CN113879559B - Aircraft skin static force loading device and skin dynamic strength test method - Google Patents
Aircraft skin static force loading device and skin dynamic strength test method Download PDFInfo
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- CN113879559B CN113879559B CN202111189111.8A CN202111189111A CN113879559B CN 113879559 B CN113879559 B CN 113879559B CN 202111189111 A CN202111189111 A CN 202111189111A CN 113879559 B CN113879559 B CN 113879559B
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- aircraft skin
- static force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The application provides an aircraft skin static force loading device and a skin dynamic strength test method, wherein the aircraft skin static force loading device comprises: the device comprises an outer frame, a force transducer, an elastic component and a static force application component; the outer frame is provided with a containing cavity, the aircraft skin is arranged in the containing cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end of the aircraft skin opposite to the one end of the aircraft skin is connected with the force transducer, and the force transducer is used for measuring the static force applied to the aircraft skin; the elastic component is respectively connected with the force transducer and the static force applying component, and the static force applying component applies static force to the aircraft skin through the elastic component and the force transducer. By applying the technical scheme of the application, the technical problem that independent static force loading cannot be carried out on the aircraft skin in the prior art can be solved.
Description
Technical Field
The application relates to the technical field of structural dynamic strength test verification under multi-field coupling of an aircraft, in particular to an aircraft skin static force loading device and a skin dynamic strength test method.
Background
In the high-speed flight of an aircraft, aerodynamic force, aerodynamic heat and aerodynamic noise loads are simultaneously acted on the surface of a titanium alloy skin structure, and under the combined action of the three loads, a complex dynamic strength failure risk exists for important stress force transmission and skin structures related to flight safety, particularly a metal thin-wall skin structure, and the complex dynamic strength problem is not mature and reliable analysis method in the current engineering. Moreover, when the combined test of force, heat and noise load is performed on the skin structure at the same time, because the equipment space for performing the noise test on the skin structure is limited, and the skin needs to be heated at the same time, conventional force loading equipment, such as an actuator cylinder loading equipment, cannot be used for loading static force on the skin.
Disclosure of Invention
The present application aims to solve at least one of the technical problems existing in the prior art.
According to an aspect of the present application, there is provided an aircraft skin static force loading device comprising: the device comprises an outer frame, a force transducer, an elastic component and a static force application component; the outer frame is provided with a containing cavity, the aircraft skin is arranged in the containing cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end of the aircraft skin opposite to the one end of the aircraft skin is connected with the force transducer, and the force transducer is used for measuring the static force applied to the aircraft skin; the elastic component is respectively connected with the force transducer and the static force applying component, and the static force applying component applies static force to the aircraft skin through the elastic component and the force transducer.
Further, the elastic member is a disc spring.
Further, the static force applying assembly comprises a pressing plate and a plurality of fasteners, wherein the pressing plate is connected with the elastic component, the fasteners are respectively connected with the pressing plate and the outer frame, and the fasteners are used for adjusting the distance between the pressing plate and the aircraft skin.
Further, the fastener is a bolt, and the pressing plate and the outer frame are both provided with threaded holes matched with the bolt.
According to another aspect of the present application, there is provided an aircraft skin structure dynamic strength test method, comprising: fixedly connecting one end of the aircraft skin with the inner side of the outer frame of the aircraft skin static force loading device, connecting the other end opposite to the one end of the aircraft skin with the force transducer, and connecting the static force applying assembly with the aircraft skin through the elastic component and the force transducer; adjusting the static force applying component according to the output value of the force transducer to enable the static force applied to the aircraft skin to reach a preset value; installing an aircraft skin static force loading device and an aircraft skin into noise equipment; installing heating equipment outside the noise equipment; and controlling the noise equipment and the heating equipment to perform skin dynamic strength test according to a preset noise control curve and a temperature load control curve respectively.
Further, prior to installing the aircraft skin in the aircraft skin static force loading device, the aircraft skin structure dynamic strength test method further comprises: and performing simulation analysis on the aircraft skin to obtain a preset value of static force applied to the aircraft skin and a static force loading point position.
Further, the heating device is arranged parallel to the surface of the aircraft skin.
Further, the noise equipment and the heating equipment are controlled by the measuring system to perform skin dynamic strength test according to a preset noise control curve and a temperature load control curve respectively.
Further, after the heating device is installed outside the noise device, the method for testing the dynamic strength of the aircraft skin structure further comprises the following steps: the measurement system, noise device and heating device are commissioned and pre-tested.
