CN116280254A - Unmanned aerial vehicle interference killing feature testing arrangement - Google Patents
Unmanned aerial vehicle interference killing feature testing arrangement Download PDFInfo
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- CN116280254A CN116280254A CN202310523414.1A CN202310523414A CN116280254A CN 116280254 A CN116280254 A CN 116280254A CN 202310523414 A CN202310523414 A CN 202310523414A CN 116280254 A CN116280254 A CN 116280254A
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- 238000012360 testing method Methods 0.000 title claims abstract description 40
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 238000004088 simulation Methods 0.000 claims abstract description 13
- 238000001514 detection method Methods 0.000 claims abstract description 10
- 238000004804 winding Methods 0.000 claims description 22
- 238000007789 sealing Methods 0.000 claims description 12
- 230000005389 magnetism Effects 0.000 claims description 8
- 230000006978 adaptation Effects 0.000 claims description 2
- 230000036039 immunity Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 7
- 230000007547 defect Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000012430 stability testing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 210000003437 trachea Anatomy 0.000 description 1
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses an unmanned aerial vehicle anti-interference capability testing device, and relates to the technical field of unmanned aerial vehicle testing devices; comprising the following steps: the base is provided with a plurality of supporting frames, and the supporting frames are provided with a pulling simulation mechanism; the detection module is arranged on the unmanned aerial vehicle body; wherein, the pulling simulation mechanism includes: the annular elastic bag is fixed on the outer wall of one side of the support frame. According to the invention, by arranging the plurality of pulling simulation mechanisms, the corresponding clamping parts can be clamped on the unmanned aerial vehicle body according to the test requirements, when the unmanned aerial vehicle flies, the elastic rope is gradually straightened, the unmanned aerial vehicle is further limited to fly, the unmanned aerial vehicle is pulled by the elastic rope, the flying is naturally interfered to a certain extent, the detection module can detect the flying state of the unmanned aerial vehicle, the interference on different angles of the unmanned aerial vehicle is realized through different pulling simulation mechanisms, and the purpose of testing is achieved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle testing devices, in particular to an unmanned aerial vehicle anti-interference capability testing device.
Background
At present, unmanned aerial vehicles are widely applied to various large fields, along with continuous progress of unmanned aerial vehicle technology, performance requirements of people on the unmanned aerial vehicles are higher and higher, in design and production of the unmanned aerial vehicles, various tests are usually carried out on the unmanned aerial vehicles so as to find defects in time and improve the defects, the current tests are usually only tests on the speed and stability of the normal flight state of the unmanned aerial vehicles, tests on anti-interference capability are also lacking, for example, the situation that the unmanned aerial vehicles cannot simulate contact and collision with other objects in the flight process, the fuselage is inclined, or heavy objects are wound on a part of the fuselage, the flight state is influenced, and the like; therefore, the anti-jamming capability of the unmanned aerial vehicle cannot be determined, and an anti-jamming capability testing device for the unmanned aerial vehicle is needed.
Through retrieval, the patent with the Chinese patent application number of CN201820283632.7 discloses an unmanned aerial vehicle load flight stability testing device, which comprises a measuring assembly, a counterweight drag hook, a balancing weight, a ground external terminal, an unmanned aerial vehicle drag hook and a tested unmanned aerial vehicle; the measuring assembly comprises a measuring box shell, a controller, a drag hook supporting piece, an MEMS gyroscope, a wireless module and a power supply; the measuring box shell is internally provided with a mounting frame, a controller, a drag hook supporting piece, an MEMS gyroscope, a wireless module and a power supply. The test device in the above patent has the following disadvantages: in terms of functionality, lack of testing for the drone in terms of physical interference resistance has yet to be improved.
