Multifunctional aircraft test platform

Abstract

The invention relates to the technical field of aircraft testing, in particular to a multifunctional aircraft testing platform which comprises a main body plate, a wind tunnel mechanism is arranged on the upper side of the main body plate, a restraining mechanism is arranged at the position, corresponding to the interior of the wind tunnel mechanism, of the upper side of the main body plate, and a driving mechanism is arranged in the main body plate; a drainage groove and a diversion groove are formed in the air guide barrel, an air outlet hole and an air guide hole are formed in the side face of the air guide barrel, a support rod is fixedly installed on the lower side of the air guide barrel, and a first inner cavity and a second inner cavity are formed in the main body plate. The wind tunnel mechanism, the constraint mechanism and the driving mechanism are arranged, the one-machine multi-testing function can be achieved, multi-direction wind tunnel combined testing can be conducted on an aircraft, dynamic swing parameter detection can be conducted on the aircraft in the testing process, constraint landing protection can be generated in the aircraft testing process, and in addition, due to the driving integrated design, the equipment integration size is small, and the reliability is high. And the occupied space is saved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft testing, and particularly to a multi-functional aircraft testing platform. Background Art

[0002] With the rapid development of unmanned aerial vehicle technology, the demand for performance testing of aircraft has increased day by day, especially the testing of key indicators such as wind resistance, flight stability, and landing safety. Traditional testing methods usually use a single wind tunnel or fixed restraint devices, and there are the following problems:

[0003] 1. Single wind direction simulation: Most existing wind tunnels have unidirectional or fixed multi-directional airflows, and cannot flexibly combine wind forces in different directions, making it difficult to simulate complex natural wind field environments;

[0004] 2. Separation of restraint and detection: Most testing platforms use rigid restraints and cannot detect the swing amplitude and direction of the aircraft after being affected by wind forces in real time, resulting in inaccurate data feedback;

[0005] 3. Lack of landing protection: Most platforms lack a buffer protection mechanism for the out-of-control landing of the aircraft, which is likely to cause equipment damage; for this reason, we propose a multi-functional aircraft testing platform. Summary of the Invention

[0006] In order to overcome the technical problems existing in the above-mentioned prior art, the present invention provides a multi-functional aircraft testing platform.

[0007] To solve the above technical problems, the present invention provides the following technical solutions: including a main body plate, a wind tunnel mechanism is arranged on the upper side of the main body plate, a restraint mechanism is arranged at a position corresponding to the inside of the wind tunnel mechanism on the upper side of the main body plate, and a driving mechanism is arranged inside the main body plate;

[0008] The wind tunnel mechanism includes a wind guide cylinder, a diversion groove and a shunt groove are opened inside the wind guide cylinder, an air outlet hole and a wind guide hole are opened on its side surface, a support rod is fixedly installed on the lower side of the wind guide cylinder, a first inner cavity and a second inner cavity are respectively opened inside the main body plate, a first adjusting plate and a second adjusting plate are respectively movably installed inside the first inner cavity and the second inner cavity, a first slot and a first fitting hole are opened on the side surface of the first adjusting plate, a second slot and a second fitting hole are opened on the side surface of the second adjusting plate, a fitting plate is arranged on the upper side of the main body plate, and a fitting pipe is fixedly installed through the side surface of the fitting plate;

[0009] The restraint mechanism includes a third inner cavity and a sliding groove, a movable plate is movably installed inside the third inner cavity, a slider is movably installed inside the sliding groove, a fitting cavity is opened on the upper side of the slider, a rotating block is arranged on the bottom wall of the fitting cavity, a connecting rod is fixedly installed on the side surface of the rotating block, and a support spring and a detection block are arranged on the side surface of the connecting rod;

[0010] The driving mechanism includes a linkage rod. A first motor and a second motor are respectively arranged on the upper and lower sides of the linkage rod. A mounting rod is movably installed inside the linkage rod. A trigger block is movably sleeved on the side of the mounting rod. A pressing block and a supporting block are arranged on the side of the trigger block.

[0011] Further, the air guide cylinder is arranged on the upper side of the main body plate and is vertically arranged at the center position of the main body plate. The air guide cylinder is a hollow regular octagon cylinder. Drainage grooves are horizontally and equidistantly opened inside the air guide cylinder. Shunt grooves are vertically and equidistantly opened on the top wall of the drainage grooves. Air outlet holes are equidistantly opened on the wall surfaces of the shunt grooves. The positions of the air guide holes are staggered with the positions of the shunt grooves.

