CN114180098A

CN114180098A - Indoor adjusting device for unmanned aerial vehicle flight test

Info

Publication number: CN114180098A
Application number: CN202111654074.3A
Authority: CN
Inventors: 李晓露; 李正强
Original assignee: Fuyang Anzhi Technology Information Consulting Co ltd
Current assignee: Fuyang Anzhi Technology Information Consulting Co ltd
Priority date: 2021-12-30
Filing date: 2021-12-30
Publication date: 2022-03-15

Abstract

The invention discloses an indoor adjusting device for unmanned aerial vehicle flight test, belonging to the field of unmanned aerial vehicle flight test, comprising a base seat platform, wherein the edge of the top end of the base seat platform is fixedly connected with a hinged seat, two sides of the hinged seat are rotatably connected with connecting movable joints, the tail end of the connecting movable joint is fixedly connected with a wind measuring cover plate, the side surface of the wind measuring cover plate is fixedly connected with an air flow fan, the top surface of the base seat platform is fixedly connected with a support rod, the top end of the support rod is fixedly connected with a fixed rod end, and the side surface of the fixed rod end is fixedly connected with a track ring. Be convenient for through test gained data, carry out accurate adjustment to unmanned aerial vehicle, performance unmanned aerial vehicle performance.

Description

Indoor adjusting device for unmanned aerial vehicle flight test

Technical Field

The invention relates to the field of flight tests of unmanned aerial vehicles, in particular to an indoor adjusting device for the flight tests of the unmanned aerial vehicles.

Background

Unmanned aerial vehicle carries out the flight test in outdoor environment, if meet fog and low cloud, will influence unmanned aerial vehicle flight, except the risk that humidity increases, cloud and fog weather still can lead to visibility to reduce, also need to pay attention to and take precautions against, if meet air humidity great, harm very big to unmanned aerial vehicle's motor and sensitive components and parts, and still need avoid the camera lens, cell-phone or panel computer screen wet, it is very big to freeze the harm to unmanned aerial vehicle, the freezing meeting of paddle increases aircraft weight, be unfavorable for unmanned aerial vehicle normal flight, outdoor flight test receives weather influence condition more, in the changeable weather of some environment or season, just need wait for the weather that is fit for the test, the limitation is great.

Disclosure of Invention

1. Technical problem to be solved

Aiming at the problems in the prior art, the invention aims to provide an indoor adjusting device for the flight test of an unmanned aerial vehicle, which can realize indoor testing of the flight capability of the unmanned aerial vehicle, can avoid the influence of the external weather environment on the flight of the unmanned aerial vehicle, utilizes the structure to fix the flight of the unmanned aerial vehicle for testing, ensures that the required occupied space area is smaller, can also play a role in protecting the unmanned aerial vehicle under the condition of lower cruising electric quantity of the unmanned aerial vehicle, can simulate and test the unmanned aerial vehicle simultaneously, and can accurately adjust the unmanned aerial vehicle through testing the obtained data when the unmanned aerial vehicle is influenced by wind force in the actual environment, thereby exerting the performance of the unmanned aerial vehicle.

2. Technical scheme

In order to solve the above problems, the present invention adopts the following technical solutions.

An indoor adjusting device for unmanned aerial vehicle flight testing comprises a base seat platform, wherein a hinged seat is fixedly connected to the edge of the top end of the base seat platform, two sides of the hinged seat are rotatably connected with a connecting movable joint, the tail end of the connecting movable joint is fixedly connected with an air measuring cover plate, the side surface of the air measuring cover plate is fixedly connected with an air flow fan, the top surface of the base seat platform is fixedly connected with a supporting rod, the top end of the supporting rod is fixedly connected with a fixed rod end, the side surface of the fixed rod end is fixedly connected with a track ring, the outer side surface of the track ring is fixedly connected with a supporting plate, and the top end of the supporting plate is fixedly connected with a top fixed ring;

the inboard of the top solid ring is provided with the lift pressure detection end that is used for detecting unmanned aerial vehicle lift data, the inboard of track ring is provided with the balanced test end of upset that is used for testing unmanned aerial vehicle upset ability, the inboard of track ring is provided with the interior track arc board that is used for testing unmanned aerial vehicle level and turns to the equilibrium, the inside test flabellum that receives the decline resistance scene with simulation unmanned aerial vehicle when descending that is provided with of base seat platform.

