Aircraft model fuselage component for wind tunnel dynamic test and manufacturing method thereof

Abstract

The invention provides a fuselage component of a wind tunnel dynamic test aircraft model and a manufacturing method thereof, relates to the technical field of wind tunnel aircraft models, and solves the technical problem in the prior art that the fuselage component of a wind tunnel aircraft model adopts a traditional fuselage structure, which affects the accuracy of experimental data due to its heavy weight. The fuselage component of the wind tunnel dynamic test aircraft model comprises a load-bearing frame, an air intake pipe and a skin, wherein the load-bearing frame is arranged as a truss structure; a first mounting portion is arranged on the load-bearing frame, and the air intake pipe is fixedly connected to the first mounting portion; the skin is wrapped around the load-bearing frame and the air intake pipe, and a lip is detachably arranged at the air intake end of the air intake pipe, and the lip is arranged outside the skin; the invention adopts a skin-frame structure as a whole, effectively reduces the overall weight of the fuselage component, thereby significantly reducing the test oscillation inertia, increasing the natural frequency, alleviating the requirement for the structural rigidity of the test device, and greatly improving the accuracy of the experimental data.

Description

Technical Field

[0001] The invention relates to the technical field of wind tunnel aircraft models, and in particular to a wind tunnel dynamic test aircraft model fuselage component and a manufacturing method thereof. Background Art

[0002] For a long time, aerodynamic research institutions at home and abroad have been committed to the research and numerical simulation analysis of dynamic wind tunnel test technology for aircraft, providing a large number of basic tests for the development of various aerospace vehicles. When conducting wind tunnel tests on aircraft, a scaled model with the same aerodynamic shape as the real aircraft must be manufactured and connected to the data acquisition device in the wind tunnel to conduct dynamic derivative tests (i.e. dynamic tests), force measurement, pressure measurement, hinge distance and other related experiments. Among them, the dynamic derivative is a verification of the derivative of the aircraft's aerodynamic coefficient and aerodynamic torque coefficient to the aircraft's rotational angular velocity or attitude angle change rate. It is an indispensable original aerodynamic parameter in the design of the aircraft's control system and dynamic quality analysis. It is an important aspect related to the aircraft's flight quality, automatic driving control system and safe flight.

[0003] During the dynamic test, the dynamic test model, which is a scaled model of the tested aircraft, is of vital importance for its important technical indicators, such as surface accuracy and structural weight reduction. As a vibration test system, the dynamic test model should ensure that the operating frequency is far away from the natural frequency of the balance model system for dynamic derivative measurement. This requires that the natural frequency of the balance model system be high. To achieve this condition, the first is to increase the balance stiffness, and the second is to reduce the model weight. Under the current test technology level, it is impossible to significantly improve the balance stiffness, so reducing the model weight and inertia is the main means to increase the system's natural frequency.

[0004] Nowadays, most of the fuselage components of traditional wind tunnel test aircraft models are relatively large in mass. During dynamic tests, aircraft models using fuselage components with relatively large mass will result in large test oscillation inertia and low natural frequency. At the same time, the requirements for the structural stiffness of the test device are extremely high, which greatly affects the accuracy of the experimental data. How to reduce the weight of wind tunnel aircraft models through structure and materials has always been a goal and technical difficulty pursued by related industries. Summary of the invention

[0005] One of the purposes of the present invention is to provide a wind tunnel dynamic test aircraft model fuselage component to solve the technical problem in the prior art that the wind tunnel aircraft model fuselage component adopts a traditional fuselage structure which is heavy and affects the accuracy of experimental data; the preferred technical scheme among the many technical schemes provided by the present invention can produce many technical effects (the first air intake pipe and the second air intake pipe are symmetrically arranged to simulate the aircraft engine air intake pipe, and the lip is used to simulate the lip of the engine air intake pipe; the air intake pipe is arranged as a nylon 3D printed part with high strength and certain flexibility; the upper skin and the lower skin are glued together and wrapped on the load-bearing frame and the air intake pipe, and the connection is tight and the wrapping is tight; the second mounting portion facilitates the installation of the wing; the third mounting portion facilitates the installation of the nose, etc.), as described below.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] The present invention provides a wind tunnel dynamic test aircraft model fuselage component, comprising a load-bearing frame, an air intake pipe and a skin, wherein: the load-bearing frame is configured as a truss structure; a first mounting portion is provided on the load-bearing frame, and the air intake pipe is fixedly connected to the first mounting portion; the skin is wrapped around the load-bearing frame and the air intake pipe and is fixedly connected to the load-bearing frame and the air intake pipe, and the air intake end of the air intake pipe is detachably provided with a lip, and the lip is arranged outside the skin.

