CN107662713B - Follow-up loading device for large-deformation wing static test - Google Patents
Follow-up loading device for large-deformation wing static test Download PDFInfo
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- CN107662713B CN107662713B CN201710780266.6A CN201710780266A CN107662713B CN 107662713 B CN107662713 B CN 107662713B CN 201710780266 A CN201710780266 A CN 201710780266A CN 107662713 B CN107662713 B CN 107662713B
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
The utility model provides a follow-up loading device of large deformation wing static test relates to aircraft technical field. The follow-up loading device comprises a support, a sliding table, a translation driving device, a clamping device, a loading device, a position detection device and a control device. The bracket can be fixed on the ground. The sliding table is slidably arranged on the bracket and is positioned above the wing. The translation driving device is arranged on the support and connected with the sliding table and used for driving the sliding table to linearly move along a preset direction. The clamping device clamps and is fixed on the wing. The loading device is provided with a first end and a second end, the first end is hinged to the sliding table, the second end is connected with the clamping device through a connecting piece, and the loading device is used for drawing the wings. The position detection device is used for detecting the position change of the clamping device and sending displacement information. The control device is used for receiving the displacement information and controlling the translation driving device to drive the sliding platform to move linearly along the preset direction so that the connecting piece is perpendicular to the wing all the time.
Description
Technical Field
The invention relates to the technical field of airplanes, in particular to a follow-up loading device for a large-deformation wing static test.
Background
With the continuous improvement of the requirements on the comprehensive performance of the airplane, the wings with large aspect ratio and large deformation are used as a big characteristic of a new generation of airplane (especially an unmanned aerial vehicle), and in order to improve the structural efficiency of the airplane, a great amount of composite materials are adopted on the wing structure, so that the composite materials become a main index for measuring the advancement of the airplane structure. The composite material wing with the large aspect ratio has the characteristics of large bending moment at the root part, large deformation of a wing bending structure and larger challenge to a wing static test due to large deformation.
The existing loading equipment for the static test of the large-deformation wing can apply test loads at a plurality of positions on the wing, and the direction of the test loads is fixed and unchanged so as to simulate the aerodynamic loads of the wing in the actual flying process, thereby verifying the indexes of the wing such as strength, rigidity and stability and judging the performance of the wing. However, after a test load is applied to the wing, the wing usually undergoes bending deformation under the action of the test load, and particularly for a wing with a large aspect ratio, the bending deformation amplitude is large, so that a certain deviation occurs between the direction of the test load and the direction of the aerodynamic load. The larger the amplitude of the bending deformation of the wing, the more obvious the deviation, and finally, the larger the error between the data of the static test and the data of the theoretical calculation exists. Therefore, indexes such as rigidity, stability and bearing capacity of the wing structure are difficult to accurately verify, the performance of the wing is not easy to judge, and the design and improvement of the wing are also not easy to realize.
It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
It is an object of the present disclosure to provide a follow-up loading device for static tests of large morphing airfoils, thereby overcoming, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.
According to one aspect of the disclosure, a follow-up loading device for a static test of a large-deformation wing is provided, which is used for the static test of the wing, the root of the wing can be fixed on a mounting surface perpendicular to the ground, and the follow-up loading device for the static test of the large-deformation wing comprises:
the bracket can be fixed on the ground;
the sliding table is slidably arranged on the bracket and is positioned above the wing;
the translation driving device is arranged on the support and connected with the sliding table and used for driving the sliding table to linearly move along a preset direction, and the preset direction is parallel to the wingspan direction of the wing;
the clamping device clamps and is fixed on the wing;
the loading device is provided with a first end and a second end, the first end is hinged to the sliding table, the second end is connected with the clamping device through a connecting piece, and the loading device is used for drawing the wing;
the position detection device is used for detecting the position change of the clamping device and sending displacement information;
and the control device is used for receiving the displacement information and controlling the translation driving device to drive the sliding platform to linearly move along the preset direction so as to enable the connecting piece to be perpendicular to the wing.