[0012] Further, a linkage cavity is opened in the main body plate corresponding to the positions below the first inner cavity and the second inner cavity. A connection cavity is opened inside the support rod and it respectively penetrates through the air guide cylinder and the main body plate to the inside positions of the drainage groove, the first inner cavity, the second inner cavity, and the linkage cavity. Connection pipes are symmetrically arranged on the lower side of the main body plate and penetrate through it to the inside position of the linkage cavity. A first adjusting plate is movably installed inside the first inner cavity. The first matching holes are distributed in a binary distribution with six equal parts between the first slots.

[0013] Further, a second adjusting plate is movably installed inside the second inner cavity. The second matching holes are distributed in a binary distribution with eight equal parts between the second slots.

[0014] Further, through holes penetrating to its inside are equidistantly opened on the top wall of the matching plate. A matching pipe penetrates through the support rod to the inside of the connection cavity.

[0015] Further, a third inner cavity is opened in the main body plate. Sliding grooves are equidistantly opened on the top wall of the third inner cavity and penetrate through the main body plate. Guide grooves are circumferentially and equidistantly opened on the side of the movable plate corresponding to the positions of the sliding grooves. Sliding blocks are movably arranged inside the guide grooves. Rotating blocks are rotatably installed inside the sliding blocks. Connecting rods extend out of the inside of the matching cavity. Supporting springs are equidistantly fixedly installed on the side of the connecting rods. Detection blocks are fixedly connected to the other ends of the supporting springs and are fixedly installed at the inner wall position of the matching cavity.

[0016] Further, a restraint frame is fixedly installed on the upper side of the connecting rod. A limiting block is arranged on the upper side of the limiting block. A buffer block is fixedly installed on the lower side of the limiting block and is arranged inside the restraint frame.

[0017] Furthermore, the linkage rod is arranged on the side of the main body plate and penetrates through the main body plate to be located at the central positions of the movable plate, the first adjusting plate, and the second adjusting plate. The first motor is fixedly installed on the lower side of the linkage rod, and the second motor is fixedly installed on the upper side of the mounting rod. Activity slots penetrating through it are equidistantly arranged in a circumferential array corresponding to the positions of the first adjusting plate, the second adjusting plate, and the movable plate on the inner side of the linkage rod. The pressing blocks are movably installed inside the activity slots, the supporting blocks are fixedly connected between the side surfaces of the pressing blocks and the wall surfaces of the activity slots, and the three trigger blocks are staggered with an offset angle of forty degrees respectively.

[0018] Compared with the prior art, the beneficial effects that the present invention can achieve are:

[0019] 1. By setting the wind tunnel mechanism, the constraint mechanism, and the driving mechanism, the present invention can realize the function of multi-testing with one machine, enabling multi-directional wind tunnel combined testing of the aircraft. During the test, the dynamic detection swing parameters of the aircraft are measured, and at the same time, constraint landing protection is provided during the aircraft test. In addition, the integrated driving design makes the integrated volume of the equipment smaller, saving floor space.

[0020] 2. By setting the wind tunnel mechanism, through the binary hole position design of the first adjusting plate and the second adjusting plate, and in cooperation with the octagonal drainage structure of the air guide cylinder, the simulation of eight-direction airflows in a single direction or in pairs (such as the combination of northwest and north winds) is realized, covering the test requirements of the full-angle wind field and solving the problem of complex wind direction simulation.

[0021] 3. By setting the cooperation plate and its peripheral components, the buffer airflows are ejected from the openings of the cooperation plate, forming a soft landing protection with the buffer blocks of the constraint frame, reducing the impact damage during the out-of-control or test landing of the aircraft. At the same time, it can also be used for the airflow resistance blowing operation during the landing test of the aircraft.

[0022] 4. By setting the constraint mechanism, the rotation of the movable plate drives the slider to slide along the guiding groove, synchronously adjusting the spacing of the four constraint frames to adapt to aircraft with different wingspans. The limit blocks can be disassembled for quick clamping, realizing the adaptive size adjustment for aircraft of different sizes.

[0023] 5. By setting the connecting rod and its peripheral components, in the constraint mechanism, the connecting rod is linked with the detection block through the rotating block. When the aircraft is deflected by the wind force, the deformation pressure of the supporting spring real-time feedbacks the swing direction and amplitude, improving the data accuracy.

[0024] 6. By setting the driving mechanism, the linkage rod is embedded with the mounting rod and the trigger block. Through the coordinated control of the first motor and the second motor, the movable plate or the adjusting plate is selectively driven, reducing the space occupied by the mechanism.

