spoiler for a transport aircraft of the present application, the directions of the maximum hinge torques in the spoiler closed state and the spoiler open state are different. Therefore, the maximum hinge torque of the spoiler needs to be given simultaneously with the maximum hinge torque of the spoiler closed state and the maximum hinge torque of the spoiler open state.

[0040] The present invention relates to a method for determining the maximum hinge torque of spoilers for transport aircraft. The hinge torque coefficient for the spoiler-closed state increases with increasing aircraft angle of attack. Analysis shows that the maximum hinge torque for the spoiler-closed state occurs in the landing configuration. The hinge torque coefficient for the spoiler-open state is greater at low angles of attack than at high angles of attack. Analysis shows that the maximum hinge torque for the spoiler-open state occurs in the cruise configuration.

[0041] In a preferred embodiment of the present application, according to the above analysis, in step 1, determining the flap state and speed state corresponding to the maximum hinge moment includes:

[0042] The flap state corresponding to the maximum hinge torque in the spoiler closed state is the landing configuration. In the landing configuration, the speed state corresponding to the maximum hinge torque in the spoiler closed state is the aircraft flap limit speed V FE ;

[0043] The flap state corresponding to the maximum hinge torque in the spoiler open state is the cruise configuration. In the cruise configuration, the speed state corresponding to the maximum hinge torque in the spoiler open state is the aircraft dive speed V D .

[0044] In this embodiment, determining the angle of attack corresponding to the maximum hinge moment according to the flap state and the speed state includes:

[0045] In the landing configuration, the angle of attack corresponding to the maximum hinge moment in the spoiler closed state is the aircraft flap limit speed V FE , maneuvering angle of attack at 2.0g overload;

[0046] In the cruise configuration, the angle of attack corresponding to the maximum hinge moment in the spoiler-open state is the aircraft dive speed V D The trim angle of attack at .

[0047] In this embodiment, determining the spoiler deflection corresponding to the maximum hinge moment according to the flap state and the speed state includes:

[0048] In the landing configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler closed state is the spoiler low-speed limit deflection;

[0049] In the cruise configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler-open state is 2 / 3 of the maximum positive deflection of the spoiler at low speed.

[0050] The method for determining the maximum hinge moment of a transport aircraft spoiler of the present application is as follows: in the landing configuration, since the maximum overload of a transport aircraft landing configuration is usually 2.0g, the angle of attack condition at which the maximum hinge moment of the spoiler occurs is the aircraft flap limit speed V FE , the angle of attack corresponding to 2.0g overload. In this embodiment, based on model experience, in the landing configuration, the aircraft flap limit speed V FE , when the overload is 2.0g, the maneuvering angle of attack is about 5°.

[0051] The method for determining the maximum hinge torque of the spoiler of a transport aircraft in this application is based on model experience. In the cruise configuration, the aircraft dive speed V D The trim angle of attack is about 0°. Although the spoiler deflection is limited by the rudder deflection limit, the speed pressure increases faster and faster with the increase of speed, which eventually leads to an increase in the hinge torque. The spoiler deflection limit curve shows that the maximum deflection angle of the spoiler decreases with the increase of speed. At low speed, the maximum deflection of the spoiler is a fixed value. According to the experience of the model, in the cruise configuration, corresponding to the deceleration function, at the aircraft dive speed V D The corresponding spoiler deflection is 2 / 3 of the maximum positive deflection at low speed.

[0052] The method for determining the maximum hinge torque of a spoiler for a transport aircraft of the present application uses the following calculation model to obtain the maximum hinge torque:

[0053] Among them, M h is the maximum hinge moment, C h is the spoiler hinge moment coefficient, C h is the angle of attack α and the spoiler deflection δ sp function, q is the velocity pressure, is the reference area of ​​the spoiler, is the reference length of the spoiler.

[0054] The spoiler hinge torque coefficient is a function of the angle of attack and spoiler deflection. A data matrix of the spoiler hinge torque coefficients related to the angle of attack and spoiler deflection is obtained in advance through experiments or calculations. When used in practice, the corresponding spoiler hinge torque coefficient can be obtained by interpolating the data matrix according to the actual angle of attack and spoiler deflection.

[0055] Finally, the angle of attack and spoiler deflection corresponding to the maximum hinge torque in the spoiler-closed state obtained according to the above method are input into the maximum hinge torque calculation model to calculate the maximum hinge torque in the spoiler-closed state; and the angle of attack and spoiler deflection corresponding to the maximum hinge torque in the spoiler-open state obtained according to the above method are input into the maximum hinge torque calculation model to calculate the maximum hinge torque in the spoiler-open state.

[0056] In one embodiment of the present application, the process of using the above method to quickly calculate the maximum hinge moment of the spoiler in a certain transport aircraft design phase is as follows:

[0057] (1) Determine the flap state and speed state corresponding to the maximum hinge moment:

[0058] The flap state with the maximum hinge moment in the spoiler closed state is the landing configuration, and the aircraft flap limit speed of 310 km / h is selected as the speed state corresponding to the maximum hinge moment in the spoiler closed state.

[0059] The flap state with the maximum hinge torque when the spoiler is opened is the cruise configuration, and the aircraft dive speed of 600 km / h is selected as the speed state corresponding to the maximum hinge torque when the spoiler is opened.

[0060] (2) Determine the angle of attack and spoiler deflection corresponding to the maximum hinge moment

[0061] When calculating the maximum hinge moment with the spoiler closed, the angle of attack is the flap limit speed V of the aircraft in the landing configuration. FE , the corresponding maneuvering angle of attack at 2.0g overload. Based on model experience, the maneuvering angle of attack is 5°, and the flow vane deflection is selected as 0°.

