CN216144490U - Aircraft engine model - Google Patents
Aircraft engine model Download PDFInfo
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- CN216144490U CN216144490U CN202121645226.9U CN202121645226U CN216144490U CN 216144490 U CN216144490 U CN 216144490U CN 202121645226 U CN202121645226 U CN 202121645226U CN 216144490 U CN216144490 U CN 216144490U
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Abstract
The patent discloses an aircraft engine model belongs to aircraft aeroelasticity wind-tunnel test model and vibration material disk and makes technical field, and this model includes covering, bearing rib board, middle skeleton, counter weight linking bridge, rib, counter weight cylinder, clear powder hole, clear powder flap, and clear powder hole and clear powder flap just set up when only needing to clear up vibration material disk residual powder. The utility model aims to provide an aircraft engine model capable of accurately simulating the dynamic characteristics of a real aircraft engine, so that the accuracy of subsequent wind tunnel test data is ensured, the processing efficiency of the aircraft engine model is improved, and the processing cost is reduced.
Description
Technical Field
The utility model belongs to the technical field of aeroelasticity wind tunnel test models and additive manufacturing of airplanes, and particularly relates to an airplane engine model for a wing flutter wind tunnel model based on additive manufacturing.
Background
When an airplane moves in airflow, the airplane is subjected to aerodynamic force, inertia force and elastic force, and self-excited vibration, also called flutter, is formed by the interaction of the aerodynamic force, the inertia force and the elastic force. When the aircraft flight speed exceeds the flutter threshold speed, irreversible structural damage will occur. Therefore, in order to determine the critical speed of the whole or local flutter of the airplane, study the influence of relevant structural parameters on the flutter characteristics, check the designed airplane flutter characteristics and theoretical calculation method, a flutter wind tunnel model of the main part of the airplane needs to be processed and manufactured, and wind tunnel tests need to be carried out. The engine model in the airplane flutter wind tunnel model needs to have similar dynamic characteristics with a simulated real airplane engine, and mainly comprises aerodynamic shape and mass distribution data.
At present, wind tunnel models of aircraft engines are rare, although the whole aircraft wind tunnel model is manufactured in an additive manufacturing field, the aircraft engine part is less concerned, and an engine model which is suitable for models, can be repeatedly used, is convenient to reform and update, has high reliability and meets the requirements of wind tunnel tests is not formed. The engine flutter wind tunnel model applied to models at present mainly adopts a metal framework matched with a dimensional skin and filling foam, and the metal framework of the engine model adopts a mode of a rib plate and front and rear supporting frameworks, so that more materials are required to be consumed. The dimensional skin is usually made of glass fiber, and foam materials are filled between the framework and the skin, so that the dimensional skin has small contribution to the rigidity of the model and low structural efficiency. And moreover, the processing is time-consuming and labor-consuming, the metal framework and the dimensional skin of the model need to be positioned in a complex manner in the assembling process, so that the assembling efficiency is low, a large error exists, the accurate simulation of the pneumatic appearance is not facilitated, the accuracy of the follow-up wind tunnel test is influenced, the processing cost is high, and the processing period is long.
Disclosure of Invention
In the prior art, an engine model has the disadvantages of more material consumption, low structural efficiency, low assembly efficiency, larger error, long processing time and high cost, is not favorable for accurate simulation of pneumatic appearance, and influences the accuracy of subsequent wind tunnel tests.
Based on the above problems, the utility model aims to provide the aircraft engine model, which can ensure the accuracy of the pneumatic appearance precision and the mass distribution of the aircraft engine model, accurately simulate the dynamic characteristics of a real aircraft engine, ensure the accuracy of subsequent wind tunnel test data, simultaneously improve the model processing efficiency and reduce the processing cost.
In order to achieve the purpose, the utility model adopts the following technical scheme:
an aircraft engine model comprising: covering (1), bearing floor (2), middle skeleton (3), counter weight linking bridge (4), add rib (7), counter weight cylinder (5), wherein:
the skin is a structure simulating the aerodynamic shape of a real aircraft engine;
the bearing rib plates are of sheet structures penetrating through the front and the back of the skin, are perpendicular to the middle skeleton, divide the interior of the skin into independent spaces and are used for supporting the skin;
the middle framework is of an annular structure, and the annular structure is provided with a groove (9) and a first through hole (10) for bolt fastening assembly connection with the hanging connecting piece;
the counterweight connecting support comprises a second through hole (11) at the center of the middle framework and a rib plate (12) for connecting the middle framework, and the second through hole at the center of the middle framework is used for installing a counterweight cylinder;
the reinforcing ribs are positioned between the middle framework and the front edge of the aircraft engine model and used for preventing connection instability of the skin and the bearing rib plates;
and the counterweight cylinder is bonded at the second through hole at the center of the middle framework.