[0008] Preferably, the air intake pipe includes a first air intake pipe and a second air intake pipe, wherein: two first mounting parts are symmetrically arranged on the supporting frame, the first air intake pipe and the second air intake pipe are respectively fixedly connected to the two first mounting parts, the skin wraps the first air intake pipe and the second air intake pipe, and the air intake ends of the first air intake pipe and the second air intake pipe are both removably installed with lips.

[0009] Preferably, the air intake pipe is configured as a nylon 3D printed part.

[0010] Preferably, the air intake pipe is bonded to the first mounting portion by structural adhesive; the skin comprises an upper skin and a lower skin that are fixedly connected, the upper skin and the lower skin are wrapped around the load-bearing frame and the air intake pipe, and are bonded to the load-bearing frame and the air intake pipe by structural adhesive.

[0011] Preferably, the skin is made of carbon fiber material.

[0012] Preferably, second mounting parts are respectively provided on both sides of the load-bearing frame, and two second mounting parts are symmetrically arranged outside the skin, and the second mounting parts are used for mounting the wings.

[0013] Preferably, a third mounting portion is provided at the front end of the load-bearing frame, the third mounting portion is provided outside the skin, and the third mounting portion is used for mounting the nose.

[0014] The invention provides a wind tunnel dynamic test aircraft model fuselage component which has at least the following beneficial effects:

[0015] The wind dynamic test aircraft model fuselage component comprises a load-bearing frame, an air intake pipe and a skin, wherein the load-bearing frame is provided with a first mounting portion, the air intake pipe is fixedly connected to the first mounting portion, the load-bearing frame is used for bearing the model, and the air intake pipe is used for simulating the engine air intake pipe; the load-bearing frame is arranged as a truss structure, the skin is wrapped around the load-bearing frame and the air intake pipe and is fixedly connected to the load-bearing frame and the air intake pipe, the fuselage component as a whole adopts a skin-frame structure, which can effectively reduce the weight of the fuselage component as a whole, thereby significantly reducing the test oscillation inertia, increasing the natural frequency, reducing the rigidity requirement for the test device structure, and greatly improving the accuracy of the experimental data; the air intake end of the air intake pipe is detachably provided with a lip, the lip is arranged outside the skin, and the lip is used for realizing the ventilation and closing of the engine air intake duct; the wind tunnel dynamic test aircraft model fuselage component of the present invention can simulate the engine air intake duct flow data and aerodynamic shape characteristic data of the aircraft in the wind tunnel, has the characteristics of light weight, high precision, reasonable structure and good economy, and has a very broad application prospect in the field of wind tunnel test aircraft model processing and manufacturing.

[0016] Another object of the present invention is to provide a method for manufacturing fuselage components of a wind tunnel dynamic test aircraft model, so as to solve the technical problem that the fuselage components manufactured by the traditional wind tunnel aircraft model fuselage component manufacturing method in the prior art are heavy in weight; the preferred technical scheme among the many technical schemes provided by the present invention can produce many technical effects (the inner and outer surfaces of the upper and lower skins have a surface accuracy of no more than 0.1 mm, and the accuracy of a single component is relatively high; the surface accuracy of the fuselage components is no more than 0.2 mm, ensuring the overall accuracy, thereby improving the accuracy of the experimental data, etc.), as described in detail below.

[0017] To achieve the above object, the present invention provides the following technical solutions:

[0018] The invention provides a method for manufacturing a fuselage component of a wind tunnel dynamic test aircraft model, comprising the following steps:

[0019] (I) processing the load-bearing frame and the lip by a CNC processing machine tool;

[0020] (II) manufacturing the air intake pipe by a nylon 3D printer;

[0021] (III) forming the composite material by using a carbon fiber skin upper mold and a carbon fiber skin lower mold to obtain an upper skin and a lower skin respectively;

[0022] (IV) The load-bearing frame processed in step (I) and the air intake pipe manufactured in step (II) are positioned and installed in the carbon fiber skin lower mold, the lower skin, the load-bearing frame and the air intake pipe are bonded by structural adhesive, and after the three-coordinate measurement installation data is qualified, the carbon fiber skin lower mold and the carbon fiber skin upper mold are positioned and molded by positioning pins;

[0023] (V) After the molds are closed, the upper skin and the lower skin are connected by bonding angles. After being heated and cured, they are demoulded and the lip is installed on the air intake end of the air intake pipe. The fuselage components are completed.