Disclosure of Invention
The invention aims to solve the defects in the prior art, and provides an unmanned aerial vehicle anti-interference capability testing device.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
an unmanned aerial vehicle interference killing feature testing arrangement includes:
the base is provided with a plurality of supporting frames, and the supporting frames are provided with a pulling simulation mechanism;
the detection module is arranged on the unmanned aerial vehicle body;
wherein, the pulling simulation mechanism includes:
the annular elastic bag is fixed on the outer wall of one side of the support frame;
the connecting frame is fixed on one side of the annular elastic bag, which is far away from the supporting frame, and a fixed bracket is arranged on the connecting frame;
the elastic rope is arranged on the inner side of the fixed support, one end of the elastic rope is connected with the clamping part through the connecting part, and the elastic rope can be clamped and fixed on the body of the unmanned aerial vehicle through the clamping part.
Preferably: the elastic rope outside is provided with antiwind protection component, antiwind protection component includes:
the two annular seats are slidably arranged on the outer sides of the elastic ropes, and the annular seats are connected with fixing knobs for fixing the annular seats on the elastic ropes through threads;
the two ends of the elastic air columns are respectively fixed on the circumferential outer walls of the two annular seats, and the elastic air columns are uniformly circumferentially distributed.
Further: a sleeve is fixed on one side of each annular seat adjacent to each annular seat, and a plurality of balancing weights are detachably arranged on the outer sides of the sleeves; the balancing weight is located the antiwind protection subassembly inboard.
Further preferred is: the balancing weight is U-shaped structure, and annular seat one side outer wall and balancing weight one side outer wall all are provided with the reference column, and the locating hole with reference column looks adaptation has been seted up to balancing weight opposite side outer wall, and the reference column outside is provided with first annular magnetism and inhales the piece, and the locating hole outside is provided with the second annular magnetism that attracts the piece to attract mutually with first annular magnetism and inhale the piece.
As a preferred embodiment of the present invention: the clamping part comprises a fixing clamp, and anti-slip ribs which are uniformly distributed are arranged on the inner side of the fixing clamp.
Further preferred as the present invention is: the connection part includes:
the ball seat is fixed at one end of the elastic rope;
the ball head rod is rotatably arranged on the inner wall of the ball seat, and one end of the ball head rod is fixed on the fixing clamp.
As still further aspects of the invention: the outer wall of one side of the connecting frame is fixedly provided with a guide rod, the guide rod is connected to the inner wall of the supporting frame in a sliding manner, the outer side of the guide rod is connected with a limiting block in a sliding manner, and the inner wall of one side of the limiting block is connected with a first jackscrew for fixing the limiting block through threads;
the elastic rope is connected in the fixed support in a sliding manner, and a second jackscrew for fixing the elastic rope is connected to the inner wall of one side of the fixed support through threads.
Based on the scheme: an air cushion is arranged in the middle of the base.
Preferred on the basis of the foregoing scheme: the base is provided with an inflating device, and the output end of the inflating device is connected with a plug through an air pipe; the outer wall of one side of the annular elastic bag is provided with a connector matched with the plug, and one end of the connector is detachably connected with a sealing cover through threads.
Further preferred on the basis of the foregoing scheme is: the inner side of the connector is provided with a diaphragm, the diaphragm is provided with a micro slit, and the inner side of the connector is provided with a sealing ring; an annular groove matched with the sealing ring is arranged on the outer side of the plug.
The beneficial effects of the invention are as follows:
according to the invention, by arranging the plurality of pulling simulation mechanisms, the corresponding clamping parts can be clamped on the unmanned aerial vehicle body according to the test requirements, when the unmanned aerial vehicle flies, the elastic rope is gradually straightened, the unmanned aerial vehicle is further limited to fly, the unmanned aerial vehicle is pulled by the elastic rope, the flying is naturally interfered to a certain extent, the detection module can detect the flying state of the unmanned aerial vehicle, the interference on different angles of the unmanned aerial vehicle is realized through different pulling simulation mechanisms, and the purpose of testing is achieved.
