A multifunctional aircraft test platform

Abstract

The present invention relates to the field of aircraft testing technology, and in particular to a multifunctional aircraft testing platform, comprising a main body plate, a wind tunnel mechanism being provided on the upper side of the main body plate, a constraint mechanism being provided on the upper side of the main body plate at a position corresponding to the internal position of the wind tunnel mechanism, a drive mechanism being provided inside the main body plate, the wind tunnel mechanism comprising an air duct, a diversion groove and a diversion groove being provided inside the air duct, an air outlet and an air guide hole being provided on the side thereof, a support rod being fixedly mounted on the lower side of the air duct, and a first inner cavity and a second inner cavity being provided inside the main body plate. The present invention provides a wind tunnel mechanism, a constraint mechanism, and a drive mechanism, thereby realizing a one-machine multi-test function, enabling the aircraft to be subjected to multi-directional wind tunnel combination testing, dynamically detecting the swing parameters of the aircraft during testing, and simultaneously generating a constraint landing protection for the aircraft during testing. In addition, the integrated drive design makes the device integrated in a small volume, saving space.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft testing, and in particular to a multifunctional aircraft testing platform. Background Art

[0002] With the rapid development of drone technology, the demand for aircraft performance testing is increasing, especially for testing key indicators such as wind resistance, flight stability, and landing safety. Traditional testing methods usually use a single wind tunnel or fixed restraint device, which has the following problems:

[0003] 1. Single wind direction simulation: Existing wind tunnels are mostly unidirectional or fixed multi-directional airflow, which cannot flexibly combine wind forces from different directions and is difficult to simulate complex natural wind field environments;

[0004] 2. Separation of constraints and detection: Test platforms often use rigid constraints, which cannot detect the swing amplitude and direction of the aircraft under the influence of wind in real time, resulting in inaccurate data feedback;

[0005] 3. Lack of landing protection: Most platforms lack a buffer protection mechanism when the aircraft lands uncontrollably, which can easily cause equipment damage. To this end, we propose a multi-functional aircraft test 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 multifunctional aircraft test platform.

[0007] To solve the above technical problems, the present invention provides the following technical solution: comprising a main body plate, a wind tunnel mechanism is provided on the upper side of the main body plate, a restraining mechanism is provided on the upper side of the main body plate at a position corresponding to the interior of the wind tunnel mechanism, and a driving mechanism is provided inside the main body plate;

[0008] The wind tunnel mechanism includes an air guide tube, the interior of the air guide tube is provided with a drainage groove and a diversion groove, the side of the air guide tube is provided with an air outlet hole and an air guide hole, a bracket rod is fixedly installed on the lower side of the air guide tube, a first inner cavity and a second inner cavity are respectively provided inside the main body plate, a first adjustment plate and a second adjustment plate are movably installed inside the first inner cavity and the second inner cavity, a first slot and a first matching hole are provided on the side of the first adjustment plate, a second slot and a second matching hole are provided on the side of the second adjustment plate, a matching plate is provided on the upper side of the main body plate, and a matching tube is fixedly installed through the side of the matching plate;

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

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

[0011] Furthermore, the air guide tube 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 tube is a hollow regular octagonal tube. The drainage grooves are equidistantly opened horizontally inside the air guide tube, the diversion grooves are equidistantly opened vertically on the top wall of the drainage grooves, and the air outlet holes are equidistantly opened on the wall of the diversion grooves. The positions of the air guide holes and the positions of the diversion grooves are staggered.

[0012] Furthermore, a linkage cavity is opened inside the main body plate at a position corresponding to the lower part of the first inner cavity and the second inner cavity, a connecting cavity is opened inside the bracket rod and passes through the air guide tube and the main body plate to the drainage groove and the first inner cavity, the second inner cavity, and the linkage cavity respectively. Connecting pipes are symmetrically arranged on the lower side of the main body plate and pass through it to the interior of the linkage cavity. The first adjustment plate is movably installed inside the first inner cavity, and the first matching holes are distributed in a binary manner according to six equal parts between the first slots.