The engine model further comprises a powder cleaning hole (6) and a powder cleaning hole cover (8).
The powder cleaning holes are positioned at the front edge and the rear edge of each independent part in the skin, the powder cleaning hole covers correspond to the powder cleaning holes one by one, and are used for cleaning powder remained in the skin after additive manufacturing, adhering the powder cleaning holes to block the powder cleaning holes, and ensuring that air flow cannot enter the interior of a model structure in a subsequent wind tunnel test to damage the model;
the main body part of the aircraft engine model is made of a material which can be used for additive manufacturing, and the material of the counterweight cylinder is metal.
The main body part of the aircraft engine model is made of nylon, and the counterweight cylinder is made of No. 45 steel.
The utility model has the beneficial effects that:
the aircraft engine model can be manufactured in series, and along with the innovation of the engine, the engine model does not need to change the structure, only needs to be adjusted in size, and can reduce the design cost;
meanwhile, by adopting an additive manufacturing technology, such as an SLS technology, an SLA technology and other suitable 3D printing technologies, the processing efficiency of the engine model is very high, and the processing period and the processing cost can be reduced;
meanwhile, the engine model can ensure the accuracy of geometric shape precision and mass distribution, and can more accurately and effectively realize the dynamic similar characteristics of the engine in a wind tunnel test.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly introduced below, and it is obvious that the drawings in the following description are only drawings obtained by some specific embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive exercise.
FIG. 1 is a schematic illustration of the structure of an engine model in one embodiment provided by the present invention;
FIG. 2 is a schematic structural view of an engine model intermediate frame and a counterweight attachment bracket according to an embodiment of the present invention;
FIG. 3 illustrates the connection of a real engine model to a wing, obtained in an embodiment of the present invention;
fig. 4 is a structure of a real engine model obtained in one embodiment provided by the present invention.
In fig. 1:
1-covering; 2-load-bearing rib plates; 3-an intermediate skeleton; 4-counterweight connecting bracket; 5-a counterweight cylinder; 6-powder cleaning hole cover; 7-adding ribs; 8-clear powder hole.
In fig. 2:
9-a groove; 10-a first via; 11-a second via; 12-ribbed plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In one embodiment provided by the present invention, there is provided an aircraft engine model comprising: a covering (1), a bearing rib plate (2), a middle framework (3), a counterweight connecting bracket (4), a reinforcing bar (7), a powder cleaning hole (6), a powder cleaning hole cover (8) and a counterweight cylinder (5),
the skin is a structure simulating the aerodynamic shape of a real aircraft engine;
the bearing rib plates are of sheet structures penetrating through the front and the back of the skin, are bilaterally symmetrical and perpendicular to the middle skeleton, and divide the interior of the skin into independent spaces; as shown in fig. 1, in this embodiment, 6 load-bearing ribs are designed for supporting the skin and providing mass and convenient counterweight, and the load-bearing ribs are sheet structures that penetrate through the front and back of the skin along the air intake direction of the engine, divide the interior of the skin into 6 independent spaces, are bilaterally symmetrical and are perpendicular to the middle skeleton.
The middle framework is of a circular structure, and the top of the middle framework is provided with a groove (9) with the diameter of 30mmX35mm and 4 first through holes (10) with the diameter of 6mm, which are shown in figure 2; since the size of the groove cannot exceed the thickness of the middle frame, the size of the first through hole is determined according to the size of the fastening bolt, and the fastening bolt adopting M6 in the embodiment is assembled and connected with the hanging connecting piece, so that 4 first through holes with the diameter of 6mm are provided.
The counterweight connecting bracket comprises 1 second through hole (11) at the center of the middle framework and 3 rib plates (12) for connecting the middle framework; that is, other structures not including the middle skeleton in fig. 2, the second through hole in the center of the middle skeleton is used for installing the counterweight cylinder, the size of the second through hole is preliminarily determined, the final structural form meets the requirement of the engine model dynamic characteristic, the diameter of the preliminarily determined second through hole in this embodiment is 50mm, the aperture size is subsequently adjustable, and the second through hole is connected with the middle skeleton through 3 rib plates.