In an exemplary embodiment of the present disclosure, the displacement information includes an angular displacement, a horizontal displacement, and a vertical displacement of the clamping device.
In an exemplary embodiment of the present disclosure, controlling the translation driving device to drive the sliding table to move linearly along the preset direction includes:
determining an adjustment displacement according to the angular displacement, the horizontal displacement and the vertical displacement;
and controlling the translation driving device to drive the sliding table to linearly move along the preset direction by the adjustment displacement.
In an exemplary embodiment of the present disclosure, determining an adjustment displacement from the angular displacement, the horizontal displacement, and the vertical displacement includes:
calculating the adjustment displacement according to a preset formula, wherein the preset formula is as follows:
Δl＝Δx+(H-Δy)tanγ；
wherein Δ l is the adjustment displacement, γ is the angular displacement, Δ x is the horizontal displacement, Δ y is the vertical displacement, and H is the distance between the first end and the clamping device.
In an exemplary embodiment of the present disclosure, the position detecting device includes:
an angular displacement sensing assembly for detecting the angular displacement;
and the linear displacement sensing assembly is used for detecting the horizontal displacement and the vertical displacement.
In an exemplary embodiment of the disclosure, a guide rail parallel to the span direction is arranged at the top of the bracket, and the sliding table is provided with a roller which is arranged on the guide rail in a matching manner.
In an exemplary embodiment of the present disclosure, the clamping device includes:
the upper clamping plate is arranged above the wing;
the lower clamping plate is arranged below the wing;
and the connecting bolt is simultaneously connected with the upper clamping plate and the lower clamping plate so that the upper clamping plate and the lower clamping plate clamp the wing.
In an exemplary embodiment of the present disclosure, the upper plate includes:
the upper bottom plate is arranged above the wings;
the upper cushion blocks are arranged on the surface, close to the wing, of the upper base plate, and are matched with the upper surface of the wing;
the lower splint includes:
the lower bottom plate is arranged below the wings and is connected with the upper bottom plate through the connecting bolt;
and the lower cushion blocks are arranged on the lower bottom plate and close to the surface of the wing, and the lower cushion blocks are matched with the lower surface of the wing.
In an exemplary embodiment of the present disclosure, the upper plate further includes:
the upper elastic cushions are correspondingly arranged on the upper cushion blocks one by one and clamped between the upper cushion blocks and the upper surface of the wing;
the lower splint further includes:
and the lower elastic cushions are correspondingly arranged on the lower cushion blocks one by one and are clamped between the lower cushion blocks and the lower surface of the wing.
In an exemplary embodiment of the disclosure, the translation drive and/or the loading device is a ram.
The follow-up loading device for the static test of the large-deformation wing can be used for pulling the wing through the connecting piece and the clamping device so as to apply test load. Meanwhile, when the position of the clamping device changes, the wing is shown to be subjected to bending deformation, the position change of the clamping device, namely the change of the position of the load action can be detected through the position detection device, and displacement information is sent out. The control device can control the translation driving device according to the displacement information, the translation driving device drives the sliding platform to linearly move along a preset direction, the connecting piece is guaranteed to be perpendicular to the wing all the time, the direction of the test load is perpendicular to the wing all the time, therefore, the pneumatic load during actual flight can be simulated more accurately, the deviation between the test load and the pneumatic load is reduced, the accuracy of a test result is improved, and the design and the improvement of the wing are facilitated.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
Fig. 1 is a schematic diagram of a follow-up loading device for a static test of a large deformation wing according to an exemplary embodiment of the disclosure.
Fig. 2 is an enlarged view of a portion a in fig. 1.
Fig. 3 is a schematic diagram illustrating installation of a sliding table and a frame of a follow-up loading device for a static test of a large morphing wing according to an exemplary embodiment of the disclosure.