[0025] 7. Through the hierarchical diversion structure of the diversion slots and the air outlet holes, the present invention enables the uniform distribution of the airflows, avoiding local turbulence from interfering with the test results and realizing the efficient distribution of the airflows. Brief Description of the Drawings

[0026] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 is a schematic diagram of the sectional structure of the present invention;

[0028] Figure 3 is a schematic diagram of the partial sectional structure of the present invention;

[0029] Figure 4 is a schematic diagram of the sectional structure of the air guide tube of the present invention;

[0030] Figure 5 is a schematic diagram of the partial structure of the first adjusting plate of the present invention;

[0031] Figure 6 is a schematic diagram of the partial structure of the second adjusting plate of the present invention;

[0032] Figure 7 is a schematic diagram of the partial structure of the wind tunnel mechanism of the present invention;

[0033] Figure 8 is a schematic diagram of the partial structure of the restraint mechanism of the present invention;

[0034] Figure 9 is an exploded schematic diagram of the partial structure of the restraint mechanism of the present invention;

[0035] Figure 10 of the present invention Figure 2 is an enlarged schematic diagram of part A;

[0036] Figure 11 is an exploded schematic diagram of the partial structure of the driving mechanism of the present invention;

[0037] Figure 12 of the present invention Figure 2 is an enlarged schematic diagram of part B.

[0038] Among them: 1. Main body board; 2. Wind tunnel mechanism; 21. Air guide cylinder; 211. Drainage groove; 212. Shunt groove; 213. Air outlet hole; 214. Air guide hole; 22. Support rod; 221. Connection cavity; 23. First inner cavity; 231. First adjusting plate; 232. First slotted opening; 233. First mating hole; 24. Second inner cavity; 241. Second adjusting plate; 242. Second slotted opening; 243. Second mating hole; 25. Linkage cavity; 26. Connecting pipe; 27. Fitting plate; 271. Opening; 272. Fitting pipe; 3. Constraint mechanism; 31. Third inner cavity; 311. Movable plate; 312. Guide groove; 32. Slide groove; 321. Slide block; 322. Fitting cavity; 323. Rotating block; 324. Connecting rod; 325. Support spring; 326. Detection block; 33. Constraint frame; 34. Limit block; 35. Buffer block; 4. Driving mechanism; 41. Linkage rod; 42. First motor; 43. Mounting rod; 44. Second motor; 45. Movable groove; 46. Pressing block; 47. Support block; 48. Trigger block. Specific embodiments

[0039] In order to make the technical means, creative features, achieved purposes and effects of the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments. However, the following embodiments are only the preferred embodiments of the present invention, not all of them. Based on the embodiments in the implementation manners, other embodiments obtained by those skilled in the art without creative labor all belong to the protection scope of the present invention. The experimental methods in the following embodiments are all conventional methods unless otherwise specified. The materials, reagents, etc. used in the following embodiments can all be obtained from commercial channels unless otherwise specified.

[0040] Embodiment: As Figure 1 and Figure 2 shown, a multifunctional aircraft test platform includes a main body board 1. The main body board 1 is a circular board with rectangular columns arranged on the lower side. On the upper side of the main body board 1, there is a wind tunnel mechanism 2 that can perform multiple wind tunnel simulation tests. Corresponding to the internal position of the wind tunnel mechanism 2 on the upper side of the main body board 1, there is a constraint mechanism 3 that can constrain and detect the aircraft. Inside the main body board 1, there is a driving mechanism 4 that can selectively drive each mechanism;

[0041] Through the provided wind tunnel mechanism 2, corresponding different wind direction tests can be carried out on the aircraft, and landing protection can be provided for the aircraft;

[0042] As Figures 2 to 6As shown in the figure, the wind tunnel mechanism 2 includes a wind guide cylinder 21 disposed on the upper side of the main body plate 1, and the wind guide cylinder 21 is vertically disposed at the center position of the main body plate 1. The wind guide cylinder 21 is a hollow regular octagon cylinder. Inside the wind guide cylinder 21, eight groups of drainage grooves 211 are horizontally arranged at equal intervals. The drainage grooves 211 are rectangular grooves. On the top wall of the drainage grooves 211, shunt grooves 212 are vertically arranged at equal intervals. The shunt grooves 212 are rectangular grooves. On the wall surface of the shunt grooves 212, air outlet holes 213 penetrating through the wind guide cylinder 21 to its inner side are arranged at equal intervals. The air outlet holes 213 are circular holes. On the side surface of the wind guide cylinder 21, air guide holes 214 penetrating through it are arranged at equal intervals, and the positions of the air guide holes 214 are staggered with the positions of the shunt grooves 212. The air guide holes 214 are circular holes. During specific operation, the air flow in the four directions of east, south, west, and north, as well as the air flows in the four diagonal directions of southeast, northeast, southwest, and northwest, are blown to the aircraft for testing through the side surfaces of each drainage groove 211. After the air flow flows into the interior of the drainage groove 211, it then flows to the interior position of the shunt groove 212 and is discharged through the air outlet holes 213 to blow the air flow. When the air outlet holes 213 blow the air flow, the air flow is discharged from the corresponding air guide holes 214 to realize the air flow;