According to the invention, the anti-winding protection component is arranged, so that the anti-winding protection component can be arranged at the position, close to the unmanned aerial vehicle, of the elastic rope, as the thicker elastic air column which is difficult to deform is adopted, the elastic rope can be protected, the wings of the unmanned aerial vehicle and the elastic rope are prevented from winding, and the safety is improved; the position of the annular seat is adjustable, so that the flexibility is high; in addition, the purpose of setting the fixed knob is not only to adjust the position of the annular seats, but also to adjust the length of the elastic rope between the two annular seats, thereby achieving the purpose of adjusting the whole effective length of the elastic rope and changing the interference effect on the unmanned aerial vehicle; namely, the anti-winding protection component not only plays a role in anti-winding protection, but also plays a role in adjusting interference effects.
According to the invention, through arranging the structures such as the balancing weight and the like, the whole weight of the anti-winding protection assembly can be adjusted according to the requirements, so that the purpose of adjusting the interference effect on the unmanned aerial vehicle is achieved, the practicability is improved, the balancing weight is positioned on the inner side of the anti-winding protection assembly, the direct collision between the balancing weight and the unmanned aerial vehicle can be effectively avoided, the safety and the reliability are improved, and the anti-winding protection assembly also plays a role in balancing weight and balancing weight protection.
According to the invention, the balancing weights can be conveniently and firmly spliced and installed by arranging the structures such as the positioning column, the positioning hole, the first annular magnetic attraction block, the second annular magnetic attraction block and the like, so that the practicability is improved.
According to the invention, through arranging the structures such as the inflating device and the connecting head, air can be injected into the annular elastic bag according to the requirements, so that the inflating degree of the annular elastic bag is adjusted, and the purposes of adjusting the size and the deformation difficulty of the annular elastic bag are achieved.
Drawings
Fig. 1 is a schematic structural diagram of an anti-interference capability test device for an unmanned aerial vehicle according to the present invention;
fig. 2 is a schematic structural diagram of an unmanned aerial vehicle anti-interference capability test device according to the present invention with an air cushion removed;
fig. 3 is a schematic structural diagram of a pulling simulation mechanism and an inflation device of the unmanned aerial vehicle anti-jamming capability test device provided by the invention;
fig. 4 is a schematic structural view of a connector and a sealing cover of the unmanned aerial vehicle anti-interference capability testing device according to the present invention;
FIG. 5 is an enlarged view of the invention at A in FIG. 4;
fig. 6 is a schematic structural diagram of a cross section of an annular elastic bag of an unmanned aerial vehicle anti-interference capability test device;
fig. 7 is a schematic structural diagram of a fixing clip and anti-winding protection assembly of an anti-jamming capability test device for an unmanned aerial vehicle according to the present invention;
fig. 8 is a schematic structural diagram of splitting a balancing weight of an anti-interference capability test device for an unmanned aerial vehicle.
In the figure: 1 base, 2 air cushion, 3 support frame, 4 elastic rope, 5 guide bar, 6 annular elastic bag, 7 plug, 8 trachea, 9 fixation clamp, 10 elastic air column, 11 aerating device, 12 ball seat, 13 first jackscrew, 14 stopper, 15 link, 16 fixed bolster, 17 ring channel, 18 sealed lid, 19 sealing washer, 20 diaphragm, 21 micro-gap, 22 connector, 23 second jackscrew, 24 anti-slip rib, 25 fixed knob, 26 annular seat, 27 balancing weight, 28 ball head pole, 29 reference column, 30 second annular magnetic attraction piece, 31 locating hole, 32 sleeve pipe, 33 first annular magnetic attraction piece.
Detailed Description
The technical scheme of the patent is further described in detail below with reference to the specific embodiments.
Embodiments of the present patent are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present patent and are not to be construed as limiting the present patent.