Fig. 4 is a schematic diagram illustrating connection of a sliding table and a loading device of a follow-up loading device for a static test of a large morphing wing according to an exemplary embodiment of the disclosure.
Fig. 5 is a schematic diagram of a clamping device of a follow-up loading device for a static test of a large deformation wing according to an exemplary embodiment of the disclosure.
Fig. 6 is a schematic diagram of a clamping device of a follow-up loading device for a large deformation wing static test according to an example embodiment of the disclosure clamping a wing.
Fig. 7 is a schematic diagram of the principle of determining the adjustment displacement in the follow-up loading device of the static test of the large-deformation wing according to the exemplary embodiment of the disclosure.
Fig. 8 is a schematic circuit block diagram of a follow-up loading device for a static test of a large-deformation wing according to an exemplary embodiment of the disclosure.
FIG. 9 is a schematic illustration of a static test performed using a plurality of wings according to an exemplary embodiment of the present disclosure.
In the figure: 1. a support; 101. a frame body; 1011. a guide rail; 102. a column; 2. a sliding table; 21. a roller; 22. a hinged seat; 3. a translation drive device; 4. a clamping device; 41. an upper splint; 411. an upper base plate; 412. an upper cushion block; 413. an upper elastic pad; 42. a lower splint; 421. a lower base plate; 422. a lower cushion block; 423. a lower elastic pad; 43. a connecting bolt; 5. a loading device; 6. a position detection device; 61. an angular displacement sensing assembly; 62. a linear displacement sensing assembly; 7. a control device; 8. a connecting member; 9. an airfoil; 10. a mounting surface; 11. and (4) the ground.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed description will be omitted.
Although relative terms, such as "upper" and "lower," may be used in this specification to describe one element of an icon relative to another, these terms are used in this specification for convenience only, e.g., in accordance with the orientation of the examples described in the figures. It will be appreciated that if the device of the icon were turned upside down, the element described as "upper" would become the element "lower". When a structure is "on" another structure, it may mean that the structure is integrally formed with the other structure, or that the structure is "directly" disposed on the other structure, or that the structure is "indirectly" disposed on the other structure via another structure.
The terms "a," "an," "the," and "said" are used to indicate the presence of one or more elements/components/etc.; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.; the terms "first," "second," and the like are used merely as labels, and are not limiting on the number of their objects.
The example embodiment provides a follow-up loading device for a static test of a large deformation wing, as shown in fig. 1 to 8, the follow-up loading device for the static test of the large deformation wing can be used for performing the static test on the wing 9, the root of the wing 9 can be fixed on a mounting surface 10, the mounting surface 10 can be a wall surface perpendicular to the ground 11 or other surfaces, and the wingspan direction of the wing 9 can be perpendicular to the mounting surface 10, namely parallel to the ground 11. The follow-up loading device for the static test of the large-deformation wing of the exemplary embodiment may include a support 1, a sliding table 2, a translation driving device 3, a clamping device 4, a loading device 5, a position detection device 6 and a control device 7.
The support 1 can be fixed on the ground 11 by welding or bolting, and the structure of the support 1 can be various, for example, the support 1 can include a frame 101 and a column 102, wherein:
the frame body 101 may be rectangular, and may be formed by a plurality of side beams, and the adjacent side beams may be fixedly connected by welding, clamping, or using bolts; of course, the housing 101 may be an integral structure. The frame 101 may be horizontally disposed above the wing 9, and the longitudinal direction of the frame 101 is parallel to the span direction. The frame 101 may have other shapes, and these shapes are listed here.
