CN210603822U - Wind tunnel dynamic test plane model body component - Google Patents
Wind tunnel dynamic test plane model body component Download PDFInfo
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- CN210603822U CN210603822U CN201921702045.8U CN201921702045U CN210603822U CN 210603822 U CN210603822 U CN 210603822U CN 201921702045 U CN201921702045 U CN 201921702045U CN 210603822 U CN210603822 U CN 210603822U
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Abstract
The utility model provides a wind tunnel dynamic test aircraft model fuselage part, which relates to the technical field of wind tunnel aircraft models and solves the technical problem that the wind tunnel aircraft model fuselage part in the prior art adopts the traditional fuselage structure to influence the accuracy of experimental data due to heavier weight; the bearing framework is provided with a first mounting part, and the air inlet pipe is fixedly connected to the first mounting part; the skin is wrapped on the bearing framework and the air inlet pipe, a lip is detachably arranged at the air inlet end of the air inlet pipe, and the lip is arranged outside the skin; the utility model discloses wholly adopt covering skeleton type structure, effectively reduce the holistic weight of fuselage part to obviously reduce experimental oscillation inertia, improve natural frequency, alleviate and require testing device structural rigidity, improve the accuracy of experimental data by a wide margin.
Description
Technical Field
The utility model relates to a wind-tunnel aircraft model technical field, concretely relates to wind-tunnel dynamic test aircraft model fuselage part.
Background
For a long time, domestic and foreign aerodynamic research institutions are dedicated to dynamic wind tunnel test technical research and numerical simulation analysis work of aircrafts, and provide a large number of basic tests for development of various aerospace aircrafts. When an airplane is subjected to a wind tunnel test, a scaling model with the same aerodynamic shape as a real airplane needs to be manufactured, the scaling model is connected to a data acquisition device in a wind tunnel, and relevant experiments such as dynamic derivative tests (namely dynamic tests), force measurement, pressure measurement, hinge distance and the like are performed, wherein the dynamic derivative is a verification of the aerodynamic coefficient and aerodynamic moment coefficient of the airplane on the derivative of the rotation angular velocity or attitude angle change rate of the airplane, is an indispensable original aerodynamic parameter in the design and dynamic quality analysis of an airplane development control system, and is an important aspect related to the flight quality, an automatic driving control system and safe flight of the airplane.
In the process of dynamic test, the dynamic test model is a scaled model of the tested airplane, and important technical indexes of the dynamic test model are important in surface precision and structure weight reduction; the dynamic test model is used as a vibration test system, the dynamic derivative measurement needs to ensure that the working frequency is far away from the natural frequency of the balance model system, so that the natural frequency of the balance model system is required to be high, and the balance stiffness is improved and the model weight is reduced to meet the condition.
At present, in a traditional wind tunnel test airplane model, a large number of airplane body components have large mass, and an airplane model adopting the airplane body components with large mass can cause large test oscillation inertia and low natural frequency in a dynamic test process, and meanwhile, the requirement on the structural rigidity of a test device is extremely high, so that the accuracy of experimental data is greatly influenced, and how to reduce the weight of the wind tunnel airplane model through the structure is always a target and a technical difficulty pursued by related industries.
SUMMERY OF THE UTILITY MODEL
One of the purposes of the utility model is to provide a wind tunnel dynamic test airplane model body component to solve the technical problem that the accuracy of experimental data is affected by the adoption of a traditional body structure of the wind tunnel airplane model body component in the prior art; the utility model provides a plurality of technical effects that can be produced by the optimized technical scheme in a plurality of technical schemes (the first air inlet pipe and the second air inlet pipe are symmetrically arranged and used for simulating the air inlet pipe of an aircraft engine, the lip is used for simulating the lip of the air inlet pipe of the engine, the air inlet pipe is connected and fastened with the bearing framework through structural adhesive, the air inlet pipe is arranged to be a nylon 3d printing piece with high strength and certain flexibility, the upper skin and the lower skin are connected and wrapped on the bearing framework and the air inlet pipe in an adhesive way, the connection and the tight wrapping are realized, the precision of the inner and outer surfaces of the upper skin and the lower skin is not more than 0.1mm, the integral precision of the fuselage part is ensured, the accuracy of experimental data is further improved, the skin is made of carbon fiber material and has higher specific strength and specific modulus, the second installation part is convenient for installing wings, the third installation part is convenient for, see below for details.
In order to achieve the above purpose, the utility model provides a following technical scheme:
the utility model provides a pair of wind-tunnel dynamic test aircraft model fuselage part, including bearing skeleton, intake pipe and covering, wherein: the bearing framework is of a truss structure; the bearing framework is provided with a first mounting part, and the air inlet pipe is fixedly connected to the first mounting part; the covering wraps up bear the skeleton with on the intake pipe and with bear the skeleton with intake pipe fixed connection, the inlet end of intake pipe can be dismantled and be provided with the lip, the lip sets up outside the covering.
