CN112722325A - Static test device and method for fixed-wing unmanned aerial vehicle body - Google Patents
Static test device and method for fixed-wing unmanned aerial vehicle body Download PDFInfo
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- CN112722325A CN112722325A CN202110215280.8A CN202110215280A CN112722325A CN 112722325 A CN112722325 A CN 112722325A CN 202110215280 A CN202110215280 A CN 202110215280A CN 112722325 A CN112722325 A CN 112722325A
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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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Abstract
The invention discloses a static test device and method for an unmanned aerial vehicle body with fixed wings, and the static test device comprises an unmanned aerial vehicle body, wherein a lifting structure is detachably mounted at the bottom of the unmanned aerial vehicle body, a suspension structure is detachably mounted at the top of the unmanned aerial vehicle body, and pressurization structures are symmetrically mounted on two sides of the unmanned aerial vehicle body.
Description
Technical Field
The invention relates to a static test device and a static test method, in particular to a static test device and a static test method for a fixed-wing unmanned aerial vehicle body.
Background
The static test is one of the contents of the structural test, so that the distribution conditions of the strength, the rigidity, the stress and the deformation of the aircraft structure or component under the action of the static load can be observed and researched, and the static test is an important means for verifying the structural strength and the static analysis correctness of the aircraft.
The prior art is carrying out full-scale static test, and fixed wing unmanned aerial vehicle organism usually prevents the motion of fixed wing unmanned aerial vehicle organism, can not simulate the actual atress condition of fixed wing unmanned aerial vehicle organism completely.
Disclosure of Invention
Technical problem to be solved by the invention
The invention aims to provide a static test device and a static test method for a fixed-wing unmanned aerial vehicle body, and aims to solve the problems in the background art that when a full-size static test is carried out in the prior art, the fixed-wing unmanned aerial vehicle body is usually fixed, especially the fixed-wing unmanned aerial vehicle body is prevented from moving, and the actual stress condition of the fixed-wing unmanned aerial vehicle body cannot be completely simulated.
Technical scheme
In order to achieve the purpose, the invention provides the following technical scheme: the static test device comprises an unmanned aerial vehicle body, wherein a lifting structure is detachably mounted at the bottom of the unmanned aerial vehicle body, a suspension structure is detachably mounted at the top of the unmanned aerial vehicle body, and pressurizing structures are symmetrically mounted on two sides of the unmanned aerial vehicle body and are mounted on a support frame.
Preferably, the lifting structure comprises a lifting platform, the bottom of the lifting platform is fixedly provided with first electric telescopic rods in a central symmetry mode, the top of the lifting platform is symmetrically provided with placing grooves, the top of the lifting platform is symmetrically provided with first fixing structures, and the middle of each of the first fixing structures is provided with a first driving structure.
Preferably, the first fixing structure comprises a first fixing plate, the first fixing plate is slidably mounted on one side of the placing groove, one side of the first fixing plate is fixedly provided with one end of a second electric telescopic rod, the other end of the second electric telescopic rod is fixedly provided with a first supporting plate, the first supporting plate is fixedly mounted on one side of the top of the lifting platform, and the other side of the placing groove is slidably provided with a second fixing plate.
Preferably, the first driving structure comprises a second supporting plate, the second supporting plate is fixedly installed on one side of the top of the lifting platform, one side of the second supporting plate is symmetrically provided with one end of a third electric telescopic rod, each of the two ends of the third electric telescopic rod is fixedly provided with a driving block, two sides of each driving block are slidably provided with first extrusion blocks, one side of each first extrusion block is fixedly provided with one end of an extrusion column, and the other end of each extrusion column is fixedly connected with the second fixing plate
Preferably, the repeated structure is fixedly installed at the top of the first driving structure and comprises a third supporting plate, the third supporting plate is fixedly installed at the top of the first extrusion block, one end of a first spring is fixedly installed at one side of the third supporting plate, and the other end of the first spring is fixedly connected with the other end of the third supporting plate
Preferably, the suspension structure comprises a supporting block, sector plates are symmetrically and slidably mounted at the bottom of the supporting block, one end of a fourth electric telescopic rod is symmetrically and fixedly mounted at two sides of the supporting block, a fourth supporting plate is fixedly mounted at the other end of the fourth electric telescopic rod, the fourth supporting plate is in a C shape, one end of the fourth supporting plate is fixedly connected with the sector plates, and a second driving structure is arranged at the top of the supporting block.
