Centroid adjustable anti-hunt airfoil and method of manufacture

Abstract

The application provides a center-of-mass-adjustable anti-chattering air rudder and a manufacturing method. A counterweight of a first mass is riveted and fixed at a position before a pneumatic pressure center of a skeleton of the air rudder; strength analysis and chattering analysis are performed on a rudder surface of the air rudder to obtain a strength margin and a chattering margin of the current rudder surface; if the margin is sufficient, the mass of the counterweight is reduced to a second mass to reduce the weight of the rudder surface, and then the strength analysis and the chattering analysis are performed again until the strength margin and the chattering margin can meet the design requirements; if the margin is insufficient, the mass of the counterweight is increased to a third mass to increase the weight of the rudder surface, and then the strength analysis and the chattering analysis are performed again until the strength margin and the chattering margin can meet the design requirements. The application adjusts the center-of-mass position of the rudder surface to improve the aeroelasticity and avoid the occurrence of the chattering problem under the premise that the air rudder has sufficient thermal strength.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of air rudder, in particular, to the center of mass adjustable anti-chatter air rudder and its manufacturing method. Especially, it relates to the structural design of the center of mass adjustable anti-chatter light air rudder. BACKGROUND

[0002] The air rudder is an important part of the aircraft, the air rudder is located on the outer surface of the aircraft, and the electric rudder control air rudder deflection, thereby changing the air flow, and then controlling the flight attitude of the aircraft, which is crucial to the stability and accuracy of the controllable flight.

[0003] High-speed flight is the future development trend of the aircraft, which brings the problems of large aerodynamic load and serious aerodynamic heating. Facing the increasingly severe flight environment, the air rudder is required to have sufficient thermal strength and anti-chatter ability. The air rudder is generally composed of a rudder surface and a rudder fork, and the rudder surface is divided into a skin structure and a skeleton structure. The aerodynamic elastic performance of the air rudder is closely related to the center of mass of the rudder surface. The closer the center of mass of the rudder surface is to the front, the better the aerodynamic elastic performance is, and the less likely the chattering is. At present, the air rudder of the high-speed aircraft has problems such as large mass and uncontrollable center of mass. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a center of mass adjustable anti-chatter air rudder and a manufacturing method.

[0005] According to the manufacturing method of the center of mass adjustable anti-chatter air rudder provided by the present application, the following steps are included:

[0006] The counterweight adjustment step: rivet a counterweight with a first mass to a position before the aerodynamic pressure center of the skeleton of the air rudder; perform strength analysis and chatter analysis on the rudder surface of the air rudder to obtain the strength margin and the chatter margin of the current rudder surface; if the margin is sufficient, reduce the mass of the counterweight to a second mass to reduce the weight of the rudder surface, and then perform strength analysis and chatter analysis until the strength margin and the chatter margin can meet the design requirements; if the margin is insufficient, increase the mass of the counterweight to a third mass to increase the weight of the rudder surface, and then perform strength analysis and chatter analysis until the strength margin and the chatter margin can meet the design requirements.

[0007] Preferably, it further includes:

[0008] The skeleton manufacturing step: topologically optimize the skeleton 3 and perform CAE strength analysis review, and obtain the skeleton 3 under the premise of meeting the strength requirements.

[0009] Preferably, it further includes:

[0010] The skin installation step: install and fix the skin 4 to the skeleton 3 by means of friction stir welding connection.

[0011] Preferably, the framework 3 and the skin 4 are made of high-temperature-resistant light alloy material.

[0012] Preferably, the weight block 5 is made of high-density, high-temperature-resistant metal or metal alloy material.

[0013] Preferably, the weight block 5 is installed in the structure with mounting clamping slots of the leading edge part of the framework 3, and the weight block 5 is fastened and connected with the framework 3 through rivets.

[0014] According to the application, a centroid-adjustable anti-chattering air vane is provided, in which a weight block is riveted and fixed at a position before the aerodynamic pressure center of the framework of the air vane, and the strength margin and the chattering margin of the vane surface of the air vane meet the design requirements.

[0015] Preferably, the air vane comprises a vane fork 1 and a vane surface 2, the vane fork 1 is fastened and connected with the vane surface 2 through rivets; the vane surface 2 comprises a framework 3, a skin 4 and a weight block 5.

[0016] Preferably, the vane fork 1 is made of high-temperature-resistant and high-strength alloy material, and the outer surface is provided with a high-temperature-resistant and anti-oxidation coating.

[0017] Preferably, the centroid-adjustable anti-chattering air vane is manufactured by the manufacturing method.

[0018] Compared with the prior art, the application has the following beneficial effects:

[0019] The application is a new air vane structure form, which can improve the aeroelasticity by reasonably adjusting the centroid position of the vane surface under the premise of ensuring that the air vane has sufficient thermal strength, and can avoid the occurrence of chattering problems. BRIEF DESCRIPTION OF DRAWINGS

[0020] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0021] Figure 1 The figure shows the outer shape of the air vane of the application.

[0022] Figure 2 The figure shows the schematic structure of the vane surface of the application.

[0023] The figure shows:

[0024] DETAILED DESCRIPTION

[0025] The application will be described in detail below with specific examples. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These are within the scope of protection of the application.