Example 1: an unmanned aerial vehicle interference killing feature testing arrangement, as shown in fig. 1-8, includes:
the device comprises a base 1, wherein a plurality of supporting frames 3 are arranged on the base 1, and a pulling simulation mechanism is arranged on each supporting frame 3;
the detection module is not shown in the detection module diagram, is arranged on the unmanned aerial vehicle body, comprises structures such as a gyroscope and various sensors, and is mainly used for detecting the flight state of the unmanned aerial vehicle, and the specific structure of the detection module can refer to the prior art, so that the detection module is not repeated herein;
wherein, the pulling simulation mechanism includes:
the annular elastic bag 6 is fixed on the outer wall of one side of the support frame 3;
the connecting frame 15 is fixed on one side of the annular elastic bag 6 far away from the supporting frame 3, and a fixing bracket 16 is arranged on the connecting frame 15;
the elastic rope 4 is arranged on the inner side of the fixed support 16, one end of the elastic rope 4 is connected with a clamping part through a connecting part, and the elastic rope 4 can be clamped and fixed on the unmanned aerial vehicle body through the clamping part, so that when the unmanned aerial vehicle flies, the unmanned aerial vehicle body is limited by the elastic rope 4, and the interference state is simulated;
through setting up a plurality of analog mechanism that pulls, can be according to the test demand, with corresponding clamping part centre gripping on unmanned aerial vehicle fuselage, when unmanned aerial vehicle flies, elastic cord 4 is stretched straight gradually, and then restrict unmanned aerial vehicle's flight, unmanned aerial vehicle receives elastic cord 4 to pull, and the flight receives the interference of certain degree naturally, and detection module can detect unmanned aerial vehicle's flight state, pulls analog mechanism through the difference and realizes the interference to unmanned aerial vehicle different angles, reaches the purpose of test.
In order to prevent the unmanned aerial vehicle wing from being wound with the elastic rope 4 during flying; as shown in fig. 1, 7 and 8, an anti-winding protection assembly is arranged on the outer side of the elastic rope 4, and the anti-winding protection assembly comprises:
the annular seats 26, two annular seats 26 are slidably arranged outside the elastic rope 4, and the annular seats 26 are connected with a fixing knob 25 for fixing the annular seats 26 on the elastic rope 4 through threads;
the elastic air columns 10, two ends of the elastic air columns 10 are respectively fixed on the circumferential outer walls of the two annular seats 26, and a plurality of the elastic air columns 10 are uniformly circumferentially distributed;
wherein the elastic air column 10 is thicker and more difficult to deform than the elastic rope 4;
by arranging the anti-winding protection component, the anti-winding protection component can be arranged at the position of the elastic rope 4 close to the unmanned aerial vehicle, and the elastic air column 10 which is thicker and is difficult to deform is adopted, so that the elastic rope 4 can be protected, the wings of the unmanned aerial vehicle and the elastic rope 4 are prevented from winding, and the safety is improved; the position of the annular seat 26 is adjustable, so that the flexibility is high; in addition, the fixing knob 25 is provided for adjusting the positions of the annular seats 26, so that a user can also adjust the length of the elastic rope 4 between the two annular seats 26, for example, pull the elastic rope 4 to enable the part of the elastic rope 4 in the anti-winding protection component to be increased, however, the whole length of the anti-winding protection component is relatively fixed, the part of the elastic rope 4 positioned outside the anti-winding protection component is shortened, and further the effective lengths of the elastic rope 4 and the whole anti-winding protection component are shortened, thereby achieving the purpose of adjusting the whole effective length of the elastic rope 4 and changing the interference effect on the unmanned aerial vehicle; namely, the anti-winding protection component not only plays a role in anti-winding protection, but also plays a role in adjusting interference effects.
To facilitate adjustment of the interference effect; as shown in fig. 7 and 8, a sleeve 32 is fixed on the adjacent side of the two annular seats 26, and a plurality of balancing weights 27 are detachably arranged on the outer side of the sleeve 32; the balancing weight 27 is positioned on the inner side of the anti-winding protection component;
through setting up balancing weight 27 isotructure, can adjust the holistic weight of antiwind protection component according to the demand to reach the purpose of adjusting the effect of interfering unmanned aerial vehicle, promoted the practicality, and balancing weight 27 is located antiwind protection component inboard, can effectively avoid taking place direct collision with unmanned aerial vehicle between, promoted security and reliability, antiwind protection component has still played the function of counter weight and protection balancing weight 27 promptly.
