CN113879559A - 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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- CN113879559A CN113879559A CN202111189111.8A CN202111189111A CN113879559A CN 113879559 A CN113879559 A CN 113879559A CN 202111189111 A CN202111189111 A CN 202111189111A CN 113879559 A CN113879559 A CN 113879559A
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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
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention 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 measuring sensor, an elastic component and a static force applying assembly; the outer frame is provided with an accommodating cavity, the aircraft skin is arranged in the accommodating cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end opposite to one end of the aircraft skin is connected with the force measuring sensor, and the force measuring sensor 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 assembly, and the static force applying assembly applies static force to the aircraft skin through the elastic component and the force transducer. By applying the technical scheme of the invention, the technical problem that the aircraft skin cannot be independently loaded with the static force in the prior art can be solved.
Description
Technical Field
The invention 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 simultaneously act on the surface of a titanium alloy skin structure, under the combined action of the three loads, complex dynamic strength failure risks exist for the important skin structure which is stressed and transmits force and relates to flight safety, particularly a metal thin-wall skin structure, and the complex dynamic strength problem does not have a mature and reliable analysis method in the current engineering. Moreover, when a force, heat and noise load combined test is simultaneously performed on the skin structure, the skin structure is heated due to the limited space of equipment for performing the noise test on the skin structure, so that the skin cannot be loaded with static force by using conventional force loading equipment, such as actuating cylinder loading equipment.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art.
According to an aspect of the invention, there is provided an aircraft skin static force loading device, comprising: the device comprises an outer frame, a force measuring sensor, an elastic component and a static force applying assembly; the outer frame is provided with an accommodating cavity, the aircraft skin is arranged in the accommodating cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end opposite to one end of the aircraft skin is connected with the force measuring sensor, and the force measuring sensor 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 assembly, and the static force applying assembly applies static force to the aircraft skin through the elastic component and the force transducer.
Further, the elastic component is a disc spring.
Further, the static force applying assembly comprises a pressing plate and a plurality of fasteners, 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 the bolt, and clamp plate and frame all are provided with the screw hole with bolt assorted.
According to another aspect of the invention, a method for testing the dynamic strength of an aircraft skin structure is provided, and the method for testing the dynamic strength of the aircraft skin structure comprises the following steps: one end of the aircraft skin is fixedly connected with the inner side of the outer frame of the aircraft skin static force loading device, the other end opposite to one end of the aircraft skin is connected with the force transducer, and the static force applying assembly is connected with the aircraft skin through the elastic component and the force transducer; adjusting the static force applying assembly 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 noise equipment; a heating device is arranged outside the noise device; and the noise control equipment and the heating equipment are controlled to carry out skin dynamic strength tests according to a preset noise control curve and a temperature load control curve respectively.
Further, before the aircraft skin is installed on the aircraft skin static force loading device, the aircraft skin structure dynamic strength test method further comprises the following steps: and carrying out simulation analysis on the aircraft skin to obtain a preset value of the static force borne by the aircraft skin and the position of a static force loading point.
Further, the heating device is arranged parallel to the surface of the aircraft skin.
And further, controlling noise equipment and heating equipment through a measuring system to perform a 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, the noise equipment and the heating equipment are debugged and pretested.
The technical scheme of the invention provides an aircraft skin static force loading device and a skin dynamic strength test method. The aircraft skin static force loading device is an independent loading device and can meet the requirement of a multi-field coupling test of the aircraft skin. Compared with the prior art, the technical scheme of the invention can solve the technical problem that the aircraft skin cannot be independently loaded with the static force in the prior art.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a schematic structural diagram of an aircraft skin static force loading device provided in accordance with a specific embodiment of the present invention;
FIG. 2 illustrates a structural schematic of an aircraft skin provided in accordance with a particular embodiment of the invention.
Wherein the figures include the following reference numerals:
1. an outer frame; 2. a force sensor; 3. an elastic member; 4. pressing a plate; 5. a fastener; 6. an aircraft skin.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. 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 only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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.