[0026] The application discloses a structure of a light-weight air vane with adjustable mass center and anti-chatter, which adjusts the mass center position of the vane by changing the mass of the counterweight, thereby improving the aeroelastic performance of the air vane.

[0027] The difficulty of the improvement of the application lies in the confirmation of the weight of the counterweight. For different air vanes, the aerodynamic pressure center is different. In principle, the overall mass center position of the air vane should be ensured to be in front of the aerodynamic pressure center, so as to effectively prevent the generation of chattering, and at the same time, the light-weight requirement should be met, so there is an optimal counterweight mass. The mass block in the application is fixed on the framework in the form of riveting, so the relative position of the mass block on the framework cannot be changed. Therefore, a large amount of simulation analysis and multiple iteration optimization are required to determine the final mass of the counterweight. The specific implementation process is as follows: first, the mass of the counterweight is initially determined, so that the mass center position of the vane is in front of the aerodynamic pressure center, the strength and chattering of the vane are analyzed, the strength margin and chattering margin of the vane in this state are obtained, if the margin is sufficient, the mass of the counterweight is adjusted to reduce the weight of the vane, and then the strength and chattering analysis is performed again, until the strength margin and chattering margin can meet the design requirements.

[0028] As shown in Figure 1 , the air vane provided by the application comprises a vane fork 1 and a vane surface 2, and the vane fork 1 is tightly connected with the vane surface 2 through rivets. As shown in Figure 2 , the vane surface 2 comprises a framework 3, a skin 4 and a counterweight 5. The framework 3 and the skin 4 are made of high-temperature-resistant light alloy materials, the vane fork 1 is made of high-temperature-resistant and high-strength alloy materials, and the outer surfaces are provided with high-temperature-resistant and anti-oxidation coating layers; the counterweight 5 is made of high-density and high-temperature-resistant metal or metal alloy materials.

[0029] The application installs the counterweight on the front end of the air vane, adjusts the mass center position of the air vane by changing the mass of the counterweight, and solves the chattering problem of the aircraft in a severe flight environment. That is, by changing the weight of the counterweight, the mass center position of the air vane is adjusted, the aeroelastic performance of the air vane is improved, and the chattering margin can meet the safety margin requirement.

[0030] The adjustment of the mass center position in the application is realized through the following method:

[0031] As shown in Figure 2 , the air vane provided by the application comprises a vane fork 1 and a vane surface 2, and the vane fork 1 is tightly connected with the vane surface 2 through rivets.As shown, the framework 3 is subjected to structural topology optimization design and CAE strength analysis review, under the premise of meeting the strength requirement, the structural mass is reduced to the maximum extent, the structure of the front edge part of the framework 3 has a clamping groove for mounting the counterweight block 5, the counterweight block 5 is fastened and connected with the framework 3 through rivets, and the skin 4 and the framework 3 are connected through friction stir welding; wherein, CAE refers to Computer Aided Engineering. The weight of the counterweight block 5 is changed, so as to adjust the center of mass position of the rudder surface. The rudder surface is subjected to aeroelastic simulation analysis, an optimal mass ratio scheme of the counterweight block is determined, the center of mass of the rudder surface is deviated forward relative to the rudder shaft, and it is ensured that the flutter allowance can meet the requirement; after the air rudder is designed, the thermal strength calculation review and the aeroelastic simulation analysis are performed, and the correctness of the scheme is verified.

[0032] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0033] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method of manufacturing a center-of-gravity-adjustable anti-hunting airfoil, characterized by, The air vane comprises a vane fork (1) and a vane surface (2), the vane fork (1) is fastened with the vane surface (2) by rivets; the vane surface (2) comprises a framework (3), a skin (4) and a counterweight (5); The counterweight adjusting step comprises: riveting and fixing the counterweight of the first mass at the position before the pneumatic pressure center of the framework of the air vane; performing strength analysis and flutter analysis on the vane surface of the air vane to obtain the strength margin and the flutter margin of the current vane surface; if the margin is sufficient, the mass of the counterweight is reduced to the second mass to reduce the weight of the vane surface, and then the strength analysis and the flutter analysis are performed until the strength margin and the flutter margin can meet the design requirements; if the margin is insufficient, the mass of the counterweight is increased to the third mass to increase the weight of the vane surface, and then the strength analysis and the flutter analysis are performed until the strength margin and the flutter margin can meet the design requirements.

2. The method of claim 1, wherein, Further comprising: The framework manufacturing step: the framework (3) is subjected to structure topology optimization and CAE strength analysis review, and the framework (3) is manufactured under the premise of meeting the strength requirement.

3. The method of claim 1, wherein, Further comprising: The skin installation step: the skin (4) is installed and fixed to the framework (3) by the way of friction stir welding connection.

4. The method of claim 3, wherein, The framework (3) and the skin (4) adopt high-temperature-resistant lightweight alloy materials.

5. The method of claim 1, wherein, The counterweight (5) adopts high-density, high-temperature-resistant metal or metal alloy materials.

6. The method of claim 1, wherein, The counterweight (5) is installed in the structure with a mounting clamping groove at the leading edge part of the framework (3), and the counterweight (5) is fastened with the framework (3) by rivets.

7. The method of claim 1, wherein, The vane fork (1) adopts high-temperature-resistant and high-strength alloy materials, and the outer surface is provided with a high-temperature-resistant and anti-thermal oxidation coating.

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