For ease of installation; as shown in fig. 7 and 8, the balancing weight 27 has a U-shaped structure, the outer wall of one side of the annular seat 26 and the outer wall of one side of the balancing weight 27 are both provided with positioning posts 29, the outer wall of the other side of the balancing weight 27 is provided with positioning holes 31 adapted to the positioning posts 29, the outer side of the positioning posts 29 is provided with first annular magnetic attraction blocks 33, and the outer side of the positioning holes 31 is provided with second annular magnetic attraction blocks 30 attracted to the first annular magnetic attraction blocks 33;
through setting up the structure such as reference column 29, locating hole 31, first annular magnetism inhale piece 33 and second annular magnetism inhale piece 30, can be convenient and firm concatenation installation balancing weight 27, promoted the practicality.
For facilitating clamping and fixing; as shown in fig. 7, the clamping part comprises a fixing clamp 9, and the inner side of the fixing clamp 9 is provided with uniformly distributed anti-slip ribs 24;
by providing the anti-slip rib 24 and the like, the holding firmness can be improved.
To improve reliability; as shown in fig. 7, the connection part includes:
a ball seat 12, the ball seat 12 being fixed to one end of the bungee cord 4;
the ball head rod 28, the ball head rod 28 is rotatably arranged on the inner wall of the ball seat 12, and one end of the ball head rod 28 is fixed on the fixing clamp 9.
To improve reliability; as shown in fig. 6, a guide rod 5 is fixed on the outer wall of one side of the connecting frame 15, the guide rod 5 is slidably connected to the inner wall of the supporting frame 3, a limiting block 14 is slidably connected to the outer side of the guide rod 5, and a first jackscrew 13 for fixing the limiting block 14 is connected to the inner wall of one side of the limiting block 14 through threads;
through setting up guide bar 5, can play the effect of direction when annular elastic bag 6 deformation, stopper 14 and link 15 can play spacing effect.
To facilitate adjustment of the effective length of the bungee cord 4; as shown in fig. 6, the elastic cord 4 is slidably connected to the fixing support 16, and a second jackscrew 23 for fixing the elastic cord 4 is screwed to the inner wall of one side of the fixing support 16.
An air cushion 2 is arranged in the middle of the base 1.
Example 2: an unmanned aerial vehicle anti-jamming capability test device is shown in figures 1-5, so as to facilitate the adjustment of the state and deformation capability of an annular elastic bag 6; the present example was modified on the basis of example 1 as follows: an air charging device 11 is arranged on the base 1, and the output end of the air charging device 11 is connected with a plug 7 through an air pipe 8; the outer wall of one side of the annular elastic bag 6 is provided with a connector 22 matched with the plug 7, and one end of the connector 22 is detachably connected with a sealing cover 18 through threads;
by arranging the structures such as the inflation device 11, the connector 22 and the like, the air can be injected into the annular elastic bag 6 according to the requirements, so that the inflation degree of the annular elastic bag 6 is adjusted, and the purposes of adjusting the size and the deformation difficulty of the annular elastic bag 6 are achieved; the elastic cord 4 may be replaced with a non-elastic cord due to the provision of the deformable annular elastic bladder 6.
As shown in fig. 5, a diaphragm 20 is arranged at the inner side of the connector 22, a micro slit 21 is arranged on the diaphragm 20, and a sealing ring 19 is arranged at the inner side of the connector 22; an annular groove 17 matched with the sealing ring 19 is arranged on the outer side of the plug 7;
when the plug 7 is inserted into the connector 22, the plug 7 passes through the diaphragm 20 through the micro-slit 21 so as to be communicated with the inside of the annular elastic bag 6, and at the moment, the sealing ring 19 is clamped in the annular groove 17, so that the functions of reinforcing connection and improving tightness are achieved.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (10)
1. Unmanned aerial vehicle interference killing feature testing arrangement, its characterized in that includes:
the device comprises a base (1), wherein a plurality of supporting frames (3) are arranged on the base (1), and a pulling simulation mechanism is arranged on each supporting frame (3);
the detection module is arranged on the unmanned aerial vehicle body;
wherein, the pulling simulation mechanism includes:
the annular elastic bag (6) is fixed on the outer wall of one side of the supporting frame (3);
the connecting frame (15), the connecting frame (15) is fixed on one side of the annular elastic bag (6) far away from the supporting frame (3), and the connecting frame (15) is provided with a fixed bracket (16);
the elastic rope (4), the elastic rope (4) is installed in the inboard of fixed bolster (16), and elastic rope (4) one end is connected with clamping part through connecting portion, and elastic rope (4) accessible clamping part centre gripping is fixed in on unmanned aerial vehicle's the fuselage.