[0013] Furthermore, the second adjustment plate is movably installed inside the second inner cavity, and the second matching holes are distributed in eight equal parts between the second slots in a binary distribution.

[0014] Furthermore, the top wall of the matching plate is provided with openings which penetrate into the interior thereof at equal intervals, and the matching tube penetrates the bracket rod to the interior of the connecting cavity.

[0015] Furthermore, the third inner cavity is opened inside the main body plate, the slide grooves are equidistantly opened on the top wall of the third inner cavity and pass through the main body plate, the side of the movable plate is equidistantly opened with guide grooves in a circular array corresponding to the position of the slide groove, the slider is movably arranged inside the guide groove, the rotating block is rotatably installed inside the slider, the connecting rod extends out of the matching cavity, the support spring is equidistantly fixed on the side of the connecting rod, and the detection block is fixedly connected to the other end of the support spring and is fixedly installed at the inner wall position of the matching cavity.

[0016] Furthermore, a restraint frame is fixedly mounted on the upper side of the connecting rod, a limit block is provided on the upper side of the limit block, and a buffer block is fixedly mounted on the lower side of the limit block and is provided inside the restraint frame.

[0017] Furthermore, the linkage rod is arranged on the side of the main plate and passes through the main plate and is arranged at the center position of the movable plate, the first adjustment plate and the second adjustment 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. The inner side of the linkage rod is provided with movable grooves passing through it in a circular array at equal intervals corresponding to the positions of the first adjustment plate, the second adjustment plate and the movable plate. The pressure block is movably installed inside the movable groove, and the support block is fixedly connected between the side of the pressure block and the wall of the movable groove. The three groups of trigger blocks are staggered and offset by forty degrees.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention realizes multiple measurement functions with one machine by providing a wind tunnel mechanism, a restraint mechanism, and a drive mechanism, enabling it to perform multi-directional wind tunnel combination tests on aircraft. During the test, the aircraft's swing parameters are dynamically detected, and restraint landing protection is generated during the test. In addition, the integrated drive design makes the equipment compact, saving space.

[0020] 2. The present invention sets up a wind tunnel mechanism, uses the binary hole design of the first adjustment plate and the second adjustment plate, and cooperates with the octagonal drainage structure of the air guide tube to achieve eight-way airflow simulation in a single direction or in pairs (such as northwest and north wind combination), covering the full-angle wind field test requirements and solving the problem of complex wind direction simulation.

[0021] 3. The present invention provides a matching plate and its peripheral components. The openings of the matching plate eject a buffer airflow, which forms a soft landing protection with the buffer block of the restraint frame, thereby reducing the impact damage when the aircraft loses control or during a test landing. It can also be used for the airflow resistance blowing operation of the aircraft landing test.

[0022] 4. The present invention sets a constraint mechanism. The movable plate rotates to drive the slider to slide along the guide groove, and the spacing between the four groups of constraint frames is adjusted synchronously to adapt to aircraft with different wingspans. The limit block can be removed for quick clamping, thereby realizing adaptive size adjustment for aircraft of different sizes.

[0023] 5. The present invention provides a connecting rod and its peripheral components. The connecting rod in the constraint mechanism is linked to the detection block through a rotating block. When the aircraft is deflected by wind force, the deformation pressure of the support spring provides real-time feedback on the swing direction and amplitude, thereby improving data accuracy.

[0024] 6. The present invention sets a driving mechanism, embeds the mounting rod and the trigger block in the linkage rod, and selectively drives the movable plate or the adjustment plate through the coordinated control of the first motor and the second motor, thereby reducing the space occupied by the mechanism.