[0024] Preferably, in step (III), the surface accuracy of the outer surface and the inner surface of the upper skin obtained is not greater than 0.1 mm; the surface accuracy of the outer surface and the inner surface of the lower skin obtained is not greater than 0.1 mm.

[0025] Preferably, the surface accuracy of the fuselage component after manufacturing is no more than 0.2 mm.

[0026] The method for manufacturing a fuselage component of a wind tunnel dynamic test aircraft model provided by the present invention has at least the following beneficial effects:

[0027] The load-bearing skeleton is processed by a CNC machining machine, with high processing efficiency and high precision; the air intake pipe is manufactured by a nylon 3D printer, which is convenient and quick, and the manufactured 3D nylon air intake pipe has high strength and certain flexibility; the upper skin and the lower skin are respectively manufactured by a carbon fiber skin upper mold and a carbon fiber skin lower mold, and have high specific strength and specific modulus; the air intake pipe and the load-bearing skeleton are installed, and after the three-coordinate measurement installation data is qualified, the mold is positioned and closed, and the manufacturing precision is high; after closing the mold, the upper skin and the lower skin are connected by a bonding angle, heated and cured, and the lip is installed, and the fuselage components are completed. Compared with the fuselage components of traditional dynamic test aircraft models, the fuselage components manufactured by this method have the characteristics of light weight, high precision, reasonable structure and good economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0029] Figure 1 It is a schematic diagram of the structure of the fuselage components of the present invention;

[0030] Figure 2 is a side view of a fuselage component of the present invention;

[0031] Figure 3 It is a schematic diagram of the installation position of the load-bearing frame of the present invention;

[0032] Figure 4 It is a side view of the installation position of the load-bearing frame of the present invention;

[0033] Figure 5 It is an exploded view of the carbon fiber skin mold and the load-bearing frame of the present invention.

[0034] Reference numerals

[0035] 1-bearing frame; 11-second mounting part; 12-third mounting part; 13-first mounting part; 2-intake pipe; 21-first intake pipe; 22-second intake pipe; 3-skin; 31-upper skin; 32-lower skin; 4-carbon fiber skin mold; 41-carbon fiber skin upper mold; 42-carbon fiber skin lower mold; 5-lip. DETAILED DESCRIPTION

[0036] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0037] Embodiment 1:

[0038] The present invention provides a wind tunnel dynamic test aircraft model fuselage component, such as Figure 1 Schematic diagram of the fuselage structure of the present invention, Figure 2 The structure side view of the present invention and Figure 5As shown in the exploded view of the carbon fiber skin mold and the load-bearing frame of the present invention, the fuselage components of the wind tunnel dynamic test aircraft model include a load-bearing frame 1, an air intake pipe 2 and a skin 3, wherein: the load-bearing frame 1 is configured as a truss structure, the non-load-bearing area of ​​the load-bearing frame 1 adopts a truss structure, and the whole adopts a cavity structure design; a first mounting portion 13 is provided on the load-bearing frame 1, and the air intake pipe 2 is fixedly connected to the first mounting portion 13, and the first mounting portion 13 is configured as an air intake pipe mounting frame, and the air intake pipe 2 is fixedly connected to the air intake pipe mounting frame; the skin 3 is wrapped around the load-bearing frame 1 and the air intake pipe 2 and is fixedly connected to the load-bearing frame 1 and the air intake pipe 2, and the air intake end of the air intake pipe 2 is detachably provided with a lip 5, and the lip 5 is arranged outside the skin 3, preferably, the air intake end of the air intake pipe 2 is provided with a metal embedded part, and a screw passes through the lip 5 and is threadedly connected to the air intake end of the air intake pipe 2.

[0039] When in use, the air intake pipe 2 is fixedly connected to the first mounting portion 13, the skin 3 wraps the air intake pipe 2 and the supporting frame 1, the lip 5 is detachably mounted on the air intake end of the air intake pipe 2, and is arranged outside the skin 3. The present invention adopts a skin-skeleton structure as a whole, which is light in weight, reasonable in structure, high in precision, and has good economy. It has a very broad application prospect in the field of wind tunnel test aircraft model processing and manufacturing.