2. The unmanned aerial vehicle antijamming capability test device according to claim 1, wherein the elastic rope (4) is provided with an antiwind protection assembly outside, the antiwind protection assembly comprising:
the annular seats (26) are slidably arranged on the outer sides of the elastic ropes (4), and the annular seats (26) are connected with fixing knobs (25) for fixing the annular seats (26) on the elastic ropes (4) through threads;
the elastic air columns (10), the two ends of the elastic air columns (10) are respectively fixed on the circumferential outer walls of the two annular seats (26), and the elastic air columns (10) are uniformly circumferentially distributed.
3. The unmanned aerial vehicle anti-interference capability testing device according to claim 2, wherein a sleeve (32) is fixed on one side of each of the two annular seats (26), and a plurality of balancing weights (27) are detachably arranged on the outer side of the sleeve (32); the balancing weight (27) is positioned on the inner side of the anti-winding protection component.
4. The unmanned aerial vehicle interference killing feature testing arrangement according to claim 3, wherein, balancing weight (27) are U-shaped structure, and annular seat (26) one side outer wall and balancing weight (27) one side outer wall all are provided with reference column (29), and locating hole (31) with reference column (29) looks adaptation are seted up to balancing weight (27) opposite side outer wall, are provided with first annular magnetism and inhale piece (33) in reference column (29) outside, are provided with second annular magnetism that attracts piece (30) that attracts with first annular magnetism and inhale piece (33) in reference hole (31) outside.
5. The unmanned aerial vehicle antijamming capability test device according to claim 4, wherein the clamping part comprises a fixing clamp (9), and anti-slip ribs (24) which are uniformly distributed are arranged on the inner side of the fixing clamp (9).
6. The unmanned aerial vehicle interference immunity testing device of claim 5, wherein the connection comprises:
the ball seat (12), the ball seat (12) is fixed on one end of the elastic rope (4);
the ball head rod (28) is rotatably arranged on the inner wall of the ball seat (12), and one end of the ball head rod (28) is fixed on the fixing clamp (9).
7. The unmanned aerial vehicle anti-interference capability testing device according to claim 1, wherein a guide rod (5) is fixed on the outer wall of one side of the connecting frame (15), the guide rod (5) is slidably connected to the inner wall of the supporting frame (3), a limiting block (14) is slidably connected to the outer side of the guide rod (5), and a first jackscrew (13) for fixing the limiting block (14) is connected to the inner wall of one side of the limiting block (14) through threads;
the elastic rope (4) is slidably connected in the fixed support (16), and a second jackscrew (23) for fixing the elastic rope (4) is connected to the inner wall of one side of the fixed support (16) through threads.
8. The unmanned aerial vehicle antijamming capability test device according to claim 1, wherein an air cushion (2) is arranged in the middle of the base (1).
9. The unmanned aerial vehicle anti-interference capability test device according to any one of claims 1 to 8, wherein an air charging device (11) is arranged on the base (1), and the output end of the air charging device (11) is connected with a plug (7) through an air pipe (8); the outer wall of one side of the annular elastic bag (6) is provided with a connector (22) matched with the plug (7), and one end of the connector (22) is detachably connected with a sealing cover (18) through threads.
10. The unmanned aerial vehicle anti-interference capability testing device according to claim 9, wherein a diaphragm (20) is arranged on the inner side of the connector (22), a micro slit (21) is arranged on the diaphragm (20), and a sealing ring (19) is arranged on the inner side of the connector (22); an annular groove (17) matched with the sealing ring (19) is arranged on the outer side of the plug (7).