The cross-section of the post 102 may be circular, rectangular, etc., and is not particularly limited herein. The top ends of the pillars 102 may be fixed to the bottom surface of the frame 101 by welding, clamping, or the like, the bottom ends of the pillars 102 may be fixed to the ground 11 by anchor screws, and the pillars 102 may be disposed perpendicular to the ground 11, so that the frame 101 may be supported above the wings 9. The number of the pillars 102 may be multiple, for example, four, and four pillars 102 may be respectively supported at four corners of the frame 101 and symmetrically distributed on two sides of the wing 9. Of course, each of the columns 102 and the frame 101 may be formed integrally. The height of the mast 102 may be 2.5 times the ultimate deflection of the wing 9, but is not so limited; the distance between two opposite vertical columns 102 on both sides of the wing 9 may be 2 times the width of the root of the wing 9, but is not limited thereto.
Of course, the structure of the bracket 1 is not limited to the above exemplary description, and it may be other structures, which are not listed here.
The sliding table 2 may be a flat plate structure, and may be rectangular or other shape, and the length thereof is not less than the width of the frame 101 of the bracket 1. The sliding platform 2 can be arranged on the top of the bracket 1 and can move linearly on the top of the bracket 1 along a preset direction, and the preset direction can be parallel to the wingspan direction of the wing 9.
The linear movement of the sliding platform 2 on the bracket 1 can be realized by the matching of rollers and guide rails or other ways.
For example, as shown in fig. 3, two ends of the sliding table 2 may be provided with rollers 21, and the number of the rollers 21 may be four, and the rollers are symmetrically disposed at two ends of the sliding table 2. Of course, the number of the rollers 21 is not limited thereto, and may be other numbers.
The frame 101 of the support 1 may be provided with a guide rail 1011, and the guide rail 1011 may be fixedly connected to the frame 101 by welding, clamping, or bolting. Of course, the guide rails 1011 may be integrally formed on the housing 101. The guide rails 1011 may be a linear structure, the extending direction of the guide rails 1011 may be parallel to the preset direction, the number of the guide rails 1011 may be two, two guide rails 1011 are disposed in parallel on two long edges of the frame 101, and the two guide rails 1011 may be disposed on two sides of the wing 9 symmetrically. The rollers 21 at the two ends of the sliding table 2 can be respectively matched with the two guide rails 1011, so that the sliding table 2 can linearly move along the preset direction.
It should be noted that, by providing the rollers on the support 1 and providing the corresponding guide rails on the sliding table 2, the sliding table 2 can also move linearly on the support 1, and details thereof are not described here. In addition, the linear movement of the slide 2 on the carriage 1 can also be realized in other ways, which are not listed here.
As shown in fig. 3, the translation drive device 3 may be a ram, and the type and specification thereof are not particularly limited. The actuating cylinder can be provided with a cylinder body and a push rod, the cylinder body of the actuating cylinder can be fixed on the frame body 101 of the bracket 1 in a welding, clamping or bolt connection mode, and the like, and the push rod can be arranged along the preset direction and can linearly reciprocate relative to the cylinder body; the push rod can be fixedly connected with the sliding table 2 in a welding or threaded connection mode and the like. Therefore, the push rod of the actuator cylinder can push the sliding table 2 to move linearly along the preset direction, and the sliding table 2 can move for any distance by controlling the actuator cylinder.
Of course, the translation driving device 3 may also be another driving device capable of achieving linear movement, as long as the sliding table 2 can be driven to linearly move along the preset direction, and the moving distance is controllable, which is not listed here any more.
As shown in fig. 2, 5 and 6, the holding device 4 can hold the wing 9 from the upper and lower sides of the wing 9 and fix the wing 9 at a predetermined position. The clamping device 4 may include an upper clamp plate 41, a lower clamp plate 42, and a connection bolt 43, wherein:
the upper clamp plate 41 may include an upper base plate 411, an upper pad 412, and an upper elastic pad 413, wherein:
the upper plate 411 may be a U-shaped plate or a strip-shaped plate. It may be arranged horizontally above the wing 9 and its length direction, i.e. the direction of extension, may be perpendicular to the wingspan direction. The length of the upper clamping plate 41 can be larger than the width of the wing 9, so that the end part of the upper clamping plate 41 can exceed the edge of the wing 9, and the length of the upper clamping plate 41 exceeding the edge of the wing 9 can be 150mm, but not limited to this.