Preferably, the second driving structure comprises a movable block, the movable block is trapezoidal, the movable block is fixedly installed at the top of the supporting block, second extrusion blocks are symmetrically and slidably installed on two sides of the movable block, one end of a fifth electric telescopic rod is fixedly installed on one side of each second extrusion block, and the other end of each fifth electric telescopic rod is fixed at the top of one side of the supporting frame.
Preferably, through the lift of elevation structure control unmanned aerial vehicle body, carry out the pressure boost through pressure boost structure at this in-process, carry out the first static experiment to the unmanned aerial vehicle organism this moment, the experiment stage in advance. Gradually and slowly adding a small load according to a certain program, observing and monitoring displacement and strain measurement points, finding out the basic trend of the bearing capacity and deformation of the structure, and checking the reliability of experimental parts, a support system, a loading device and measuring equipment;
and (5) a formal test stage. The method is characterized in that 0% of the predicted load is taken as the initial load, the initial stress, strain and displacement are measured, then the load is loaded step by step, uniformly and slowly according to a certain program, and the data of each strain measuring point, each displacement measuring point and each load measuring point are measured and recorded successively. Meanwhile, carefully observing the test piece until reaching a preset load such as a design load, a use load and the like or a preset experimental state such as a state that the experimental piece is damaged or deformed too much to continue the experiment;
the actual experiment may be repeated several times. And finally, inspecting the experimental part, carefully inspecting the residual deformation and damage condition of the experimental part, and performing data processing and error analysis on the recorded data such as displacement, strain, load and the like to obtain a scientific experimental conclusion.
Preferably, through suspension structure simulation unmanned aerial vehicle suspension, carrying out the pressure boost through pressure boost structure, carrying out the static experiment of second time to the unmanned aerial vehicle organism, the experimental mode is as above.
Advantageous effects
Compared with the prior art, the invention has the beneficial effects that: the unmanned aerial vehicle body is controlled to ascend and descend through the lifting structure to simulate the ascending and descending of the unmanned aerial vehicle, in the process, the pressurization is carried out through the pressurization structure, the first static experiment is carried out on the unmanned aerial vehicle body, the suspension of the unmanned aerial vehicle is simulated through the suspension structure, then the pressurization is carried out through the pressurization structure, and the second static experiment is carried out on the unmanned aerial vehicle body.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a lift control structure according to the present invention;
FIG. 3 is a schematic diagram of a first driving structure and a repeating structure according to the present invention;
fig. 4 is a schematic view of the suspension structure of the present invention.
In the figure: 1. an unmanned aerial vehicle body; 2. a lifting structure; 21. a lifting platform; 22. a first electric telescopic rod; 23. a placement groove; 24. a first fixed structure; 241. a first fixing plate; 242. a second electric telescopic rod; 243. a first support plate; 244. a second fixing plate; 25. a first drive structure; 251. a second support plate; 252. a third electric telescopic rod; 253. a drive block; 254. a first extrusion block; 255. extruding the column; 3. a suspended structure; 31. a support block; 32. a sector plate; 33. a fourth electric telescopic rod; 34. a fourth support plate; 35. a second drive structure; 351. a moving block; 352. a second extrusion block; 353. a fifth electric telescopic rod; 4. a pressurizing structure; 5. repeating the structure; 51. a third support plate; 52. a first spring.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the invention without making creative efforts, shall fall within the protection scope of the invention.