[0040] As an optional implementation, Figure 1 , Figure 2 and Figure 5 As shown, the air intake pipe 2 includes a first air intake pipe 21 and a second air intake pipe 22, wherein: two first mounting portions 13 are symmetrically arranged on the supporting frame 1, the first mounting portion 13 is arranged as an air intake pipe mounting frame, the first air intake pipe 21 and the second air intake pipe 22 are respectively fixedly connected to the two first mounting portions 13, the skin 3 wraps the first air intake pipe 21 and the second air intake pipe 22, and the air intake ends of the first air intake pipe 21 and the second air intake pipe 22 are both removably installed with lips 5.

[0041] As an optional embodiment, the air intake pipe 2 is configured as a nylon 3D printed part, the first air intake pipe 21 is configured as a nylon 3D printed part left part, and the second air intake pipe 22 is configured as a nylon 3D printed part right part, and the nylon 3D printed part left part and the nylon 3D printed part right part are symmetrical to each other.

[0042] As an optional implementation, Figure 5 As shown, the air intake pipe 2 is bonded to the first mounting portion 13 by structural adhesive; the skin 3 includes an upper skin 31 and a lower skin 32 that are fixedly connected, and the upper skin 31 and the lower skin 32 are wrapped around the supporting frame 1 and the air intake pipe 2, and are bonded to the supporting frame 1 and the air intake pipe 2 by structural adhesive; the bonding method is adopted to ensure a tight connection and a tight wrapping.

[0043] As an optional implementation, the skin 3 is made of carbon fiber material, and the upper skin 31 and the lower skin 32 are both configured as carbon fiber skins, which have high specific strength and specific modulus.

[0044] As an optional implementation, Figure 1 and Figure 5 As shown, second mounting parts 11 are respectively provided on both sides of the load-bearing frame 1, and the two second mounting parts 11 are symmetrically arranged outside the skin 3. The second mounting parts 11 are used for installing the wings, and the second mounting parts 11 are arranged as wing mounting frames. The number of the wing mounting frames is set to two, and the two wing mounting frames are symmetrically arranged.

[0045] As an optional implementation, Figure 1 and Figure 5 As shown, a third mounting portion 12 is provided at the front end of the supporting skeleton 1. The third mounting portion 12 is provided outside the skin 3, and the third mounting portion 12 is used for installing the nose. The third mounting portion 12 is provided as a nose mounting frame, and the nose is fixedly connected to the supporting skeleton 1 via the nose mounting frame.

[0046] Embodiment 2:

[0047] The present invention provides a method for manufacturing a fuselage component of a wind tunnel dynamic test aircraft model, such as Figure 3 Schematic diagram of the installation position of the load-bearing frame of the present invention, Figure 4 The side view of the installation position of the load-bearing frame of the present invention and Figure 5 As shown, the following steps are included:

[0048] (I) Processing the load-bearing frame 1 and the lip 5 by a CNC processing machine tool;

[0049] (II) manufacturing the air intake pipe 2 by a nylon 3D printer;

[0050] (III) forming the composite material by using the carbon fiber skin upper mold 41 and the carbon fiber skin lower mold 42 to obtain the upper skin 31 and the lower skin 32 respectively, and the surface accuracy of the outer surface and the inner surface of the obtained upper skin 31 and the lower skin 32 is not greater than 0.1 mm;

[0051] The bottom of the carbon fiber skin upper mold 41 and the top of the carbon fiber skin lower mold 42 are provided with cavities that cooperate with the load-bearing frame 1, and the carbon fiber skin upper mold 41 and the carbon fiber skin lower mold 42 are both configured as bonding angle molds;

[0052] (IV) The load-bearing frame 1 processed in step (I) and the air intake pipe 2 manufactured in step (II) are positioned and installed in the carbon fiber skin lower mold 42. The lower skin 32, the load-bearing frame 1 and the air intake pipe 2 are bonded by structural adhesive. After the three-coordinate measurement installation data is qualified, the carbon fiber skin lower mold 42 and the carbon fiber skin upper mold 41 are positioned and molded by positioning pins;

[0053] (V) After the molds are closed, the upper skin 31 and the lower skin 32 are connected by bonding angles. After being heated and cured, they are demoulded and the lip 5 is installed on the air intake end of the air intake pipe 2. The fuselage components are completed. The overall surface accuracy of the fuselage components after production is no more than 0.2 mm.