By applying the technical scheme of the application, the static force loading device for the aircraft skin and the dynamic strength testing method for the skin are provided, and the static force loading device for the aircraft skin applies static force to the aircraft skin through the elastic component and the force transducer by utilizing the static force applying component. The static force loading device for the aircraft skin is an independent loading device, and can meet the requirements of multi-field coupling tests of the aircraft skin. Compared with the prior art, the technical scheme of the application can solve the technical problem that the independent static force loading can not be carried out on the aircraft skin in the prior art.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. It is evident that the drawings in the following description are only some embodiments of the present application and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 illustrates a schematic structural view of an aircraft skin static force loading device provided in accordance with a specific embodiment of the present application;
fig. 2 shows a schematic structural view of an aircraft skin provided in accordance with a specific embodiment of the application.
Wherein the above figures include the following reference numerals:
1. an outer frame; 2. a load cell; 3. an elastic member; 4. a pressing plate; 5. a fastener; 6. aircraft skin.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1 and 2, according to an embodiment of the present application, there is provided an aircraft skin static force loading device including: the device comprises an outer frame, a force transducer, an elastic component and a static force application component; the outer frame is provided with a containing cavity, the aircraft skin is arranged in the containing cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end of the aircraft skin opposite to the one end of the aircraft skin is connected with the force transducer, and the force transducer is used for measuring the static force applied to the aircraft skin; the elastic component is respectively connected with the force transducer and the static force applying component, and the static force applying component applies static force to the aircraft skin through the elastic component and the force transducer.
By applying the configuration mode, the static force loading device for the aircraft skin is provided, and the static force loading device for the aircraft skin applies static force to the aircraft skin through the elastic component and the force transducer by utilizing the static force application assembly. The static force loading device for the aircraft skin is an independent loading device, and can meet the requirements of multi-field coupling tests of the aircraft skin. Compared with the prior art, the technical scheme of the application can solve the technical problem that the independent static force loading can not be carried out on the aircraft skin in the prior art.
Further, in the present application, in order to satisfy the application of high-strength static force to the aircraft skin, the elastic member may be configured as a disc spring. According to the application, the size and the number of the disc springs can be set according to the size of the static force obtained through simulation, so that the static force applied to the aircraft skin by the static force applying component through the disc springs can fully simulate aerodynamic force applied to the aircraft in the high-speed flight process, and further, the reliable analysis of the dynamic strength of the aircraft skin is obtained. As a specific embodiment of the application, the static force loading of which the aircraft skin stress is less than or equal to 50000N can be realized by adjusting the size and the number of the disc springs, so that the test requirement of simulating high-speed flight is met.
In addition, in order to realize the application of the static force to the aircraft skin, the static force application assembly comprises a pressing plate and a plurality of fasteners, wherein the pressing plate is connected with the elastic component, the fasteners are respectively connected with the pressing plate and the outer frame, and the fasteners are used for adjusting the distance between the pressing plate and the aircraft skin. In the application, the adjustment of the static force applied to the aircraft skin can be achieved by adjusting the distance between the pressure plate and the aircraft skin. The elastic component can be stably forced through the fasteners and the pressing plates, and meanwhile, after the static force applied to the aircraft skin reaches a preset value, the fasteners are not adjusted any more, so that the static force applied to the aircraft skin is in a constant force state, and other test tests such as a thermal noise test and the like can be conveniently carried out subsequently.
As a specific embodiment of the application, the fastening elements can be configured as bolts, the pressure plate and the outer frame are provided with threaded holes matching the bolts, and the distance between the pressure plate and the aircraft skin can be adjusted by means of a number of bolts. In the application, the number of the fasteners can be adjusted according to the actual fastening requirement, for example, two fasteners can be arranged.
Furthermore, the static force loading device for the aircraft skin is suitable for static force loading of the metal aircraft skin, for example, the static force loading device can be used for static force loading of the titanium alloy thin-wall skin.
According to another aspect of the present application, there is provided an aircraft skin structure dynamic strength test method comprising: fixedly connecting one end of the aircraft skin with the inner side of the outer frame of the aircraft skin static force loading device, connecting the other end opposite to the one end of the aircraft skin with the force transducer, and connecting the static force applying assembly with the aircraft skin through the elastic component and the force transducer; adjusting the static force applying component according to the output value of the force transducer to enable the static force applied to the aircraft skin to reach a preset value; installing an aircraft skin static force loading device and an aircraft skin into noise equipment; installing heating equipment outside the noise equipment; and controlling the noise equipment and the heating equipment to perform skin dynamic strength test according to a preset noise control curve and a temperature load control curve respectively.
Further, in the present application, before the aircraft skin is mounted on the aircraft skin static force loading device, the aircraft skin structure dynamic strength test method further includes: and performing simulation analysis on the aircraft skin to obtain a preset value of static force applied to the aircraft skin and a static force loading point position. In the application, the static force loading point is positioned at the other end of the aircraft skin, and the load cell is connected with the aircraft skin at the static force loading point.