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20030056405A (en) * | 2001-12-28 | 2003-07-04 | 한국항공우주연구원 | Airship Envelop Components Testing Machine |
| CN106864768A (en) * | 2017-03-31 | 2017-06-20 | 天津中德应用技术大学 | VUAV four-way motion and test flight training system |
| CN108415442A (en) * | 2018-01-23 | 2018-08-17 | 歌尔股份有限公司 | Unmanned plane adjusts test device |
| CN207908036U (en) * | 2018-02-28 | 2018-09-25 | 成都市国科泰达科技有限公司 | A kind of unmanned plane load-carrying is had a smooth flight system safety testing device |
| CN210822823U (en) * | 2019-09-07 | 2020-06-23 | 成都信息工程大学 | Multi-freedom-degree miniature four-rotor aircraft mounting and debugging support |
| CN214190165U (en) * | 2020-12-11 | 2021-09-14 | 中国特种飞行器研究所 | Many rotor unmanned aerial vehicle testing arrangement |
| CN214793834U (en) * | 2021-05-26 | 2021-11-19 | 中国航空工业集团公司西安飞机设计研究所 | Elastic supporting device for small airplane modal test |
| KR102382888B1 (en) * | 2021-07-07 | 2022-04-08 | 주식회사 에프엠케이 | Flying performance testing apparatus for drone |
| CN216783894U (en) * | 2021-11-09 | 2022-06-21 | 中国人民解放军陆军装甲兵学院 | Unmanned aerial vehicle stability capability test device |
| CN114671048A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Aircraft wing static force and vibration combined loading system and method for aircraft strength test |
| CN115196040A (en) * | 2022-07-25 | 2022-10-18 | 中国航空工业集团公司哈尔滨空气动力研究所 | Support interference flexibility measuring device of opening large-attack-angle test system |
| CN218142218U (en) * | 2022-06-21 | 2022-12-27 | 拓攻（南京）机器人有限公司 | Aircraft performance detection platform |
-
2023
- 2023-05-10 CN CN202310523414.1A patent/CN116280254B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20030056405A (en) * | 2001-12-28 | 2003-07-04 | 한국항공우주연구원 | Airship Envelop Components Testing Machine |
| CN106864768A (en) * | 2017-03-31 | 2017-06-20 | 天津中德应用技术大学 | VUAV four-way motion and test flight training system |
| CN108415442A (en) * | 2018-01-23 | 2018-08-17 | 歌尔股份有限公司 | Unmanned plane adjusts test device |
| CN207908036U (en) * | 2018-02-28 | 2018-09-25 | 成都市国科泰达科技有限公司 | A kind of unmanned plane load-carrying is had a smooth flight system safety testing device |
| CN210822823U (en) * | 2019-09-07 | 2020-06-23 | 成都信息工程大学 | Multi-freedom-degree miniature four-rotor aircraft mounting and debugging support |
| CN214190165U (en) * | 2020-12-11 | 2021-09-14 | 中国特种飞行器研究所 | Many rotor unmanned aerial vehicle testing arrangement |
| CN214793834U (en) * | 2021-05-26 | 2021-11-19 | 中国航空工业集团公司西安飞机设计研究所 | Elastic supporting device for small airplane modal test |
| KR102382888B1 (en) * | 2021-07-07 | 2022-04-08 | 주식회사 에프엠케이 | Flying performance testing apparatus for drone |
| CN216783894U (en) * | 2021-11-09 | 2022-06-21 | 中国人民解放军陆军装甲兵学院 | Unmanned aerial vehicle stability capability test device |
| CN114671048A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Aircraft wing static force and vibration combined loading system and method for aircraft strength test |
| CN218142218U (en) * | 2022-06-21 | 2022-12-27 | 拓攻（南京）机器人有限公司 | Aircraft performance detection platform |
| CN115196040A (en) * | 2022-07-25 | 2022-10-18 | 中国航空工业集团公司哈尔滨空气动力研究所 | Support interference flexibility measuring device of opening large-attack-angle test system |
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