[0043] At the lower side of the air guide tube 21, support rods 22 are fixedly installed at equal intervals corresponding to the positions of the drainage grooves 211. The support rods 22 are cylindrical rods. Inside the main body plate 1, a first inner cavity 23 and a second inner cavity 24 are respectively formed. The first inner cavity 23 and the second inner cavity 24 are circular cavities. At the position below the first inner cavity 23 and the second inner cavity 24 inside the main body plate 1, a linkage cavity 25 is formed. The linkage cavity 25 is an annular cavity. Inside the support rod 22, a connection cavity 221 is formed, and the connection cavity 221 respectively penetrates through the air guide tube 21 and the main body plate 1 to the inside positions of the drainage groove 211, the first inner cavity 23, the second inner cavity 24, and the linkage cavity 25. The connection cavity 221 is a cylindrical cavity. At the lower side of the main body plate 1, connection pipes 26 are symmetrically arranged and penetrate through it to the inside position of the linkage cavity 25. The connection pipes 26 are connected to an external air supply module, and corresponding air blowing can be carried out. Inside the first inner cavity 23, a first adjusting plate 231 is movably installed. The first adjusting plate 231 is an annular plate with a rubber ring sleeved on its side. On the side of the first inner cavity 23 corresponding to the position of the support rod 22, eight groups of first slots 232 penetrating through it are equidistantly arranged. The first slots 232 are square holes. On the side of the first adjusting plate 231 corresponding to the position of the first slots 232, first matching holes 233 penetrating through it are arranged. The first matching holes 233 are distributed in a binary distribution in six equal parts between the first slots 232, so that when the first adjusting plate 231 rotates to different angles, two-way combined airflows can be selected in the semi-circular direction, such as combinations of northwest and north, northwest and northeast, northwest and east, etc. Inside the second inner cavity 24, a second adjusting plate 241 is movably installed. The second adjusting plate 241 is an annular plate with a rubber ring sleeved on its side. On the side of the second inner cavity 24 corresponding to the position of the support rod 22, eight groups of second slots 242 penetrating through it are equidistantly arranged. The second slots 242 are square holes. On the side of the second inner cavity 24 corresponding to the position of the second slots 242, second matching holes 243 penetrating through it are arranged. The second matching holes 243 are distributed in a binary distribution in eight equal parts between the second slots 242, so that a single-direction airflow can be selected when the second adjusting plate 241 rotates; specifically, the first adjusting plate 231 or the second adjusting plate 241 can be driven by subsequent components to rotate. When the first adjusting plate 231 rotates to a corresponding angle, the airflow inside the linkage cavity 25 can pass through the first matching holes 233, the second slots 242, and the connection cavity 221 to the inside of the drainage groove 211, flow through the diversion groove 212, and be discharged from the air outlet holes 213, so as to realize the blowing test of the airflow in one direction of the aircraft; when the second adjusting plate 241 rotates to a corresponding angle, the airflow inside the linkage cavity 25 can pass through the first slots 232, the second matching holes 243, and the connection cavity 221 to the inside of the drainage groove 211, flow through the diversion groove 212, and be discharged from the air outlet holes 213, so as to realize the blowing test of the airflow in two directions of the aircraft;

[0044] A mating plate 27 is provided on the upper side of the main body plate 1. The mating plate 27 is a circular ring plate with a hollow interior, and four rectangular grooves are provided on its side surface. A plurality of through holes 271 penetrating through to its interior are equidistantly provided on the top wall of the mating plate 27. The through holes 271 are circular holes. A plurality of mating pipes 272 are fixedly installed through the side surface of the mating plate 27 at positions corresponding to the support rods 22, and the mating pipes 272 penetrate through the support rods 22 to the inside of the connection cavity 221. The mating pipes 272 are circular pipes with electric control valves on their sides. Specifically, the external controller can control the opening and closing of the mating pipes 272, so that the air flow in the connection cavity 221 can flow through the mating pipes 272 into the interior of the mating plate 27 and be discharged from the through holes 271, blowing the bottom side of the aircraft, realizing the landing test of the bottom-side blowing aircraft. Also, when the aircraft fails and falls, the air flow can buffer the aircraft, reducing the degree of damage to the aircraft;