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 example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those 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 particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 and 2, according to a specific embodiment of the present invention, there is provided an aircraft skin static force loading device, including: the device comprises an outer frame, a force measuring sensor, an elastic component and a static force applying assembly; the outer frame is provided with an accommodating cavity, the aircraft skin is arranged in the accommodating cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end opposite to one end of the aircraft skin is connected with the force measuring sensor, and the force measuring sensor 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 assembly, and the static force applying assembly 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 applies static force to the aircraft skin through the elastic component and the force transducer by using the static force applying assembly. The aircraft skin static force loading device is an independent loading device and can meet the requirement of a multi-field coupling test of the aircraft skin. Compared with the prior art, the technical scheme of the invention can solve the technical problem that the aircraft skin cannot be independently loaded with the static force in the prior art.
Further, in the present invention, in order to satisfy the application of high-strength static force to the aircraft skin, the configurable elastic component is a disc spring. In the invention, the size and the number of the disc springs can be set according to the size of the static force obtained by simulation, so that the static force applied to the aircraft skin by the static force applying component through the disc springs can fully simulate the aerodynamic force applied to the aircraft in the high-speed flight process, and further the reliable analysis on the dynamic strength of the aircraft skin is obtained. As a specific embodiment of the invention, by adjusting the size and the number of the disc springs, the static force loading of the aircraft skin with the stress less than or equal to 50000N can be realized, and the test requirement of simulating high-speed flight is met.
In addition, in the invention, in order to realize the application of the static force to the aircraft skin, the configurable 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 invention, the adjustment of the static force applied to the aircraft skin can be realized by adjusting the distance between the pressure plate and the aircraft skin. The stable force application to the elastic component can be realized through the plurality of fasteners and the pressing plate, and meanwhile, after the static force received by the aircraft skin reaches the preset value, the fasteners are not adjusted any more, so that the static force received by the aircraft skin is in a constant force state, and other subsequent test tests such as a thermal noise test and the like are conveniently carried out.
As a specific embodiment of the invention, the fasteners can be configured as bolts, the pressure plate and the outer frame are provided with threaded holes matched with the bolts, and the distance between the pressure plate and the aircraft skin can be adjusted through a plurality of bolts. In the invention, the number of the fastening pieces can be adjusted according to the actual fastening requirement, and for example, two fastening pieces can be arranged.
Further, the aircraft skin static force loading device is suitable for static force loading of metal aircraft skins, and can be used for static force loading of titanium alloy thin-wall skins.
According to another aspect of the invention, an aircraft skin structure dynamic strength test method is provided, and comprises the following steps: one end of the aircraft skin is fixedly connected with the inner side of the outer frame of the aircraft skin static force loading device, the other end opposite to one end of the aircraft skin is connected with the force transducer, and the static force applying assembly is connected with the aircraft skin through the elastic component and the force transducer; adjusting the static force applying assembly 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 noise equipment; a heating device is arranged outside the noise device; and the noise control equipment and the heating equipment are controlled to carry out skin dynamic strength tests according to a preset noise control curve and a temperature load control curve respectively.
Further, in the present invention, before the aircraft skin is installed on the aircraft skin static force loading device, the aircraft skin structure dynamic strength test method further includes: and carrying out simulation analysis on the aircraft skin to obtain a preset value of the static force borne by the aircraft skin and the position of a static force loading point. In the invention, the position of the static force loading point is positioned at the other end of the aircraft skin, and the force measuring sensor is connected with the aircraft skin at the position of the static force loading point.
In addition, in the invention, in order to reduce the space occupied by the heating equipment and ensure that the aircraft skin is heated uniformly, the heating equipment can be configured to be parallel to the surface of the aircraft skin.
Further, in the invention, the skin dynamic strength test can be carried out by controlling the noise equipment and the heating equipment through the measuring system according to a preset noise control curve and a temperature load control curve respectively. According to the invention, 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 invention, 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, the noise equipment and the heating equipment are debugged and pretested. In the invention, the reliability of the skin dynamic strength test can be improved by debugging and pre-testing the measurement system, the noise equipment and the heating equipment.