[0062] When calculating the maximum hinge moment when the spoiler is open, the angle of attack is the dive speed V of the aircraft in the cruise configuration.D The trim angle of attack is set at 0° based on model experience, and the vane deflection is selected to be 2 / 3 of the maximum positive deflection of the spoiler at low speed. The maximum positive deflection of the spoiler at low speed is 24°, which means the vane deflection is 16°.

[0063] (3) Determine the maximum hinge moment of the spoiler

[0064] According to the formula Substituting the maneuvering angle of attack of 5° and the spoiler deflection of 0° into the landing configuration hinge moment coefficient function, the corresponding spoiler hinge moment coefficient is -0.80. The reference area of ​​the aircraft spoiler is 0.4m 2 The reference length of the spoiler (i.e. the average chord length) is 0.4m. After being substituted into the formula for calculation, the hinge torque is -581N.m, which is the maximum hinge torque when the spoiler is closed.

[0065] According to the formula Substituting the trim angle of attack of 0° and the spoiler deflection of 16° into the cruise configuration hinge moment coefficient function, the corresponding spoiler hinge moment coefficient is 0.15. The reference area of ​​the aircraft spoiler is 0.4m 2 The reference length of the spoiler (i.e. the average chord length) is 0.4m. After being substituted into the formula for calculation, the hinge torque is 408N.m, which is the maximum hinge torque when the spoiler is in the open state.

[0066] This application presents a method for determining the maximum hinge torque of spoilers on transport aircraft. It provides a method for selecting the corresponding flap state, speed state, angle of attack, and spoiler deflection when calculating the maximum hinge torque of the spoiler, and also provides a computational model for rapidly calculating the maximum hinge torque. This method can quickly determine the maximum hinge torque of a spoiler without performing full-envelope, full-configuration hinge torque calculations. This method is suitable for determining the maximum hinge torque of a spoiler during the aircraft design phase, and the results are highly accurate. This application has already been applied in aircraft with positive results.

[0067] The above description is merely a specific embodiment of the present application, but the scope of protection of this application is not limited thereto. Any modifications 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 this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

Claims

1. A method for determining the maximum hinge moment of a spoiler of a transport aircraft, characterized in that: include: Step 1, determining the flap state and speed state corresponding to the maximum hinge moment; Step 2: determining the angle of attack and spoiler deflection corresponding to the maximum hinge moment according to the flap state and the speed state; Step 3: Obtain a maximum hinge moment calculation model, input the angle of attack and the spoiler deflection into the maximum hinge moment calculation model, and calculate the maximum hinge moment.

2. The method for determining the maximum hinge moment of a spoiler of a transport aircraft according to claim 1, characterized in that: In step 1, the flap state and speed state corresponding to the maximum hinge moment are determined, including: The flap state corresponding to the maximum hinge torque in the spoiler closed state is the landing configuration. In the landing configuration, the speed state corresponding to the maximum hinge torque in the spoiler closed state is the aircraft flap limit speed V FE ; The flap state corresponding to the maximum hinge torque in the spoiler open state is the cruise configuration. In the cruise configuration, the speed state corresponding to the maximum hinge torque in the spoiler open state is the aircraft dive speed V D .

3. The method for determining the maximum hinge moment of a spoiler of a transport aircraft according to claim 2, characterized in that: In step 2, determining the angle of attack corresponding to the maximum hinge moment according to the flap state and the speed state includes: In the landing configuration, the angle of attack corresponding to the maximum hinge moment in the spoiler closed state is the aircraft flap limit speed V FE , maneuvering angle of attack at 2.0g overload; In the cruise configuration, the angle of attack corresponding to the maximum hinge moment of the spoiler in the open state is the aircraft dive speed V D The trim angle of attack at .

4. The method for determining the maximum hinge moment of a spoiler of a transport aircraft according to claim 3, characterized in that: Aircraft flap limit speed V FE , the maneuvering angle of attack at 2.0g overload is 5°; Aircraft dive speed V D The trim angle of attack is 0°.

5. The method for determining the maximum hinge moment of a spoiler of a transport aircraft according to claim 4, characterized in that: In step 2, determining the spoiler deflection corresponding to the maximum hinge moment according to the flap state and the speed state includes: In the landing configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler closed state is the spoiler low-speed limit deflection; In the cruise configuration, the spoiler deflection corresponding to the maximum hinge torque in the spoiler open state is 2 / 3 of the maximum positive deflection of the spoiler at low speed.

6. The method for determining the maximum hinge moment of a spoiler of a transport aircraft according to claim 5, characterized in that: In step three, a maximum hinge moment calculation model is obtained, the angle of attack and the spoiler deflection are input into the maximum hinge moment calculation model, and the maximum hinge moment is calculated, including: Get the maximum hinge moment calculation model: Among them, M h is the maximum hinge moment, C h is the spoiler hinge moment coefficient, C h is the angle of attack α and the spoiler deflection δ sp function, q is the velocity pressure, is the reference area of ​​the spoiler, is the reference length of the spoiler; Inputting the angle of attack and the deflection of the spoiler corresponding to the maximum hinge moment in the spoiler closed state into the maximum hinge moment calculation model to calculate the maximum hinge moment in the spoiler closed state; The angle of attack and the deflection of the spoiler corresponding to the maximum hinge moment in the spoiler-open state are input into the maximum hinge moment calculation model to calculate the maximum hinge moment in the spoiler-open state.

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