[0045] The restraint mechanism 3 provided can restrain the corresponding aircraft, and can detect the swing generated when the aircraft is blown by the wind, and the test installation and disassembly are also relatively convenient;

[0046] Such as Figure 2 、 Figure 3 and Figures 7 to 10As shown in the figure, the constraint mechanism 3 includes a third inner cavity 31 formed inside the main body plate 1. The third inner cavity 31 is located above the first inner cavity 23 and the second inner cavity 24. The third inner cavity 31 is a circular cavity. Four groups of sliding grooves 32 penetrating the main body plate 1 are equidistantly arranged on the top wall of the third inner cavity 31. The sliding grooves 32 are rectangular grooves. An activity plate 311 is movably installed inside the third inner cavity 31. The activity plate 311 is an annular plate with a rubber ring sleeved on the side surface. Arc-shaped guiding grooves 312 are equidistantly arranged in a circumferential array at positions corresponding to the sliding grooves 32 on the side surface of the activity plate 311. A slider 321 is movably installed inside the sliding groove 32, and the slider 321 is movably arranged inside the guiding groove 312. The slider 321 is also movably arranged inside the rectangular groove of the matching plate 27 and is constrained by it. The slider 321 is a combination of a convex-shaped block and a cylindrical block. The cylindrical block is slidably installed inside the guiding groove 312, and the convex-shaped block is slidably installed inside the sliding groove 32. A matching cavity 322 is formed on the upper side of the slider 321. The matching cavity 322 is a frustum-shaped cavity. A rotating block 323 is arranged on the bottom wall of the matching cavity 322, and the rotating block 323 is rotatably installed inside the slider 321. The rotating block 323 is a spherical block. A connecting rod 324 is fixedly installed on the side surface of the rotating block 323 and extends out of the matching cavity 322. The connecting rod 324 is a circular rod. Four groups of supporting springs 325 are fixedly installed on the side surface of the connecting rod 324 in a circumferential array at equal intervals. A detection block 326 is fixedly connected to the other end of the supporting spring 325, and the detection block 326 is fixedly installed at the inner wall position of the matching cavity 322. The detection block 326 is a pressure sensor (a micro-force sensor such as HX711 can be used); specifically, when the connecting rod 324 is stressed and swings, the rotating block 323 rotates inside the slider 321 to constrain the connecting rod 324 at the same time. The supporting spring 325 elastically supports and pulls the connecting rod 324. When the supporting spring 325 deforms, the change in the lateral pressure can be detected through the detection block 326 and fed back to the external controller, so that the swinging direction and amplitude of the connecting rod 324 can be known. In addition, the activity plate 311 is driven to rotate by subsequent components. The slider 321 slides and guides inside the guiding groove 312. At the same time, the slider 321 slides and cooperates inside the sliding groove 32, so that the slider 321 can synchronously adjust its position to adapt to different sizes of the aircraft;

[0047] A restraint frame 33 is fixedly installed on the upper side of the connecting rod 324. The restraint frame 33 is a "U"-shaped frame. A limit block 34 is arranged on the upper side of the restraint frame 33, and the limit block 34 is fixed to the side of the restraint frame 33 by screws. The limit block 34 is a rectangular block. A buffer block 35 is fixedly installed on the lower side of the limit block 34, and the buffer block 35 is arranged inside the restraint frame 33; specifically, the limit block 34 can be disassembled. After disassembly, the four sets of arms of the aircraft can be movably arranged inside the restraint frame 33, and then the limit block 34 is fixed to the side of the restraint frame 33 by screws. In this way, a four-side restraint path is provided during the aircraft test. When the aircraft test deviates, it can drive the connecting rod 324 to swing and trigger the detection of its swing direction and amplitude; the buffer block 35 provided can play a buffering role when the aircraft takes off too high, avoiding collision damage;

[0048] Through the provided drive mechanism 4, multi-state driving can be performed, making the drive module more concentrated and occupying less space;