[0054] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. Wind tunnel dynamic test of aircraft model fuselage parts, characterized in that: It comprises a load-bearing frame (1), an air intake pipe (2) and a skin (3), wherein: The load-bearing frame (1) is configured as a truss structure; a first mounting portion (13) is provided on the load-bearing frame (1), and the air intake pipe (2) is fixedly connected to the first mounting portion (13); the skin (3) is wrapped around the load-bearing frame (1) and the air intake pipe (2) and is fixedly connected to the load-bearing frame (1) and the air intake pipe (2); the air intake end of the air intake pipe (2) is detachably provided with a lip (5), and the lip (5) is provided outside the skin (3); The air intake pipe (2) comprises a first air intake pipe (21) and a second air intake pipe (22), wherein: Two first mounting parts (13) are symmetrically arranged on the supporting frame (1); the first air intake pipe (21) and the second air intake pipe (22) are respectively fixedly connected to the two first mounting parts (13); the skin (3) wraps the first air intake pipe (21) and the second air intake pipe (22); and the air intake ends of the first air intake pipe (21) and the second air intake pipe (22) are both detachably provided with lips (5); The air intake pipe (2) is configured as a nylon 3D printed part, the first air intake pipe (21) is configured as a left nylon 3D printed part, and the second air intake pipe (22) is configured as a right nylon 3D printed part, and the left nylon 3D printed part and the right nylon 3D printed part are symmetrical to each other; The air intake pipe (2) is bonded to the first mounting portion (13) by means of structural adhesive; the skin (3) comprises an upper skin (31) and a lower skin (32) which are fixedly connected, the upper skin (31) and the lower skin (32) are wrapped around the load-bearing frame (1) and the air intake pipe (2), and are bonded to the load-bearing frame (1) and the air intake pipe (2) by means of structural adhesive; The first mounting portion (13) is configured as an air intake pipe mounting frame; Second mounting portions (11) are respectively arranged on both sides of the load-bearing frame (1), and two second mounting portions (11) are symmetrically arranged outside the skin (3), and the second mounting portions (11) are used for mounting the wing; A third mounting portion (12) is provided at the front end of the load-bearing frame (1), the third mounting portion (12) being arranged outside the skin (3), and the third mounting portion (12) being used for mounting the nose of the machine.

2. The wind tunnel dynamic test aircraft model fuselage component according to claim 1, characterized in that: The skin (3) is made of carbon fiber material.

3. A method for manufacturing a fuselage component of a wind tunnel dynamic test aircraft model according to any one of claims 1 to 2, characterized in that: The following steps are involved: (I) machining the load-bearing frame (1) and the lip (5) by means of a CNC machining machine; (II) manufacturing the air intake pipe (2) by a nylon 3D printer; (III) forming the composite material by using a carbon fiber skin upper mold (41) and a carbon fiber skin lower mold (42) to obtain an upper skin (31) and a lower skin (32), respectively; (IV) the load-bearing frame (1) processed in step (I) and the air intake pipe (2) manufactured in step (II) are positioned and installed in the carbon fiber skin lower mold (42); the lower skin (32), the load-bearing frame (1) and the air intake pipe (2) are bonded by means of structural adhesive; after the three-coordinate measurement installation data is qualified, the carbon fiber skin lower mold (42) and the carbon fiber skin upper mold (41) are positioned and molded by means of positioning pins; (V) After the molds are closed, the upper skin (31) and the lower skin (32) are connected by bonding corners. After being heated and cured, they are demoulded and the lip (5) is installed on the air intake end of the air intake pipe (2). The fuselage component is manufactured.

4. The method for manufacturing a wind tunnel dynamic test aircraft model fuselage component according to claim 3, characterized in that: In step (III), the surface accuracy of the outer surface and the inner surface of the upper skin (31) obtained is not greater than 0.1 mm; the surface accuracy of the outer surface and the inner surface of the lower skin (32) obtained is not greater than 0.1 mm.

5. The method for manufacturing a wind tunnel dynamic test aircraft model fuselage component according to claim 3, characterized in that: The surface accuracy of the fuselage components after production is no more than 0.2 mm.

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