[0025] 7. The present invention uses a hierarchical flow-guiding structure of diverter slots and air outlets to evenly distribute the airflow, avoid local turbulence interfering with the test results, and achieve efficient distribution of the airflow. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0028] Figure 3 It is a partial cross-sectional structural schematic diagram of the present invention;

[0029] Figure 4 Schematic diagram of the cross-sectional structure of the air guide tube of the present invention;

[0030] Figure 5 Schematic diagram of the partial structure of the first adjustment plate of the present invention;

[0031] Figure 6 Schematic diagram of the partial structure of the second adjustment plate of the present invention;

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

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

[0034] Figure 9 Schematic diagram of the partial explosion structure of the restraint mechanism of the present invention;

[0035] Figure 10 For the present invention Figure 2 A schematic diagram of the enlarged structure at point A;

[0036] Figure 11 It is a schematic diagram of the partial explosion structure of the driving mechanism of the present invention;

[0037] Figure 12 For the present invention Figure 2 Schematic diagram of the enlarged structure at point B.

[0038] Wherein: 1. Main body plate; 2. Wind tunnel mechanism; 21. Air guide tube; 211. Drainage groove; 212. Diverter groove; 213. Air outlet; 214. Air guide hole; 22. Support rod; 221. Connecting cavity; 23. First inner cavity; 231. First adjustment plate; 232. First slot; 233. First matching hole; 24. Second inner cavity; 241. Second adjustment plate; 242. Second slot; 243. Second matching hole; 25. Linkage cavity; 26. Connecting pipe; 27. Matching plate; 271. Opening; 27 2. Matching tube; 3. Constraint mechanism; 31. Third inner cavity; 311. Movable plate; 312. Guide groove; 32. Slide groove; 321. Slider; 322. Matching 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. DETAILED DESCRIPTION

[0039] In order to make the technical means, creative features, purpose and efficacy of the present invention easy to understand, the present invention is further described below in conjunction with specific examples, but the following examples are only preferred embodiments of the present invention, not all. Based on the examples in the embodiments, other embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present invention. The experimental methods in the following examples, unless otherwise specified, are conventional methods, and the materials, reagents, etc. used in the following examples, unless otherwise specified, can be obtained from commercial channels.

[0040] Example: Figure 1 and Figure 2 As shown, a multifunctional aircraft test platform includes a main body panel 1, which is a circular panel with rectangular struts disposed on its lower side. A wind tunnel mechanism 2 capable of multiple wind tunnel simulation tests is disposed on the upper side of the main body panel 1. A restraint mechanism 3 capable of restraining a test aircraft is disposed on the upper side of the main body panel 1 at a position corresponding to the interior of the wind tunnel mechanism 2. A drive mechanism 4 capable of selectively driving various mechanisms is disposed within the interior of the main body panel 1.

[0041] The wind tunnel mechanism 2 can be used to test the aircraft in different wind directions and provide landing protection for the aircraft.

[0042] like Figures 2 to 6As shown, the wind tunnel mechanism 2 includes an air guide tube 21 arranged on the upper side of the main body plate 1 and the air guide tube 21 is vertically arranged at the center of the main body plate 1. The air guide tube 21 is a hollow regular octagonal tube. Eight groups of drainage grooves 211 are equidistantly opened horizontally inside the air guide tube 21. The drainage grooves 211 are rectangular grooves. Diversion grooves 212 are equidistantly opened vertically on the top wall of the drainage groove 211. The diversion grooves 212 are rectangular grooves. Air outlet holes 213 that penetrate the air guide tube 21 to the inside thereof are equidistantly opened on the wall surface of the diversion groove 212. The air outlet holes 213 are circular holes. 1 is provided with air guide holes 214 at equal intervals on its side, and the positions of the air guide holes 214 are staggered with the positions of the diverter slots 212. The air guide holes 214 are circular holes. In specific operation, airflow is blown in the southeast, northwest, southeast, northeast, southwest, and northwest directions through the sides of the diversion slots 211 to test the aircraft. After the air flows into the interior of the diversion slots 211, it flows into the interior of the diverter slots 212 and is discharged from the air outlet holes 213 for airflow blowing. When the air outlet holes 213 are blowing, the airflow is discharged from the corresponding air guide holes 214 to achieve airflow.