[0049] Such as Figure 2 、 Figure 11 and Figure 12As shown in the figure, the driving mechanism 4 includes a linkage rod 41 arranged on the side of the main body plate 1, and the linkage rod 41 penetrates through the main body plate 1 and is arranged at the central positions of the movable plate 311, the first adjusting plate 231 and the second adjusting plate 241. The linkage rod 41 is a cylindrical rod with a cylindrical groove on its side wall. A first motor 42 is fixedly installed on the lower side of the linkage rod 41, and the first motor 42 is fixed to the lower side of the main body plate 1 through a bracket. A mounting rod 43 is movably installed inside the linkage rod 41. The mounting rod 43 is a cylindrical rod with an "I"-shaped cross-section. A second motor 44 is fixedly installed on the upper side of the mounting rod 43, and the second motor 44 is fixed to the upper side of the linkage rod 41 through a bracket. The second motor 44 is also arranged at the central position of the matching plate 27. Corresponding to the positions of the first adjusting plate 231, the second adjusting plate 241 and the movable plate 311 on the inner side of the linkage rod 41, movable grooves 45 penetrating through it are equidistantly arranged in a circumferential array. The movable grooves 45 are convex-shaped grooves. A pressing block 46 is movably installed inside the movable grooves 45. The pressing block 46 is a convex-shaped block made of wear-resistant rubber. Support blocks 47 are symmetrically and fixedly connected between the side surface of the pressing block 46 and the wall surface of the movable groove 45. The support blocks 47 are "W"-shaped blocks made of elastic material. Trigger blocks 48 are movably sleeved on the side surface of the mounting rod 43 at equal distances corresponding to the positions of the movable grooves 45. The three trigger blocks 48 are staggered with a 40-degree angle difference. When the mounting rod 43 drives the trigger blocks 48 to rotate, the pressing blocks 46 on the side surfaces of the first adjusting plate 231, the second adjusting plate 241 and the movable plate 311 can be respectively squeezed and triggered; specifically, the second motor 44 drives the mounting rod 43 to rotate, the mounting rod 43 drives the trigger blocks 48 to rotate synchronously, the trigger blocks 48 respectively squeeze the pressing blocks 46 on the side surfaces of the corresponding first adjusting plate 231, the second adjusting plate 241 or the movable plate 311. When the pressing blocks 46 are squeezed, the support blocks 47 are pulled and deformed to fit on the inner side positions of the first adjusting plate 231, the second adjusting plate 241 or the movable plate 311. At this time, when the first motor 42 drives the linkage rod 41 to rotate, the first adjusting plate 231, the second adjusting plate 241 or the movable plate 311 can be driven to rotate synchronously through the linkage rod 41, so that the switching drive operation of its components can be carried out. The structure is relatively concentrated and occupies a small space.

[0050] Working principle:

[0051] Before detection: In the first step, all the limit blocks 34 are disassembled and separated from the side position of the restraint frame 33. The second motor 44 drives the mounting rod 43 to rotate so that the corresponding trigger block 48 squeezes the pressing block 46 on the side surface of the movable plate 311, and the pressing block 46 fits on the inner side position of the movable plate 311. At this time, when the first motor 42 drives the linkage rod 41 to rotate, the movable plate 311 can be driven to rotate inside the third inner cavity 31. The sliding grooves 32 can slide inside the guiding grooves 312 and the sliding grooves 32 respectively to synchronously adjust the position, so that the restraint frame 33 can be driven to move to the corresponding position to adapt to unmanned aerial vehicles of different sizes.

[0052] In the second step, after setting the four sets of arm activities of the UAV aircraft at the internal position of the restraint frame 33, control the UAV to slowly land on the upper side of the mating plate 27, and then fix the limit block 34 to the side of the restraint frame 33 with screws.

[0053] During detection: In the first step, control the UAV aircraft to take off and hover. The arm drives the connecting rod 324 to swing slightly under the restraint of the restraint frame 33. The linkage rod 41 of the restraint mechanism 3 is rotationally constrained by the rotating block 323. At this time, the elastic deformation of each support spring 325 occurs, and the force received by each detection block 326 is recorded as the zero position by default.