Preferably, the intake pipe includes a first intake pipe and a second intake pipe, wherein: bear the weight of the symmetry on the skeleton and be provided with two first installation department, first intake pipe with second intake pipe fixed connection respectively is two on the first installation department, the covering parcel is lived first intake pipe with the second intake pipe, the inlet end of first intake pipe with the equal demountable installation of inlet end of second intake pipe has the lip.
Preferably, the air inlet pipe is glued on the first mounting portion through structural glue.
Preferably, the air inlet tube is provided as a nylon 3d print.
Preferably, the covering includes fixed connection's last covering and covering down, go up the covering with the covering is spliced down and is linked to each other, go up the covering with the covering parcel is in down bear the skeleton with on the intake pipe, and with bear the skeleton with the intake pipe is glued through the structure and is spliced.
Preferably, the surface precision of the outer surface and the inner surface of each of the upper skin and the lower skin is not more than 0.1 mm.
Preferably, the skin is made of a carbon fiber material.
Preferably, the air inlet end of the air inlet pipe is provided with a metal embedded part, and the lip is detachably connected to the air inlet end of the air inlet pipe through a threaded fastener and the metal embedded part.
Preferably, bear the weight of the skeleton both sides and be provided with the second installation department respectively, two the second installation department symmetry sets up outside the skin, the second installation department is used for the installation of wing.
Preferably, the front end of bearing the weight of the skeleton is provided with the third installation department, the third installation department sets up outside the skin, the third installation department is used for the installation of aircraft nose.
The utility model provides a pair of wind-tunnel dynamic test aircraft model fuselage part has following beneficial effect at least:
the wind-driven test aircraft model body part comprises a bearing framework, an air inlet pipe and a skin, wherein a first mounting part is arranged on the bearing framework, the air inlet pipe is fixedly connected to the first mounting part, the bearing framework is used for bearing a model, and the air inlet pipe is used for simulating an engine air inlet pipe; the bearing framework is of a truss structure, the skin is wrapped on the bearing framework and the air inlet pipe and is fixedly connected with the bearing framework and the air inlet pipe, and the whole body of the body component is of a skin framework type structure, so that the whole weight of the body component can be effectively reduced, the test oscillation inertia is obviously reduced, the inherent frequency is improved, the rigidity requirement on the structure of the test device is reduced, and the accuracy of the experimental data is greatly improved; the inlet end of the air inlet pipe is detachably provided with a lip, the lip is arranged outside the skin and simulates the lip of the engine air inlet pipe so as to realize the ventilation and the closing of the engine air inlet pipe; the utility model discloses can simulate aircraft's engine intake duct flow data and pneumatic appearance characteristic data in the wind-tunnel, have light in weight, the precision is higher, rational in infrastructure, the better characteristics of economic nature have very wide application prospect in wind-tunnel test aircraft model manufacturing field.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of the fuselage assembly of the present invention;
fig. 2 is a side view of the fuselage section of the present invention;
FIG. 3 is a schematic view of the installation position of the load-bearing frame of the present invention;
FIG. 4 is a side view of the installation position of the load-bearing frame of the present invention;
fig. 5 is an exploded view of the carbon fiber skin mold and the bearing frame of the present invention.
Reference numerals
1-a load-bearing skeleton; 11-a second mounting portion; 12-a third mounting portion; 13-a first mounting portion; 2, an air inlet pipe; 21-a first inlet pipe; 22-a second inlet pipe; 3-covering the skin; 31-upper skin; 32-a lower skin; 4-carbon fiber skin mould; 41-carbon fiber skin upper die; 42-carbon fiber skin lower die; 5-lip.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. It is to be understood that the embodiments described are only some embodiments of the invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
The utility model provides a wind-tunnel dynamic test aircraft model fuselage part, like figure 1 the utility model discloses fuselage part structure schematic diagram, figure 2 the utility model discloses structure side view and figure 5 the utility model discloses carbon fiber covering mould and bearing frame exploded view are shown, wind-tunnel dynamic test aircraft model fuselage part is including bearing frame 1, intake pipe 2 and covering 3, wherein: the bearing framework 1 is of a truss structure, the non-bearing area of the bearing framework 1 adopts the truss structure, and the whole bearing framework adopts a cavity structure design; a first mounting part 13 is arranged on the bearing framework 1, the air inlet pipe 2 is fixedly connected to the first mounting part 13, the first mounting part 13 is arranged as an air inlet pipe mounting frame, and the air inlet pipe 2 is fixedly connected to the air inlet pipe mounting frame; covering 3 parcel is on bearing skeleton 1 and intake pipe 2 and with bearing skeleton 1 and intake pipe 2 fixed connection, and intake pipe 2's inlet end can be dismantled and be provided with lip 5, and lip 5 sets up outside covering 3.