[0043] The lower side of the air guide tube 21 corresponds to the position of the drainage groove 211 and is fixedly installed with a support rod 22 at equal distances. The support rod 22 is a cylindrical rod, and a first inner cavity 23 and a second inner cavity 24 are respectively opened inside the main body plate 1. The first inner cavity 23 and the second inner cavity 24 are circular cavities. A linkage cavity 25 is opened inside the main body plate 1 at a position below the first inner cavity 23 and the second inner cavity 24. The linkage cavity 25 is a circular cavity. A connecting cavity 221 is opened inside the support rod 22, and the connecting cavity 221 passes through the air guide tube 21 and the main body plate 1 to the drainage groove 211 and the first inner cavity 23, the second inner cavity 24, and the linkage cavity 25. The connecting cavity 221 is a cylindrical cavity, and connecting cavities 221 are symmetrically arranged on the lower side of the main body plate 1. The first adjusting plate 231 is movably installed in the first inner cavity 23. The first adjusting plate 231 is a circular plate with a rubber ring sleeved on the side. Eight groups of first slots 232 are equidistantly provided on the side of the first inner cavity 23 corresponding to the position of the bracket rod 22. The first slots 232 are square holes. A first matching hole 233 is provided on the side of the first adjusting plate 231 corresponding to the position of the first slot 232. The first matching holes 233 are divided into six equal parts and are binary distributed between the first slots 232 to realize the rotation of the first adjusting plate 231 to different angles. When the angle is adjusted, the airflow in two directions can be selected in a semicircular direction, such as northwest and north, northwest and northeast, northwest and east, etc. A second adjustment plate 241 is movably installed inside the second inner cavity 24. The second adjustment plate 241 is a circular plate with a rubber ring sleeved on the side. Eight groups of second slots 242 are equidistantly provided on the side of the second inner cavity 24 corresponding to the position of the bracket rod 22. The second slots 242 are square holes. Second matching holes 243 are provided on the side of the second inner cavity 24 corresponding to the second slots 242. The second matching holes 243 are distributed in eight equal parts between the second slots 242 in a binary distribution, so that a single direction of airflow can be selected when the second adjustment plate 241 rotates. Specifically, after The follow-up component can drive the first adjustment plate 231 or the second adjustment plate 241 to rotate. When the first adjustment plate 231 is rotated to a corresponding angle, the airflow inside the linkage chamber 25 can pass through the first matching hole 233, the second slot 242 and the connecting chamber 221 to the inside of the diversion groove 211, and then flow out of the diverter groove 212 and be discharged through the air outlet 213, thereby realizing a blowing test on the one-way airflow of the aircraft; when the second adjustment plate 241 is rotated to a corresponding angle, the airflow inside the linkage chamber 25 can pass through the first matching hole 232, the second matching hole 243 and the connecting chamber 221 to the inside of the diversion groove 211, and then flow out of the diverter groove 212 and be discharged through the air outlet 213, thereby realizing a blowing test on the two-way airflow of the aircraft;

[0044] The upper side of the main body plate 1 is provided with a matching plate 27, which is a circular ring plate with a hollow interior and four groups of rectangular grooves are opened on its side. Openings 271 are equidistantly opened on the top wall of the matching plate 27 and penetrate into its interior. The openings 271 are circular holes. Matching tubes 272 are fixedly installed equidistantly on the side of the matching plate 27 corresponding to the position of the bracket rod 22, and the matching tubes 272 pass through the bracket rod 22 to the interior of the connecting cavity 221. The matching tubes 272 are circular tubes with electric control valves on the side. Specifically, the matching tubes 272 can be controlled to open and close by an external controller, so that the airflow in the connecting cavity 221 can flow into the matching plate 27 through the matching tubes 272 and be discharged from the openings 271, thereby blowing the bottom side of the aircraft, realizing the bottom-blowing aircraft landing test, and also when the aircraft fails to fall, the airflow can buffer the aircraft to reduce the damage to the aircraft.