[0054] In the second step, for the one-way wind tunnel test, the second motor 44 drives the mounting rod 43 to rotate, so that the corresponding trigger block 48 squeezes the pressure block 46 on the side of the second adjusting plate 241. The pressure block 46 fits inside the second adjusting plate 241. The first motor 42 drives the linkage rod 41 to rotate, driving the second adjusting plate 241 to rotate inside the second inner cavity 24, and is matched with the corresponding position of the connection cavity 221 through the second fitting hole 243. At this time, the first adjusting plate 231 is in the default original position, that is, the first slot 232 corresponds to the connection cavity 221 position, realizing the one-way ventilation operation in all directions. That is, the airflow supplied by the connecting pipe 26 passes through the linkage cavity 25, the first slot 232, the second fitting hole 243 and the connection cavity 221 into the drainage groove 211, and then is shunted through the shunt groove 212 and discharged from the air outlet hole 213. The one-way airflow blows the UAV aircraft, flows out from the corresponding air guiding hole 214 to complete the airflow movement. After it generates a swing, it drives each connecting rod 324 to swing under the restraint of the restraint frame 33. By recording the value through the detection block 326, the swing amplitude of the aircraft can be known.

[0055] In the third step, for the two-way wind tunnel test, the second motor 44 drives the mounting rod 43 to rotate, so that the corresponding trigger block 48 squeezes the pressure block 46 on the side of the first adjusting plate 231. The pressure block 46 fits inside the first adjusting plate 231. The first motor 42 drives the linkage rod 41 to rotate, driving the first adjusting plate 231 to rotate inside the first inner cavity 23, and is matched with the corresponding position of the connection cavity 221 through the first fitting hole 233. At this time, the second adjusting plate 241 is in the default original position, that is, the second slot 242 corresponds to the connection cavity 221 position, realizing the two-way ventilation operation in the semi-circular direction. That is, the airflow supplied by the connecting pipe 26 passes through the linkage cavity 25, the first fitting hole 233, the second slot 242 and the connection cavity 221 into the drainage groove 211, and then is shunted through the shunt groove 212 and discharged from the air outlet hole 213. The two-way airflow blows the UAV aircraft, flows out from the corresponding air guiding hole 214 to complete the airflow movement. After it generates a swing, it drives each connecting rod 324 to swing under the restraint of the restraint frame 33. By recording the value through the detection block 326, the swing amplitude of the aircraft can be known.

[0056] Fourthly, perform a wind tunnel test on the side of the UAV in the same way as above. When it is necessary to test the landing, control the UAV to perform a landing test. At this time, open the electric control valve on the side of the cooperation pipe 272, guide the internal air flow of the connection cavity 221 to the inside of the cooperation plate 27 through the cooperation pipe 272, and then discharge it from the opening 271 to generate a blowing force on the bottom side of the UAV, so that the swing amplitude generated during the landing of the UAV can be tested.

[0057] When the UAV fails and lands, the restraint frame 33 can still restrain the landing of the UAV. At the same time, controlling the air flow blown out from the opening 271 can perform a wind buffering operation on the aircraft to reduce its damage degree. In addition, when the UAV ascends too fast, the buffer block 35 can also perform a buffering operation on the arm, also reducing its damage degree.

[0058] The embodiments of the present invention have been described in detail above in conjunction with the accompanying drawings. However, the present invention is not limited to this. Various changes can be made without departing from the spirit of the present invention within the scope of knowledge possessed by those skilled in the art.

Claims

1. A multi-functional aircraft test platform, including a main board (1), a wind tunnel mechanism (2) is arranged on the upper side of the main board (1), a restraint mechanism (3) is arranged at the position corresponding to the inside of the wind tunnel mechanism (2) on the upper side of the main board (1), and a driving mechanism (4) is arranged inside the main board (1); It is characterized in that: The wind tunnel mechanism (2) includes a wind guide cylinder (21), a drainage groove (211) and a diversion groove (212) are opened inside the wind guide cylinder (21), an air outlet hole (213) and a wind guide hole (214) are opened on its side surface, a support rod (22) is fixedly installed on the lower side of the wind guide cylinder (21), a first inner cavity (23) and a second inner cavity (24) are respectively opened inside the main board (1), a first adjusting plate (231) and a second adjusting plate (241) are respectively movably installed inside the first inner cavity (23) and the second inner cavity (24), a first slot (232) and a first matching hole (233) are opened on the side surface of the first adjusting plate (231), a second slot (242) and a second matching hole (243) are opened on the side surface of the second adjusting plate (241), a matching plate (27) is arranged on the upper side of the main board (1), and a matching pipe (272) is fixedly installed through the side surface of the matching plate (27); The restraint mechanism (3) includes a third inner cavity (31) and a chute (32), a movable plate (311) is movably installed inside the third inner cavity (31), a slider (321) is movably installed inside the chute (32), a matching cavity (322) is opened on the upper side of the slider (321), a rotating block (323) is arranged on the bottom wall of the matching cavity (322), a connecting rod (324) is fixedly installed on the side surface of the rotating block (323), and a support spring (325) and a detection block (326) are arranged on the side surface of the connecting rod (324); The driving mechanism (4) includes a linkage rod (41), a first motor (42) and a second motor (44) are respectively arranged on the upper and lower sides of the linkage rod (41), a mounting rod (43) is movably installed inside the linkage rod (41), a trigger block (48) is movably sleeved on the side surface of the mounting rod (43), and a pressing block (46) and a support block (47) are arranged on the side surface of the trigger block (48).