During the use, intake pipe 2 fixed connection is on first installation department 13, and intake pipe 2 and bearing frame 1 are lived in the parcel of covering 3, and lip 5 demountable installation is on the inlet end of intake pipe 2 to the setting is outside covering 3, the utility model discloses wholly adopt covering skeleton type structure, the quality is light, and is rational in infrastructure, and the precision is high, has good economic nature, has very wide application prospect in wind-tunnel test aircraft model manufacturing field.
As an alternative embodiment, as shown in fig. 1, 2 and 5, the intake pipe 2 includes a first intake pipe 21 and a second intake pipe 22, in which: bear skeleton 1 and go up the symmetry and be provided with two first installation departments 13, first installation department 13 sets up to the intake pipe installation frame, and first intake pipe 21 and second intake pipe 22 are fixed connection respectively two on the intake pipe installation frame, first intake pipe 21 and second intake pipe 22 are lived to skin 3 parcel, and the lip 5 is installed to the equal demountable installation of inlet end of first intake pipe 21 and the inlet end of second intake pipe 22.
As an optional implementation manner, the air inlet pipe 2 is glued on the first mounting portion 13 by structural glue, and the first air inlet pipe 21 and the second air inlet pipe 22 are glued on the corresponding first mounting portion 13 by structural glue.
As an alternative embodiment, the air inlet pipe 2 is configured as a nylon 3d printing piece, the first air inlet pipe 21 is configured as a left nylon 3d printing piece, the second air inlet pipe 22 is configured as a right nylon 3d printing piece, and the left nylon 3d printing piece and the right nylon 3d printing piece are symmetrical to each other.
As an alternative embodiment, as shown in fig. 5, the air inlet pipe 2 is glued on the first mounting portion 13 by structural glue; 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 connected in a bonding mode, the upper skin 31 and the lower skin 32 are wrapped on the bearing framework 1 and the air inlet pipe 2, and the upper skin 31 and the lower skin are bonded with the bearing framework 1 and the air inlet pipe 2 through structural adhesives; the mode of cementing is adopted, the connection is tight, and the package is tight.
In an optional embodiment, the shape precision of the outer shape surface and the inner shape surface of each of the upper skin 31 and the lower skin 32 is not greater than 0.1mm, and the overall shape precision of the fuselage part of the wind tunnel dynamic test aircraft model is not greater than 0.2mm, so that the accuracy of the experimental data is further improved.
As an alternative embodiment, the skin 3 is made of a carbon fiber material, and the upper skin 31 and the lower skin 32 are both made of carbon fiber skin, and the specific strength and specific modulus of the carbon fiber skin are high.
As an alternative embodiment, as shown in fig. 1 and 2, a metal embedded part is arranged at the air inlet end of the air inlet pipe 2, and the lip 5 is detachably connected to the air inlet end of the air inlet pipe 2 through a threaded fastener and the metal embedded part; the metal embedded part is arranged on the pipe wall of the air inlet end of the air inlet pipe 2, the lip 5 is provided with a mounting hole, and a screw penetrates through the mounting hole to fix the lip 5 on the air inlet end of the air inlet pipe 2.
As an alternative embodiment, as shown in fig. 1 and fig. 5, second installation portions 11 are respectively disposed on two sides of the load-bearing framework 1, the two second installation portions 11 are symmetrically disposed outside the skin 3, the second installation portions 11 are used for installing wings, the second installation portions 11 are wing installation frames, the number of the wing installation frames is two, and the two wing installation frames are symmetrically disposed.
As an alternative embodiment, as shown in fig. 1 and 5, the front end of the load-bearing framework 1 is provided with a third mounting part 12, the third mounting part 12 is arranged outside the skin 3, and the third mounting part 12 is used for mounting a nose; the third installation part 12 is configured as a machine head installation frame, and the machine head is fixedly connected with the bearing framework 1 through the machine head installation frame.