[0045] The constraint mechanism 3 can realize the constraint of the corresponding aircraft and detect the swing of the aircraft when it is blown by the wind. It is also convenient to test, install and disassemble.

[0046] like Figure 2 、 Figure 3 and Figures 7 to 10As shown, the constraint mechanism 3 includes a third inner cavity 31 opened inside the main body plate 1, and the third inner cavity 31 is arranged above the first inner cavity 23 and the second inner cavity 24. The third inner cavity 31 is a circular cavity, and four groups of slide grooves 32 penetrating the main body plate 1 are equidistantly opened on the top wall of the third inner cavity 31. The slide grooves 32 are rectangular grooves. A movable plate 311 is movably installed inside the third inner cavity 31. The movable plate 311 is a circular plate with a rubber ring on the side. Guide grooves 312 are equidistantly opened in a circular array on the side of the movable plate 311 corresponding to the position of the slide grooves 32. The guide grooves 312 are The arc groove is provided with a slider 321 movably installed in the interior of the slide groove 32 and the slider 321 is movably arranged in the guide groove 312. The slider 321 is also movably arranged in the rectangular groove of the matching plate 27 and is constrained by it. The slider 321 is a combination of a convex block and a cylindrical block. The cylindrical block is slidably installed in the guide groove 312, and the convex block is slidably installed in the slide groove 32. A matching cavity 322 is provided on the upper side of the slider 321. The matching cavity 322 is a frustum cavity. A rotating block 323 is provided on the bottom wall of the matching cavity 322 and the rotating block 323 is rotatably installed in the slider 321. The rotating block 323 is a spherical block. A connecting rod 324 is fixedly installed on the side of the rotating block 323 and the connecting rod 324 extends out of the matching cavity 322. The connecting rod 324 is a circular rod. Four groups of supporting springs 325 are fixedly installed in a circular array on the side of the connecting rod 324 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 on the inner wall of the matching cavity 322. The detection block 326 is a pressure sensor (a micro force sensor such as HX711 can be used). Specifically, the connecting rod 324 swings under force, and the synchronous The rotating block 323 rotates inside the slider 321 to constrain the connecting rod 324, and the support spring 325 elastically supports and pulls the connecting rod 324. When the support spring 325 deforms, the detection block 326 can detect the change in its side pressure, and feedback is sent to the external controller to determine the swing direction and amplitude of the connecting rod 324. In addition, the movable plate 311 is driven to rotate by subsequent components, and the slider 321 slides and guides inside the guide groove 312. At the same time, the slider 321 slides and cooperates with the slide groove 32, so that the slider 321 can be synchronously adjusted to adapt to different sizes of aircraft;

[0047] The upper side of the connecting rod 324 is fixedly installed with a restraining frame 33, which is a "U"-shaped frame, and a limiting block 34 is provided on the upper side of the restraining frame 33 and the limiting block 34 is fixed to the side of the restraining frame 33 by screws. The limiting block 34 is a rectangular block, and a buffer block 35 is fixedly installed on the lower side of the limiting block 34, and the buffer block 35 is arranged at the inner position of the restraining frame 33; specifically, the limiting block 34 is removable, and after disassembly, the four sets of aircraft arms can be movably set to the internal position of the restraining frame 33, and then the limiting block 34 is fixed to the side of the restraining frame 33 by screws, so that it plays a four-side constraint path during aircraft testing. When the aircraft is deviated during testing, it can drive the connecting rod 324 to swing, triggering the above-mentioned detection of its swing direction and amplitude; the buffer block 35 provided can play a buffering role when the aircraft takes off too high to avoid bumping and damage;

[0048] The drive mechanism 4 can be used for multi-state driving, so that the drive modules are arranged more centrally and occupy less space.