The number of the upper cushion blocks 412 may be multiple, and multiple upper cushion blocks 412 may be distributed on the surface of the upper base plate 411 close to the wing 9 along the length direction of the upper base plate 411. Each upper spacer block 412 may be fixed to the surface of the upper base plate 411 near the wing 9 by welding, clamping, or bolting. The lower surface of any of the upper blocks 412 may match the shape of the area of the upper surface of the wing 9 corresponding to that upper block 412, the lower surface of the upper block 412 being the surface of the upper block 412 adjacent to the upper surface of the wing 9. So as to more closely conform to the upper surface of the wing 9.
The upper elastic pad 413 may be made of an elastic material such as rubber, and the number of the upper elastic pads 413 may be plural and may be the same as that of the upper pad 412, and the thickness of the upper elastic pad 413 may be 3mm, but not limited thereto. Each of the upper elastic pads 413 may be adhered to the lower surface of each of the upper pads 412 in a one-to-one correspondence. The upper base plate 411 and the upper pad 412 can be pressed down on the wing 9, so that the upper elastic pad 413 is clamped between the upper pad 412 and the upper surface of the wing 9, and the upper elastic pad 413 has elasticity, so that the upper elastic pad is favorable for being in close contact with the upper surface of the wing 9, and the wing 9 is prevented from being damaged.
Of course, the upper clamping plate 41 may also have other structures, for example, the upper clamping plate 41 may also have a flat plate structure, and the lower surface of the flat plate may match with the upper surface of the wing 9, so as to be able to fit the upper surface of the wing 9. Are not listed here.
The lower clamping plate 42 may include a lower base plate 421, a lower pad 422, and a lower elastic pad 423, wherein:
the lower plate 421 may also be a U-shaped plate or a strip-shaped flat plate. It may be positioned horizontally below the wing 9 and its length may be perpendicular to the span direction. The length of the lower clamping plate 42 may be greater than the width of the wing 9, so that the end of the lower clamping plate may extend beyond the edge of the wing 9, and the length of the lower clamping plate 42 extending beyond the edge of the wing 9 may be 150mm, but is not limited thereto. Lower plate 421 and upper plate 411 may be symmetrical about wing 9.
The number of the lower cushion blocks 422 may be multiple, and the multiple lower cushion blocks 422 may be distributed on the surface of the lower base plate 421, which is close to the wing 9, along the length direction of the lower base plate 421. Each lower cushion 422 may be fixed to the surface of the lower plate 421 near the wing 9 by welding, clamping, or bolting. The upper surface of any one of the lower pads 422 may match the shape of the area of the lower surface of the wing 9 corresponding to that lower pad 422, the upper surface of the lower pad 422 being the surface of the lower pad 422 adjacent to the lower surface of the wing 9. So as to more closely conform to the lower surface of wing 9.
The lower elastic pad 423 may be made of an elastic material such as rubber, the number of the lower elastic pads may be multiple, and may be the same as the number of the lower pads 422, and the thickness of the lower elastic pad 423 may also be 3mm, but not limited thereto. Each of the lower elastic pads 423 may be adhered to the upper surface of each of the lower pads 422 in a one-to-one correspondence. The lower base plate 421 and the lower cushion block 422 can be pressed onto the wing 9, so that the lower elastic cushion 423 is clamped between the lower cushion block 422 and the lower surface of the wing 9, and the lower elastic cushion 423 has elasticity, so that the lower elastic cushion is favorable for being in close contact with the lower surface of the wing 9, and the wing 9 is prevented from being damaged.
Of course, other configurations for the lower jaw 42 are possible. Are not listed here.