2. The multifunctional aircraft test platform according to claim 1, characterized in that: The wind guide cylinder (21) is arranged on the upper side of the main board (1) and is vertically arranged at the center position of the main board (1). The wind guide cylinder (21) is a hollow regular octagon cylinder. The drainage grooves (211) are horizontally arranged at equal intervals inside the wind guide cylinder (21), the diversion grooves (212) are vertically arranged at equal intervals on the top wall of the drainage grooves (211), the air outlet holes (213) are arranged at equal intervals on the wall surface of the diversion grooves (212), and the positions of the wind guide holes (214) are staggered with the positions of the diversion grooves (212).

3. The multifunctional aircraft test platform according to claim 2, wherein: A linkage cavity (25) is formed inside the main body plate (1) corresponding to the positions below the first inner cavity (23) and the second inner cavity (24). A connection cavity (221) is formed inside the support rod (22), and the connection cavity (221) penetrates through the air guide cylinder (21) and the main body plate (1) to the inside of the drainage groove (211), the first inner cavity (23), the second inner cavity (24), and the linkage cavity (25). Connection pipes (26) are symmetrically arranged on the lower side of the main body plate (1) and penetrate through it to the inside of the linkage cavity (25). The first adjusting plate (231) is movably installed inside the first inner cavity (23), and the first matching holes (233) are distributed in a binary pattern at six equal intervals between the first slots (232).

4. The multifunctional aircraft test platform according to claim 3, characterized in that: The second adjusting plate (241) is movably installed inside the second inner cavity (24), and the second matching holes (243) are distributed in a binary pattern at eight equal intervals between the second slots (242).

5. The multifunctional aircraft test platform according to claim 4, wherein: Openings (271) penetrating through to its inside are equidistantly formed on the top wall of the matching plate (27). The matching pipe (272) penetrates through the support rod (22) to the inside of the connection cavity (221), and an electric control valve is arranged on the side of the matching pipe (272).

6. The multifunctional aircraft test platform according to claim 5, wherein: A third inner cavity (31) is formed inside the main body plate (1). Sliding grooves (32) are equidistantly formed on the top wall of the third inner cavity (31) and penetrate through the main body plate (1). Guide grooves (312) are circularly and equidistantly formed on the side surface of the movable plate (311) corresponding to the sliding grooves (32). The cylindrical part of the slider (321) is movably arranged inside the guide grooves (312). A rotating block (323) is rotatably installed inside the slider (321). A connecting rod (324) extends out of the inside of the matching cavity (322). Support springs (325) are equidistantly and fixedly installed on the side surface of the connecting rod (324). A detection block (326) is fixedly connected to the other end of the support spring (325) and is fixedly installed at the inner wall position of the matching cavity (322).

7. A multifunctional aircraft test platform according to claim 6, characterized in that: A restraint frame (33) is fixedly installed on the upper side of the connecting rod (324). A limiting block (34) is arranged on the upper side of the restraint frame (33). A buffer block (35) is fixedly installed on the lower side of the limiting block (34) and is arranged inside the restraint frame (33).

8. A multifunctional aircraft test platform according to claim 7, characterized in that: A linkage rod (41) is arranged on the side surface of the main body plate (1) and penetrates through the main body plate (1) to be arranged at the central positions of the movable plate (311), the first adjusting plate (231), and the second adjusting plate (241). A first motor (42) is fixedly installed on the lower side of the linkage rod (41). A second motor (44) is fixedly installed on the upper side of the mounting rod (43). Activity slots (45) penetrating through it are circularly and equidistantly formed on the inner side of the linkage rod (41) corresponding to the positions of the first adjusting plate (231), the second adjusting plate (241), and the movable plate (311). A pressing block (46) is movably installed inside the activity slots (45). A support block (47) is fixedly connected between the side surface of the pressing block (46) and the wall surface of the activity slots (45). Three trigger blocks (48) are arranged staggeredly with an angular difference of forty degrees.

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