[0049] like Figure 2 、 Figure 11 and Figure 12As shown, the driving mechanism 4 includes a linkage rod 41 arranged on the side of the main plate 1, and the linkage rod 41 passes through the main plate 1 and is arranged at the center of the movable plate 311, the first adjustment plate 231 and the second adjustment plate 241. The linkage rod 41 is a cylindrical rod with a cylindrical groove on the 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 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 mounting rod 43 is fixedly installed on the upper side of the mounting rod 43. 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 center of the matching plate 27. On the inner side of the linkage rod 41, corresponding to the first adjustment plate 231, the second adjustment plate 241 and the movable plate 311, there are movable grooves 45 running through them in a circular array at equal intervals. The movable groove 45 is a convex groove. A pressure block 46 is movably installed inside the movable groove 45. The pressure block 46 is a convex block made of wear-resistant rubber. A support is symmetrically fixed between the side of the pressure block 46 and the wall of the movable groove 45. Block 47, the support block 47 is a "W"-shaped block made of elastic material, and a trigger block 48 is equidistantly and movably sleeved on the side of the mounting rod 43 corresponding to the movable groove 45. The three groups of trigger blocks 48 are staggered at a forty-degree angle difference, so that when the mounting rod 43 drives the trigger block 48 to rotate, the pressure blocks 46 corresponding to the side positions of the first adjustment plate 231, the second adjustment plate 241 and the movable plate 311 can be squeezed and triggered respectively; specifically, the second motor 44 drives the mounting rod 43 to rotate, and the mounting rod 43 drives the trigger block 48 to rotate synchronously, and the trigger block 48 is respectively The pressing block 46 corresponding to the side position of the first adjustment plate 231, the second adjustment plate 241 or the movable plate 311 is squeezed. The pressing block 46 is squeezed so that the support block 47 is pulled and deformed and fits into the inner position of the first adjustment plate 231, the second adjustment plate 241 or the movable plate 311. At this time, when the first motor 42 drives the linkage rod 41 to rotate, the first adjustment plate 231, the second adjustment plate 241 or the movable plate 311 can be driven to rotate synchronously through the linkage rod 41, so that the drive operation of its components can be switched, the structural setting is relatively centralized, and the space occupied is small.

[0050] Working principle:

[0051] Before testing: First, completely disassemble the limit block 34 and detach it from the side position of the constraint frame 33. 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 movable plate 311, so that the pressure block 46 fits the inner position of the movable plate 311. At this time, the first motor 42 drives the linkage rod 41 to rotate, which can drive the movable plate 311 to rotate inside the third inner cavity 31. The slide 32 slides in the guide groove 312 and the slide 32 respectively to adjust the position synchronously. In this way, the constraint frame 33 can be driven to move to the corresponding position to adapt to UAVs of different sizes.

[0052] In the second step, after the four sets of UAV arms are movably set in the internal position of the restraint frame 33, the UAV is controlled to slowly land on the upper side of the matching plate 27, and the limit block 34 is fixed to the side of the restraint frame 33 by screws;

[0053] During the test: First, the UAV is controlled to lift off and hover. The arm drives the constrained frame 33 to constrain the connecting rod 324 to swing slightly. The linkage rod 41 of the constraint mechanism 3 is constrained by the rotation of the rotating block 323. At this time, each support spring 325 is elastically deformed, and the force applied to each detection block 326 is recorded as zero by default.