The connecting bolt 43 has one end connected to the upper clamping plate 41 and the other end connected to the lower clamping plate 42, so that the distance between the upper clamping plate 41 and the lower clamping plate 42 can be adjusted by the connecting bolt 43, and the upper clamping plate 41 and the lower clamping plate 42 clamp the wing 9. The number of the connecting bolts 43 is not particularly limited herein. For example, the number of the connecting bolts 43 is two, and the connecting bolts are respectively disposed on two sides of the wing 9, and the upper bottom plate 411 of the upper clamping plate 41 and the lower bottom plate 421 of the lower clamping plate 42 can be connected by two connecting bolts 43 at the same time.
The above clamping device 4 is only an example and does not constitute a limitation on the structure of the clamping device 4, and the clamping device 4 may also adopt other structures as long as it can clamp the wing 9 and be fixed on the wing 9, which is not listed here.
As shown in fig. 4, the loading device 5 may have a first end and a second end, the first end may be hinged to the lower surface of the slide table 2, and the loading device 5 may rotate in a vertical plane with respect to the slide table 2 when the slide table 2 is linearly moved. The second end may be connected to the holding device 4 by a connection 8, whereby the wing 9 is pulled by the connection 8 to apply a test load to the wing 9. The application of the test load may be performed in stages, i.e. the test load may be applied several times and the test load may be increased in steps, the increasing magnitude may be 5%, although the increasing magnitude may be larger or smaller. The connecting member 8 may be a steel wire rope or other members capable of performing a connecting function, and is not particularly limited herein. Before the first pulling of the wing 9 is not performed, i.e. before the first application of the test load to the wing 9, the connection 8 is perpendicular to the wing 9, i.e. the initial position of the connection 8 is perpendicular to the wing 9.
For example: the loading device 5 may also be a ram which also has a cylinder, the bottom end of which may be the first end, and a ram, the end of which outside the cylinder may be the second end. The centre of the lower surface of the skid 2 may be provided with a hinge base 22, a first end of the ram may be hinged to the hinge base 22, and a second end of the ram may be connected to the upper base plate 411 via a steel cable, and the ram may be controlled to pull the upper base plate 411 via the steel cable, thereby applying a test load to the wing 9.
As shown in fig. 7 and 8, the position detection device 6 can detect a change in the position of the gripping device 4 and transmit displacement information. This displacement information may reflect a change in position of the region of the wing 9 corresponding to the clamping device 4, and thus a deformation of this region. The displacement information may include the angular displacement, the horizontal displacement, and the vertical displacement of the gripping device 4, but may also include only one or two of the angular displacement, the horizontal displacement, and the vertical displacement.
For example, the position detection device 6 may include an angular displacement sensing assembly 61 and a linear displacement sensing assembly 62, wherein:
the angular displacement sensing assembly 61 may detect the angular displacement of the clamping device 4. Angular displacement sensing assembly 61 may be an angular displacement sensor or other detection device capable of performing the same function, and is not further described herein. The angular displacement sensing assembly 61 may be mounted on the upper clamping plate 41 of the clamping device 4, or may be mounted on the wing 9 in an area corresponding to the clamping device 4, and the specific configuration of the angular displacement sensing assembly 61 may be determined, and the mounting position and manner thereof are not particularly limited as long as the angular displacement of the clamping device 4 can be detected.
The linear displacement sensing assembly 62 may be used to detect both horizontal and vertical displacement of the clamping device 4. The linear displacement sensing assembly 62 may include two linear displacement sensors for detecting the horizontal displacement and the vertical displacement of the holding device 4, respectively; alternatively, the linear displacement sensing assembly 62 may be other detection devices capable of performing the same function, and are not listed here. The linear displacement sensing assembly 62 may be mounted on the upper clamping plate 41 or the lower clamping plate 42 of the clamping device 4, or may be mounted on the wing 9 in an area corresponding to the clamping device 4, and the mounting position and the mounting manner of the linear displacement sensing assembly 62 are not particularly limited, as long as the horizontal displacement and the vertical displacement of the clamping device 4 can be detected.