Further, after the dynamic strength test of the aircraft skin structure is finished, the appearance of the aircraft skin is checked, and the check result provides support for the optimization design of the dynamic strength of the thin-wall skin structure and the evaluation of safety and reliability.
The aircraft skin static force loading device can meet the requirements of the aircraft skin multi-field coupling test, the aircraft skin structure dynamic strength test method adopting the aircraft skin static force loading device realizes simultaneous loading of multiple loads of force, heat and noise on the skin, the skin structure dynamic strength test is closer to the actual flight environment condition, and favorable support is provided for design and reliability evaluation of the aircraft thin-wall skin structure dynamic strength.
In summary, the invention provides an aircraft skin static force loading device and a skin dynamic strength test method. The aircraft skin static force loading device is an independent loading device and can meet the requirement of a multi-field coupling test of the aircraft skin. Compared with the prior art, the technical scheme of the invention can solve the technical problem that the aircraft skin cannot be independently loaded with the static force in the prior art.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship 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 of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An aircraft skin static force loading device, the aircraft skin static force loading device comprising: the device comprises an outer frame, a force measuring sensor, an elastic component and a static force applying assembly; the outer frame is provided with an accommodating cavity, an aircraft skin is arranged in the accommodating cavity, one end of the aircraft skin is fixedly connected with the inner side of the outer frame, the other end opposite to one end of the aircraft skin is connected with the force measuring sensor, and the force measuring sensor is used for measuring the static force applied to the aircraft skin; the elastic component is respectively connected with the load cell 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 load cell.
2. The aircraft skin static force loading apparatus of claim 1, wherein the resilient member is a belleville spring.
3. The aircraft skin static force loading apparatus of claim 1, wherein the static force applying assembly comprises a pressure plate and a plurality of fasteners, the pressure plate is connected to the elastic member, the fasteners are respectively connected to the pressure plate and the outer frame, and the fasteners are used to adjust a distance between the pressure plate and the aircraft skin.
4. The aircraft skin static force loading apparatus of claim 3, wherein the fasteners are bolts, and the pressure plate and the outer frame are provided with threaded holes that mate with the bolts.
5. The method for testing the dynamic strength of the aircraft skin structure is characterized by comprising the following steps of:
fixedly connecting one end of the aircraft skin with the inner side of the outer frame of the aircraft skin static force loading device as claimed in any one of claims 1 to 4, connecting the other end opposite to the one end of the aircraft skin with the load cell, and connecting the static force applying assembly with the aircraft skin through the elastic component and the load cell;
adjusting the static force applying assembly 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 a heating device outside the noise device;
and controlling the noise equipment and the heating equipment to perform a skin dynamic strength test according to a preset noise control curve and a temperature load control curve respectively.
6. The aircraft skin structure dynamic strength testing method of claim 5, wherein prior to installing the aircraft skin on the aircraft skin static force loading device, the aircraft skin structure dynamic strength testing method further comprises: and carrying out simulation analysis on the aircraft skin to obtain a preset value of the static force borne by the aircraft skin and the position of a static force loading point.
7. The aircraft skin structure dynamic strength testing method of claim 5, wherein the heating apparatus is disposed parallel to a surface of the aircraft skin.
8. The aircraft skin structure dynamic strength test method according to claim 5, characterized in that the skin dynamic strength test is performed by controlling the noise equipment and the heating equipment through the measurement system according to a preset noise control curve and a temperature load control curve, respectively.
9. The aircraft skin structure dynamic strength testing method according to claim 8, wherein after the heating device is installed outside the noise device, the aircraft skin structure dynamic strength testing method further comprises: debugging and pre-testing the measuring system, the noise equipment and the heating equipment.
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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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| 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 true CN113879559A (en) | 2022-01-04 |
| CN113879559B CN113879559B (en) | 2023-08-15 |
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Cited By (1)
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