As shown in fig. 3 the utility model discloses bear skeleton mounted position schematic diagram, fig. 4 the utility model discloses bear skeleton mounted position side view and fig. 5 shown, the forming process of wind-tunnel dynamic test aircraft model fuselage part is as follows:
(I) processing the bearing framework 1 and the lip 5 by a CNC (computer numerical control) processing machine tool;
(II) manufacturing an air inlet pipe 2 by a nylon 3d printer;
(III) molding a composite material through a carbon fiber skin upper mold 41 and a carbon fiber skin lower mold 42 to respectively obtain an upper skin 31 and a lower skin 32, wherein the surface accuracy of the outer surface and the inner surface of the upper skin 31 and the lower skin 32 is not more than 0.1 mm;
cavities matched with the bearing framework 1 are formed in the bottom of the carbon fiber skin upper die 41 and the top of the carbon fiber skin lower die 42, and the carbon fiber skin upper die 41 and the carbon fiber skin lower die 42 are both arranged to be bonding angle dies;
(IV) positioning and installing the bearing framework 1 processed in the step (I) and the air inlet pipe 2 manufactured in the step (II) in a carbon fiber skin lower die 42, gluing the lower skin 32, the bearing framework 1 and the air inlet pipe 2 through structural glue, and positioning and die assembling the carbon fiber skin lower die 42 and the carbon fiber skin upper die 41 through positioning pins after the three-coordinate measuring and installing data are qualified;
(V) after die assembly, connecting the upper skin 31 with the lower skin 32 through a bonding angle, demolding after temperature rise and solidification, and installing the lip 5 on the air inlet end of the air inlet pipe 2, wherein the fuselage component is manufactured, and the overall shape precision of the fuselage component after the manufacturing is not more than 0.2 mm.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. Wind-tunnel dynamic test aircraft model fuselage part, its characterized in that, including bearing skeleton (1), intake pipe (2) and covering (3), wherein:
the bearing framework (1) is arranged into a truss structure; a first mounting part (13) is arranged on the bearing framework (1), and the air inlet pipe (2) is fixedly connected to the first mounting part (13); covering (3) parcel is in bear skeleton (1) with intake pipe (2) go up and with bear skeleton (1) with intake pipe (2) fixed connection, the inlet end of intake pipe (2) can be dismantled and be provided with lip (5), lip (5) set up outside covering (3).
2. The wind tunnel dynamic test aircraft model fuselage component according to claim 1, characterized in that the air inlet duct (2) comprises a first air inlet duct (21) and a second air inlet duct (22), wherein:
bear the weight of on skeleton (1) the symmetry be provided with two first installation department (13), first intake pipe (21) with second intake pipe (22) fixed connection respectively is two on first installation department (13), covering (3) parcel is lived first intake pipe (21) with second intake pipe (22), the inlet end of first intake pipe (21) with the equal demountable installation of inlet end of second intake pipe (22) has lip (5).
3. The wind tunnel dynamic test aircraft model fuselage component of claim 1, characterized in that the air inlet pipe (2) is glued to the first mounting section (13) by means of structural glue.
4. The wind tunnel dynamic test aircraft model fuselage component according to claim 1, characterized in that the air inlet tube (2) is provided as a nylon 3d print.
5. The wind tunnel dynamic test aircraft model fuselage component of claim 1, characterized in that, the skin (3) includes fixed connection's upper skin (31) and lower skin (32), upper skin (31) with lower skin (32) are glued to link to each other, upper skin (31) with lower skin (32) parcel is in bear skeleton (1) with intake pipe (2) on, and with bear skeleton (1) with intake pipe (2) through the structure glue to bond.
6. The wind tunnel dynamic test aircraft model fuselage component according to claim 5, characterized in that the outer and inner faces of the upper skin (31) and the lower skin (32) each have a face precision of no more than 0.1 mm.
7. The fuselage component of the wind tunnel dynamic test aircraft model according to claim 1, characterized in that the skin (3) is made of carbon fiber.
8. The wind tunnel dynamic test aircraft model body component of claim 1, characterized in that the air inlet end of the air inlet pipe (2) is provided with a metal embedded part, and the lip (5) is detachably connected to the air inlet end of the air inlet pipe (2) through a threaded fastener and the metal embedded part.
9. The wind tunnel dynamic test aircraft model fuselage component of claim 1, characterized in that two sides of the bearing framework (1) are respectively provided with a second mounting portion (11), two second mounting portions (11) are symmetrically arranged outside the skin (3), and the second mounting portions (11) are used for mounting wings.
10. The wind tunnel dynamic test aircraft model fuselage component of claim 1, characterized in that the front end of the bearing skeleton (1) is provided with a third mounting portion (12), the third mounting portion (12) being arranged outside the skin (3), the third mounting portion (12) being used for the mounting of a nose.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921702045.8U CN210603822U (en) | 2019-10-11 | 2019-10-11 | Wind tunnel dynamic test plane model body component |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921702045.8U CN210603822U (en) | 2019-10-11 | 2019-10-11 | Wind tunnel dynamic test plane model body component |
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| CN210603822U true CN210603822U (en) | 2020-05-22 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595730A (en) * | 2019-10-11 | 2019-12-20 | 哈尔滨市航科技术开发有限责任公司 | Wind tunnel dynamic test airplane model body component and manufacturing method thereof |
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2019
- 2019-10-11 CN CN201921702045.8U patent/CN210603822U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595730A (en) * | 2019-10-11 | 2019-12-20 | 哈尔滨市航科技术开发有限责任公司 | Wind tunnel dynamic test airplane model body component and manufacturing method thereof |
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