In an embodiment, referring to fig. 1-4, the present invention provides a technical solution: the static test device and method for the fixed-wing unmanned aerial vehicle body comprise an unmanned aerial vehicle body 1, a lifting structure 2 is detachably mounted at the bottom of the unmanned aerial vehicle body 1, a suspension structure 3 is detachably mounted at the top of the unmanned aerial vehicle body 1, supercharging structures 4 are symmetrically mounted on two sides of the unmanned aerial vehicle body 1, and the supercharging structures 4 are mounted on a support frame. The pressurizing structure 4 is an automatic closed loop coordinated loading system of an electric hydraulic servo system controlled by an electronic computer in the prior art, and is provided with hundreds of loaders, hundreds of loading points, hundreds of measuring channels and thousands of strain gauges, and data acquisition and processing are carried out by the electronic computer.
In an embodiment, referring to fig. 2, the lifting structure 2 includes a lifting platform 21, first electric telescopic rods 22 are symmetrically and fixedly installed at the bottom center of the lifting platform 21, placing grooves 23 are symmetrically formed at the top of the lifting platform 21, first fixing structures 24 are symmetrically formed at the top of the lifting platform 21, and a first driving structure 25 is arranged in the middle of each of the two first fixing structures 24.
In an embodiment, referring to fig. 2, the first fixing structure 24 includes a first fixing plate 241, the first fixing plate 241 is slidably mounted on one side of the placing groove 23, one side of the first fixing plate 241 is fixedly mounted with one end of a second electric telescopic rod 242, the other end of the second electric telescopic rod 242 is fixedly mounted with a first supporting plate 243, the first supporting plate 243 is fixedly mounted on one side of the top of the lifting platform 21, and the other side of the placing groove 23 is slidably mounted with a second fixing plate 244.
In an embodiment, referring to fig. 3, the first driving structure 25 includes a second supporting plate 251, the second supporting plate 251 is fixedly installed at one side of the top of the lifting table 21, one side of the second supporting plate 251 is symmetrically installed with one end of a third electric telescopic rod 252, the other end of each third electric telescopic rod 252 is fixedly installed with a driving block 253, two sides of the driving block 253 are slidably installed with first extruding blocks 254, one side of each first extruding block 254 is fixedly installed with one end of an extruding column 255, the other end of each extruding column 255 is fixedly connected to the second fixing plate 244, and the upper and lower first extruding blocks 254 are fixedly connected through supporting columns.
In an embodiment, referring to fig. 3, a repeating structure 5 is fixedly installed at the top of the first driving structure 25, the repeating structure 5 includes a third support plate 51, the third support plate 51 is fixedly installed at the top of the first pressing block 254, one side of the third support plate 51 is fixedly installed at one end of a first spring 52, the other end of the first spring 52 is fixedly connected to another third support plate 51, the repeating structure 5 is fixedly installed at the bottom of another first driving structure 25, and the repeating structure 5 is installed inside the lifting platform 21.
In an embodiment, referring to fig. 4, the suspension structure 3 includes a supporting block 31, a sector plate 32 is symmetrically and slidably installed at the bottom of the supporting block 31, one end of a fourth electric telescopic rod 33 is symmetrically and fixedly installed at two sides of the supporting block 31, a fourth supporting plate 34 is fixedly installed at the other end of the fourth electric telescopic rod 33, the fourth supporting plate 34 is C-shaped, one end of the fourth supporting plate 34 is fixedly connected to the sector plate 32, and a second driving structure 35 is disposed at the top of the supporting block 31.
In an embodiment, referring to fig. 4, the second driving structure 35 includes a moving block 351, the moving block 351 is trapezoidal, the moving block 351 is fixedly installed at the top of the supporting block 31, second squeezing blocks 352 are symmetrically and slidably installed at two sides of the moving block 351, one side of each second squeezing block 352 is fixedly installed at one end of a fifth electric telescopic rod 353, and the other end of each fifth electric telescopic rod 353 is fixedly installed at the top of one side of the supporting frame.