Furthermore, in the present application, in order to reduce the space occupied by the heating device while ensuring an even heating of the aircraft skin, the heating device may be configured to be disposed parallel to the surface of the aircraft skin.
Further, in the application, the skin dynamic strength test can be performed by controlling the noise equipment and the heating equipment through the measuring system according to the preset noise control curve and the temperature load control curve respectively. According to the application, the measuring system can accurately regulate and control the noise equipment and the heating equipment, so that the accuracy of the skin dynamic strength test is improved.
In addition, in the application, after the heating equipment is installed outside the noise equipment, the method for testing the dynamic strength of the aircraft skin structure further comprises the following steps: the measurement system, noise device and heating device are commissioned and pre-tested. In the application, the reliability of the skin dynamic strength test can be improved by debugging and pre-testing the measuring system, the noise equipment and the heating equipment.
Furthermore, after the dynamic strength test of the aircraft skin structure is finished, the aircraft skin is subjected to appearance inspection, and the inspection result provides support for the optimization design, safety and reliability assessment of the dynamic strength of the thin-wall skin structure.
The static force loading device for the aircraft skin can meet the requirements of multi-field coupling tests of the aircraft skin, and the dynamic strength test method for the aircraft skin structure of the static force loading device for the aircraft skin achieves simultaneous loading of various loads of force, heat and noise on the skin.
In summary, the application provides an aircraft skin static force loading device and a skin dynamic strength test method, wherein the aircraft skin static force loading device applies static force to an aircraft skin through an elastic component and a load cell by utilizing a static force application component. The static force loading device for the aircraft skin is an independent loading device, and can meet the requirements of multi-field coupling tests of the aircraft skin. Compared with the prior art, the technical scheme of the application can solve the technical problem that the independent static force loading can not be carried out on the aircraft skin in the prior art.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present application.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (8)
1. The method for testing the dynamic strength of the aircraft skin structure is characterized by comprising the following steps of:
one end of the aircraft skin is fixedly connected with the inner side of an outer frame of the aircraft skin static force loading device, the other end opposite to the one end of the aircraft skin is connected with the force transducer, and the static force applying component is connected with the aircraft skin through the elastic component and the force transducer;
adjusting the static force applying component according to the output value of the force transducer to enable the static force applied to the aircraft skin to reach a preset value;
installing the aircraft skin static force loading device and the aircraft skin into a noise device;
installing heating equipment outside the noise equipment;
controlling the noise equipment and the heating equipment to perform skin dynamic strength test according to a preset noise control curve and a temperature load control curve respectively;
the aircraft skin static force loading device comprises: the device comprises an outer frame, a force transducer, an elastic component and a static force application component; the outer frame is provided with a containing cavity, the aircraft skin is arranged in the containing cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end of the aircraft skin opposite to the one end of the aircraft skin is connected with the force transducer, and the force transducer is used for measuring the static force applied to the aircraft skin; the elastic component is respectively connected with the force transducer and the static force applying component, and the static force applying component applies static force to the aircraft skin through the elastic component and the force transducer.
2. The method of claim 1, wherein the elastic member is a disc spring.
3. The method of claim 1, wherein the static force application assembly comprises a platen and a plurality of fasteners, the platen being coupled to the elastic member, the fasteners being coupled to the platen and the outer frame, respectively, the fasteners being used to adjust a distance between the platen and the aircraft skin.
4. The method for testing the dynamic strength of an aircraft skin structure according to claim 3, wherein said fasteners are bolts, and said pressure plate and said outer frame are each provided with threaded holes matching said bolts.
5. The method of claim 1, wherein prior to installing the aircraft skin in the aircraft skin static force loading device, the method further comprises: and performing simulation analysis on the aircraft skin to obtain a preset value of static force applied to the aircraft skin and a static force loading point position.
6. The method of claim 1, wherein the heating device is disposed parallel to a surface of the aircraft skin.
7. The method for testing the dynamic strength of the skin structure of the aircraft according to claim 1, wherein the measuring system controls the noise equipment and the heating equipment to respectively conduct the skin dynamic strength test according to a preset noise control curve and a preset temperature load control curve.
8. The method of claim 7, further comprising, after installing the heating device outside the noise device: debugging and pre-testing the measurement system, the noise device and the heating device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111189111.8A CN113879559B (en) | 2021-10-12 | 2021-10-12 | Aircraft skin static force loading device and skin dynamic strength test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111189111.8A CN113879559B (en) | 2021-10-12 | 2021-10-12 | Aircraft skin static force loading device and skin dynamic strength test method |
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| CN113879559A CN113879559A (en) | 2022-01-04 |
| CN113879559B true CN113879559B (en) | 2023-08-15 |
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| CN114721450B (en) * | 2022-06-10 | 2022-08-26 | 中国飞机强度研究所 | Heat test iteration temperature control method for temperature control in aerospace plane structural strength test |
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