[0054] The second step is a 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 adjustment plate 241. The pressure block 46 fits the inner position of the second adjustment plate 241. The first motor 42 drives the linkage rod 41 to rotate and drives the second adjustment plate 241 to rotate inside the second inner cavity 24. The second matching hole 243 matches the corresponding position of the connecting cavity 221. At this time, the first adjustment plate 231 defaults to its original position, that is, the first slot 232 corresponds to the position of the connecting cavity 221, so that each One-way ventilation operation in the direction, that is, the airflow supplied by the connecting pipe 26 passes through the linkage cavity 25, the first slot 232, the second matching hole 243 and the connecting cavity 221 to the inside of the guide groove 211, and then is diverted by the diversion groove 212 and discharged from the air outlet 213. The one-way airflow blows the UAV aircraft and flows out from the corresponding air guide hole 214 to complete the airflow flow. After the UAV aircraft swings, it is constrained by the constraint frame 33 and drives each connecting rod 324 to swing. The swing amplitude of the aircraft can be obtained by recording the value through the detection block 326;

[0055] The third step is a 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 adjustment plate 231. The pressure block 46 fits the inner position of the first adjustment plate 231. The first motor 42 drives the linkage rod 41 to rotate and drives the first adjustment plate 231 to rotate inside the first inner cavity 23. The first matching hole 233 matches the corresponding position of the connecting cavity 221. At this time, the second adjustment plate 241 defaults to its original position, that is, the second slot 242 corresponds to the position of the connecting cavity 221, realizing semi-automatic operation. The two-way ventilation operation in the circular direction, that is, the airflow supplied by the connecting pipe 26 passes through the linkage cavity 25, the first matching hole 233, the second slot 242 and the connecting cavity 221 to the inside of the guide groove 211, and then is diverted by the diversion groove 212 and discharged from the air outlet 213. The two-way airflow blows on the UAV aircraft and flows out from the corresponding air guide hole 214 to complete the air flow. After the UAV aircraft swings, it is constrained by the constraint frame 33 and drives each connecting rod 324 to swing. The swing amplitude of the aircraft can be obtained by recording the value through the detection block 326;

[0056] The fourth step is to perform a wind tunnel test on the side of the UAV aircraft as above. When a landing test is required, the UAV is controlled to perform a landing test. At this time, the electric control valve on the side of the matching pipe 272 is controlled to open, and the air flow inside the connecting cavity 221 is guided to the inside of the matching plate 27 through the matching pipe 272, and then discharged from the opening 271, blowing on the bottom side of the UAV aircraft. In this way, the swing amplitude of the UAV landing can be tested.

[0057] When the UAV malfunctions and needs to land, the restraint frame 33 can still restrain the UAV aircraft from landing, and at the same time, the airflow blown out from the opening 271 can be controlled to perform wind buffering operations on the aircraft, reducing the degree of damage; in addition, when the UAV takes off too fast, the buffer block 35 can also perform buffering operations on the aircraft arm, similarly reducing the degree of damage.

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

Claims

1. A multifunctional aircraft test platform, comprising a main body plate (1), a wind tunnel mechanism (2) being provided on the upper side of the main body plate (1), a restraining mechanism (3) being provided on the upper side of the main body plate (1) at a position corresponding to an interior position of the wind tunnel mechanism (2), and a driving mechanism (4) being provided inside the main body plate (1); Its characteristics are: The wind tunnel mechanism (2) comprises an air guide tube (21), the interior of the air guide tube (21) is provided with a drainage groove (211) and a diversion groove (212), and the side of the air guide tube (21) is provided with an air outlet hole (213) and an air guide hole (214), a support rod (22) is fixedly installed on the lower side of the air guide tube (21), a first inner cavity (23) and a second inner cavity (24) are respectively provided inside the main body plate (1), a first adjustment plate (231) and a second adjustment plate (241) are 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 provided on the side of the first adjustment plate (231), a second slot (242) and a second matching hole (243) are provided on the side of the second adjustment plate (241), a matching plate (27) is provided on the upper side of the main body plate (1), and a matching tube (272) is fixedly installed through the side of the matching plate (27); The restraining mechanism (3) includes a third inner cavity (31) and a slide groove (32), a movable plate (311) is movably installed inside the third inner cavity (31), a slider (321) is movably installed inside the slide groove (32), a matching cavity (322) is provided on the upper side of the slider (321), a rotating block (323) is provided on the bottom wall of the matching cavity (322), a connecting rod (324) is fixedly installed on the side of the rotating block (323), and a supporting spring (325) and a detection block (326) are provided on the side of the connecting rod (324); The driving mechanism (4) comprises a linkage rod (41), wherein a first motor (42) and a second motor (44) are respectively provided 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 of the mounting rod (43), and a pressure block (46) and a support block (47) are provided on the side of the trigger block (48).