As shown in fig. 8, the control device 7 may be connected to the position detecting device 6 and the translation driving device 3, and may receive the displacement information, and may control the translation driving device 3 according to the displacement information, so as to linearly move the sliding platform 2 along a predetermined direction, so that the connecting element 8 and the wing 9 are always perpendicular to each other. The control device 7 may be a microprocessor such as a single chip microcomputer, or a control device such as a computer, or an industrial control system such as an MTI control system.
For example, the control device 7 is connected to both the angular displacement sensing element 61 and the linear displacement sensing element 62, as shown in fig. 7, and the positions of the wing 9 and the components after the wing 9 is bent are shown by the dashed lines in fig. 7. The control device 7 can calculate the adjustment displacement according to a preset formula after receiving the angular displacement, the horizontal displacement and the vertical displacement of the clamping device 4, wherein the preset formula is as follows:
Δl＝Δx+(H-Δy)tanγ；
wherein, Δ l is the adjustment displacement of the clamping device 4, and γ is the angular displacement of the clamping device 4; Δ x is the horizontal displacement of the holding device 4, Δ y is the vertical displacement of the holding device 4, and H is the distance between the first end and the holding device 4. In the case of a connection 8 perpendicular to the wing 9, its angle to the vertical is equal to the angular displacement γ.
Subsequently, the control device 7 can control the translation driving device 3 to drive the sliding table 2 to move linearly along the preset direction, and the moving displacement is the adjusting displacement.
As can be seen from fig. 7, when the wing 9 is subjected to bending deformation, if the sliding table 2 moves by Δ l, the connecting member 8 and the wing 9 can be kept perpendicular to each other, so that the direction of the test load more conforms to the direction of the actual aerodynamic load, which is beneficial to improving the accuracy of the test result.
Of course, the adjustment displacement can also be determined in other ways, as long as the connection is perpendicular to the wing 9, and will not be described in detail here.
It should be noted that for a wing 9 with a long span, it may be necessary to apply test loads to several locations of the wing 9 in the span-wise direction. As shown in fig. 9, a plurality of follow-up loading devices for the static test of the large morphing wing according to the present exemplary embodiment may be adopted, for example, two follow-up loading devices are sequentially distributed in the wingspan direction, the structure and the installation manner of the follow-up loading devices for the static test of the large morphing wing are the same, except that the clamping devices 4 of the follow-up loading devices for the static test of the large morphing wing are clamped at different positions of the wing 9, and because the deformation degrees at different positions are different, the moving distances of the slipways 2 may be different, but it is ensured that each of the connectors 8 is perpendicular to the wing 9.
The follow-up loading device for the static test of the large-deformation wing of the exemplary embodiment can be used for applying a test load by pulling the wing 9 through the connecting piece 8 and the clamping device 4 by the loading device 5. Meanwhile, when the position of the clamping device 4 changes, the wing 9 is shown to be subjected to bending deformation, the position change of the clamping device 4, namely the position change of the test load action can be detected through the position detection device 6, and displacement information is sent out. The control device 7 can control the translation driving device 3 according to the displacement information, the translation driving device 3 drives the sliding table 2 to linearly move along a preset direction, the connecting piece 8 is guaranteed to be perpendicular to the wing 9 all the time, the direction of the test load is perpendicular to the wing 9 all the time, therefore, the pneumatic load during actual flight can be simulated more accurately, the deviation between the test load and the pneumatic load is reduced, the accuracy of the test result is improved, and the design and the improvement of the wing 9 are facilitated.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (7)
1. The follow-up loading device for the static test of the large-deformation wing is used for the static test of the wing, the root part of the wing can be fixed on a mounting surface vertical to the ground, and the follow-up loading device for the static test of the large-deformation wing is characterized by comprising:
the bracket can be fixed on the ground; the sliding table is slidably arranged on the bracket and is positioned above the wing; the translation driving device is arranged on the support and connected with the sliding table and used for driving the sliding table to linearly move along a preset direction, and the preset direction is parallel to the wingspan direction of the wing; the clamping device clamps and is fixed on the wing;
the loading device is provided with a first end and a second end, the first end is hinged to the sliding table, the second end is connected with the clamping device through a connecting piece, and the loading device is used for drawing the wing;
the position detection device is used for detecting the position change of the clamping device and sending displacement information;
the control device is used for receiving the displacement information, and the displacement information comprises the angular displacement, the horizontal displacement and the vertical displacement of the clamping device; determining an adjusting displacement according to the angular displacement, the horizontal displacement and the vertical displacement, and controlling the translation driving device to drive the sliding platform to linearly move along the preset direction by the adjusting displacement so as to enable the connecting piece to be perpendicular to the wing;
determining an adjustment displacement based on the angular displacement, the horizontal displacement, and the vertical displacement includes calculating the adjustment displacement based on a preset formula,
Δl＝Δx+(H-Δy)tanγ；
wherein Δ l is the adjustment displacement, γ is the angular displacement, Δ x is the horizontal displacement, Δ y is the vertical displacement, and H is the distance between the first end and the clamping device.
2. The follow-up loading device for the static test of the large-deformation wing according to claim 1, wherein the position detection device comprises:
an angular displacement sensing assembly for detecting the angular displacement; and the linear displacement sensing assembly is used for detecting the horizontal displacement and the vertical displacement.
3. The follow-up loading device for the static test of the large-deformation wing according to any one of claims 1-2, wherein a guide rail parallel to the wingspan direction is arranged at the top of the bracket, and the sliding table is provided with a roller which is arranged on the guide rail in a matching manner.
4. The follow-up loading device for the static test of the large-deformation wing according to any one of claims 1-2, wherein the clamping device comprises:
the upper clamping plate is arranged above the wing; the lower clamping plate is arranged below the wing;
and the connecting bolt is simultaneously connected with the upper clamping plate and the lower clamping plate so that the upper clamping plate and the lower clamping plate clamp the wing.
5. The follow-up loading device for the static test of the large-deformation wing according to claim 4, wherein the upper clamping plate comprises:
the upper bottom plate is arranged above the wings; the upper cushion blocks are arranged on the surface, close to the wing, of the upper base plate, and are matched with the upper surface of the wing; the lower splint includes:
the lower bottom plate is arranged below the wings and is connected with the upper bottom plate through the connecting bolt;
and the lower cushion blocks are arranged on the lower bottom plate and close to the surface of the wing, and the lower cushion blocks are matched with the lower surface of the wing.
6. The follow-up loading device for the static test of the large-deformation wing according to claim 5, wherein the upper clamping plate further comprises:
the upper elastic cushions are correspondingly arranged on the upper cushion blocks one by one and clamped between the upper cushion blocks and the upper surface of the wing;
the lower splint further includes: and the lower elastic cushions are correspondingly arranged on the lower cushion blocks one by one and are clamped between the lower cushion blocks and the lower surface of the wing.
7. The follow-up loading device for the static test of the large-deformation wing according to claim 1, wherein the translation driving device and/or the loading device is an actuating cylinder.
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| CN108956179A (en) * | 2018-07-03 | 2018-12-07 | 上海交通大学 | The vertical following loading device and method of self-balancing |
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| CN110243686A (en) * | 2019-05-22 | 2019-09-17 | 航天科工防御技术研究试验中心 | A kind of loading method of loading device and power |
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| CN114486517B (en) * | 2021-12-28 | 2023-06-30 | 中国航空工业集团公司北京长城航空测控技术研究所 | Follow-up loading device and method based on industrial robot system |
| CN114633900B (en) * | 2022-05-20 | 2022-08-12 | 中国飞机强度研究所 | Large-stroke aircraft airfoil static loading system and method for aircraft strength test |
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