The embodiment, through the lift of elevation structure control unmanned aerial vehicle body, carry out the pressure boost through the pressure boost structure at this in-process, carry out the first static experiment to the unmanned aerial vehicle organism this moment, the experimental stage in advance. Gradually and slowly adding a small load according to a certain program, observing and monitoring displacement and strain measurement points, finding out the basic trend of the bearing capacity and deformation of the structure, and checking the reliability of experimental parts, a support system, a loading device and measuring equipment;
and (5) a formal test stage. And (3) taking 5-10% of the predicted load as an initial load, measuring initial stress, strain and displacement, loading step by step, uniformly and slowly according to a certain program, and measuring and recording data of each strain measuring point, each displacement measuring point and each load measuring point. Meanwhile, carefully observing the test piece until reaching a preset load such as a design load, a use load and the like or a preset experimental state such as a state that the experimental piece is damaged or deformed too much to continue the experiment;
the actual experiment may be repeated several times. And finally, inspecting the experimental part, carefully inspecting the residual deformation and damage condition of the experimental part, and performing data processing and error analysis on the recorded data such as displacement, strain, load and the like to obtain a scientific experimental conclusion.
Then through suspension structure simulation unmanned aerial vehicle suspension, carrying out the pressure boost through pressure boost structure, carry out static experiment for the second time to the unmanned aerial vehicle organism, the experimental mode is as above.
The working principle is as follows: according to the invention, an unmanned aerial vehicle is placed in the placing groove 23 on the lifting platform 21, then the second electric telescopic rod 242 is controlled to operate, the first fixing plate 241 is pushed, the third electric telescopic rod 252 is controlled at the same time, the driving block 253 moves, the first extrusion block 254 moves towards two sides, the second fixing plate 244 moves through the extrusion column 255, the unmanned aerial vehicle is fixed through the matching of the first fixing plate 241 and the second fixing plate 244, then the first electric telescopic rod 22 is controlled, the unmanned aerial vehicle is controlled to move up and down, at the moment, the pressurizing structure 4 is controlled to pressurize, and a first static experiment is carried out;
let unmanned aerial vehicle open, control the operation of fourth electric telescopic handle 33, drive sector plate 32 through fourth backup pad 34, fix unmanned aerial vehicle, then control the operation of fifth electric telescopic handle 353, and then extrude movable block 351 through second extrusion piece 352, drive supporting shoe 31 and reciprocate, and then drive unmanned aerial vehicle and suspend, control pressure intensifying structure 4 at this moment and carry out the pressure boost, carry out the static experiment of second time.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention.
Claims (9)
1. The utility model provides a fixed wing unmanned aerial vehicle organism static test device, includes unmanned aerial vehicle body (1), its characterized in that: the unmanned aerial vehicle comprises an unmanned aerial vehicle body (1), a bottom detachable mounting lifting structure (2), a top detachable mounting suspension structure (3) of the unmanned aerial vehicle body (1), a bilateral symmetry mounting supercharging structure (4) of the unmanned aerial vehicle body (1), and the supercharging structure (4) is mounted on a support frame.
2. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 1, wherein: the lifting structure (2) comprises a lifting platform (21), wherein first electric telescopic rods (22) are fixedly installed at the bottom of the lifting platform (21) in a centrosymmetric mode, placing grooves (23) are symmetrically formed in the top of the lifting platform (21), first fixing structures (24) are symmetrically formed in the top of the lifting platform (21), and a first driving structure (25) is arranged in the middle of each first fixing structure (24).
3. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 2, is characterized in that: the first fixing structure (24) comprises a first fixing plate (241), the first fixing plate (241) is slidably mounted on one side of the placing groove (23), one side of the first fixing plate (241) is fixedly provided with one end of a second electric telescopic rod (242), the other end of the second electric telescopic rod (242) is fixedly provided with a first supporting plate (243), the first supporting plate (243) is fixedly mounted on one side of the top of the lifting platform (21), and the other side of the placing groove (23) is slidably provided with a second fixing plate (244).
4. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 3, wherein: the first driving structure (25) comprises a second supporting plate (251), the second supporting plate (251) is fixedly installed on one side of the top of the lifting table (21), one side of the second supporting plate (251) is symmetrically provided with one end of a third electric telescopic rod (252), the other end of each third electric telescopic rod (252) is fixedly provided with a driving block (253), two sides of each driving block (253) are slidably provided with first extrusion blocks (254), one side of each first extrusion block (254) is fixedly provided with one end of an extrusion column (255), and the other end of each extrusion column (255) is fixedly connected with the second fixing plate (244).
5. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 4, wherein: the top of the first driving structure (25) is fixedly provided with a repeating structure (5), the repeating structure (5) comprises a third supporting plate (51), the third supporting plate (51) is fixedly arranged at the top of the first extrusion block (254), one end of a first spring (52) is fixedly arranged on one side of the third supporting plate (51), and the other end of the first spring (52) is fixedly connected with the other third supporting plate (51).
6. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 1, wherein: the suspension structure (3) comprises a supporting block (31), sector plates (32) are symmetrically and slidably mounted at the bottom of the supporting block (31), one ends of fourth electric telescopic rods (33) are symmetrically and fixedly mounted at two sides of the supporting block (31), a fourth supporting plate (34) is fixedly mounted at the other end of each fourth electric telescopic rod (33), the fourth supporting plate (34) is C-shaped, one end of each fourth supporting plate (34) is fixedly connected with the sector plates (32), and a second driving structure (35) is arranged at the top of the supporting block (31).
7. The static test device for the fixed-wing unmanned aerial vehicle body according to claim 6, wherein: the second driving structure (35) comprises a moving block (351), the moving block (351) is trapezoidal, the moving block (351) is fixedly installed at the top of the supporting block (31), second squeezing blocks (352) are symmetrically and slidably installed on two sides of the moving block (351), one side of each second squeezing block (352) is fixedly installed at one end of a fifth electric telescopic rod (353), and the other end of each fifth electric telescopic rod (353) is fixedly installed at the top of one side of the supporting frame.
8. The static test method for the body of the fixed-wing unmanned aerial vehicle as claimed in claim 1, wherein the lifting of the unmanned aerial vehicle body is controlled by a lifting structure, pressurization is performed by a pressurization structure in the process, at the moment, a first static test is performed on the unmanned aerial vehicle body, in a pre-test stage, a small load is slowly added step by step according to a certain program, displacement and strain measurement points are observed and monitored, the basic trend of the bearing capacity and deformation of the structure is found, and the reliability of the test piece, the support system, the loading device and the measurement equipment is tested;
in the formal test stage, firstly, taking 5-10% of the predicted load as an initial load, measuring initial stress, strain and displacement, then, loading step by step, uniformly and slowly according to a certain program, and measuring and recording data of each strain measuring point, each displacement measuring point and each load measuring point successively, and meanwhile, carefully observing the test piece until a preset load (such as a design load, a use load and the like) or a preset experimental state (such as a state that the experimental piece is damaged or deforms too much to continue the experiment) is reached;
and the formal experiment is repeated for many times, and finally, the experimental part is inspected, the residual deformation and the damage condition of the experimental part are carefully inspected, and data processing and error analysis are carried out on the recorded data such as displacement, strain, load and the like so as to obtain a scientific experimental conclusion.
9. The static test method for the fixed-wing unmanned aerial vehicle body according to claim 1, characterized in that: through suspension structure simulation unmanned aerial vehicle suspension, carrying out the pressure boost through pressure boost structure, carrying out the static experiment of second time to the unmanned aerial vehicle organism, the experimental mode is as above.
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| CN211527791U (en) * | 2019-11-13 | 2020-09-18 | 彩虹无人机科技有限公司 | Small and medium-sized fixed wing static test device |
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| CN104677744A (en) * | 2015-02-03 | 2015-06-03 | 中国航天科工集团第六研究院四十一所 | Static loading test device for missile wing |
| CN106742052A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter body slow test suspension |
| KR20180082236A (en) * | 2017-01-10 | 2018-07-18 | 드로젠(주) | Drone flight test equipment |
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