2. The multifunctional aircraft test platform according to claim 1, characterized in that: The air guide tube (21) is arranged on the upper side of the main body plate (1) and is vertically arranged at the center of the main body plate (1). The air guide tube (21) is a hollow regular octagonal tube. The drainage grooves (211) are equidistantly horizontally opened inside the air guide tube (21). The diversion grooves (212) are equidistantly vertically opened on the top wall of the drainage groove (211). The air outlet holes (213) are equidistantly opened on the wall surface of the diversion groove (212). The positions of the air guide holes (214) and the diversion grooves (212) are staggered.

3. The multifunctional aircraft test platform according to claim 2, characterized in that: A linkage cavity (25) is provided inside the main body plate (1) at a position corresponding to the lower portion of the first inner cavity (23) and the second inner cavity (24); a connecting cavity (221) is provided inside the support rod (22); and the connecting cavity (221) respectively penetrates the air guide tube (21) and the main body plate (1) to the drainage groove (211) and the inner position of the first inner cavity (23), the second inner cavity (24), and the linkage cavity (25); a connecting pipe (26) is symmetrically provided on the lower side of the main body plate (1) and penetrates it to the inner position of the linkage cavity (25); a first adjustment plate (231) is movably installed inside the first inner cavity (23); and the first matching holes (233) are distributed in six equal parts between the first slots (232) in a binary distribution.

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

5. The multifunctional aircraft test platform according to claim 4, characterized in that: The top wall of the matching plate (27) is provided with openings (271) extending therethrough at equal intervals. The matching tube (272) extends through the support rod (22) to the interior of the connecting cavity (221). An electric control valve is provided on the side of the matching tube (272).

6. The multifunctional aircraft test platform according to claim 5, characterized in that: The third inner cavity (31) is opened inside the main body plate (1), the slide groove (32) is equidistantly opened on the top wall of the third inner cavity (31) and passes through the main body plate (1), the side of the movable plate (311) is equidistantly provided with guide grooves (312) in a circular array corresponding to the position of the slide groove (32), the cylindrical block part of the slider (321) is movably set inside the guide groove (312), the rotating block (323) is rotatably installed inside the slider (321), the connecting rod (324) extends out of the matching cavity (322), the support spring (325) is equidistantly fixed on the side of the connecting rod (324), and the detection block (326) is fixedly connected to the other end of the support spring (325) and is fixedly installed on the inner wall of the matching cavity (322).

7. The multifunctional aircraft test platform according to claim 6, characterized in that: A restraining frame (33) is fixedly mounted on the upper side of the connecting rod (324), a limiting block (34) is provided on the upper side of the restraining frame (33), and a buffer block (35) is fixedly mounted on the lower side of the limiting block (34) and is provided at an inner side of the restraining frame (33).

8. The multifunctional aircraft test platform according to claim 7, characterized in that: The linkage rod (41) is arranged on the side of the main plate (1) and passes through the main plate (1) and is arranged at the center of the movable plate (311), the first adjustment plate (231) and the second adjustment plate (241). The first motor (42) is fixedly installed on the lower side of the linkage rod (41), and the second motor (44) is fixedly installed on the upper side of the installation rod (43). The inner side of the linkage rod (41) is equidistantly provided with movable grooves (45) passing through it in a circular array corresponding to the positions of the first adjustment plate (231), the second adjustment plate (241) and the movable plate (311). The pressure block (46) is movably installed inside the movable groove (45). The support block (47) is fixedly connected between the side of the pressure block (46) and the wall of the movable groove (45). The three groups of trigger blocks (48) are staggered at a forty-degree angle difference.

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