The reinforcing ribs are arranged between the middle framework and the front edge of the engine and are uniformly distributed between the middle framework and the front edge of the engine to prevent the connection instability of the skin and the bearing rib plates, and 3 reinforcing ribs are arranged in the embodiment.
The powder cleaning holes and the corresponding powder cleaning hole covers are determined according to the number of the load-bearing ribbed plates, in the embodiment, the 6 load-bearing ribbed plates divide the interior of a skin of the engine model into 6 mutually independent spaces, one powder cleaning hole is arranged at the front edge of each independent space, one powder cleaning hole is arranged at the rear edge of each independent space, the number of the powder cleaning holes is 2 times that of the load-bearing ribbed plates, namely 12, the diameter of each powder cleaning hole is 10mm, and the powder cleaning holes are used for cleaning residual powder in the interior of the engine model after additive manufacturing.
The corresponding powder cleaning hole cover is determined according to the size and the number of the powder cleaning holes, and the powder cleaning hole cover is used for being pasted at the powder cleaning holes after residual powder is cleaned up, so that the powder cleaning holes are blocked, and the phenomenon that the model is damaged due to the fact that airflow enters the model structure in a subsequent wind tunnel test is prevented.
And the counterweight cylinder is bonded at the second through hole at the center of the middle framework.
The powder cleaning hole is a reserved design for cleaning residual powder in additive manufacturing, and if no powder is left in additive manufacturing, the powder cleaning hole and a corresponding powder cleaning hole cover are not arranged.
The main part of the aircraft engine model is a material that can be used for additive manufacturing, such as resin, rubber, metal, etc.; the counterweight cylinder is made of materials with high density and low cost, such as 45-grade steel, 65Mn steel and the like. In this embodiment, the main body of the aircraft engine model is made of nylon, and the counterweight cylinder is made of 45 # steel. The specific implementation results are shown in fig. 3 and 4.
One of ordinary skill in the art will understand that all or part of the processes in the methods of the above embodiments may be implemented.
It will be apparent to those skilled in the art that the implementation of the engine model is merely illustrative for the convenience and brevity of description. The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention.
Claims (5)
1. The utility model provides an aircraft engine model, its characterized in that includes covering (1), bearing floor (2), middle skeleton (3), counter weight linking bridge (4), adds rib (7), counter weight cylinder (5), wherein:
the skin is a structure simulating the aerodynamic shape of a real aircraft engine;
the bearing rib plates are of sheet structures penetrating through the front and the back of the skin, are perpendicular to the middle framework, and divide the interior of the skin into independent spaces;
the middle framework is of an annular structure, and a groove (9) and a first through hole (10) are formed in the annular structure;
the counterweight connecting bracket comprises a second through hole (11) at the center of the middle framework and a rib plate (12) used for connecting the middle framework;
the ribbing is located between the intermediate frame and a leading edge of the aircraft engine model;
and the counterweight cylinder is bonded at the through hole at the center of the middle framework.
2. The aircraft engine model as claimed in claim 1, characterized in that the engine model further comprises a powder cleaning hole (6) and a powder cleaning hatch (8).
3. The aircraft engine model of claim 2, wherein the powder cleaning holes are located at the front edge and the rear edge of each independent part in the skin, and the powder cleaning hole covers correspond to the powder cleaning holes one to one.
4. An aircraft engine model according to claim 1, wherein the main body of the aircraft engine model is made of a material that can be used for additive manufacturing, and the counterweight cylinders are made of metal.
5. An aircraft engine model according to claim 1, wherein the main body of the aircraft engine model is of nylon material and the counterweight cylinders are of steel 45.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121645226.9U CN216144490U (en) | 2021-07-20 | 2021-07-20 | Aircraft engine model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121645226.9U CN216144490U (en) | 2021-07-20 | 2021-07-20 | Aircraft engine model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216144490U true CN216144490U (en) | 2022-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121645226.9U Active CN216144490U (en) | 2021-07-20 | 2021-07-20 | Aircraft engine model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216144490U (en) |
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2021
- 2021-07-20 CN CN202121645226.9U patent/CN216144490U/en active Active
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