Further, an inner ring groove is formed in the inner side face of the track ring, the inner ring groove is in sliding connection with the inner rail arc plate, inner groove rollers are rotatably connected to the two sides of the inner rail arc plate, the inner groove rollers are in contact fit with the inner ring groove, and the inner rail arc plate is arc-shaped integrally.

Further, the side intermediate position fixed connection of track ring has the horizontal beam pole, the side fixedly connected with sublance of horizontal beam pole, horizontal beam pole and sublance all adopt the polyethylene material, and horizontal beam pole and sublance are hollow structure, the other end fixedly connected with of horizontal beam pole changes solid ring end, the internally mounted of horizontal beam pole has direction sensor.

Furthermore, the overturning balance test end comprises an overturning ring, a frame ring, a lifting force ejector rod, an upper clamping plate and a lower clamping disc, the overturning ring is fixedly connected to the side face of the overturning ring end, the frame ring is rotatably connected to the side face of the overturning ring, the overturning ring is distributed on two sides of the frame ring, the lifting force ejector rod penetrates through the side faces of two ends of the frame ring, the upper clamping plate is fixedly connected to the tail end of the lifting force ejector rod at one position, and the lower clamping disc is fixedly connected to the tail end of the lifting force ejector rod at the other position.

Furthermore, the inboard of turning ring is provided with interior supplementary gyro wheel, interior supplementary gyro wheel with the frame ring constitutes to rotate and is connected, the arc wall has been seted up in the outside of turning ring, the both ends side fixedly connected with diaphragm of frame ring, the circular slot has been seted up on the surface of diaphragm, be provided with the ball under the circular slot of diaphragm, the ball with the arc groove agrees with mutually.

Further, go up the grip block with the equal fixedly connected with fixed block in both ends of lower grip block, the fixture block groove has been seted up to the side of fixed block, fixture block groove side shape is dwindled to the middle part width by both ends gradually, fixture block inslot side is provided with the fixture block that cross-sectional shape is the same, the side fixedly connected with slip guide vane of fixed block, slip guide vane sliding connection has the guide bar, the guide bar with frame ring fixed connection, the bottom side fixedly connected with shrink pole of going up the grip block, the end of shrink pole is provided with the sucking disc, go up the grip block with lower grip block overall structure is the same.

Furthermore, the inboard fixed connection of top solid ring is no less than three connection cover plate, the crossing department sliding connection of connection cover plate has the linking dish pole, the terminal fixedly connected with top force dish of the bottom side of linking dish pole, the linking dish pole passes the crossing department of connection cover plate and constitutes sliding structure rather than, the top fixedly connected with atress dish of linking dish pole, the bottom surface fixedly connected with of atress dish is no less than three pressure detection sensor, pressure detection sensor with connection cover plate fixed connection, the top force dish is located the lift ejector pin directly over, the outside of linking dish pole is provided with the lift spring, the lift spring with connection cover plate fixed connection.

Furthermore, a displacement block groove is formed in the surface of the base seat platform, a pulling frame is connected to the inner side of the displacement block groove in a sliding mode, the other end of the pulling frame and the connecting movable joint form a movable connection, a sliding block is fixedly connected to the bottom side of one end of the pulling frame, a sliding rod is connected to the inner side of the sliding block in a sliding mode, the outer wall of the bottom shaft is fixedly connected to one end of the sliding rod, a fixed seat plate is fixedly connected to the other end of the sliding rod, the fixed seat plate is fixedly connected with the base seat platform, and a displacement sliding rod is fixedly connected to the bottom end of the sliding rod.

Furthermore, the bottom outer side of the bottom shaft outer wall is rotatably connected with a rotating disc, a tooth path is formed in the outer side of the rotating disc, a motor gear is connected to the outer side face of the rotating disc in a meshed mode, a small motor is fixedly connected to the outer side of the bottom shaft outer wall, an outer rotating disc is fixedly connected to the outer side face of the rotating disc, an arc-shaped driving rod is fixedly connected to the outer side face of the outer rotating disc, the arc-shaped driving rod and a displacement slide rod form a sliding structure, clamping holes distributed at equal intervals are formed in the outer side face of the outer rotating disc, and a spring clamping rod is arranged on the outer side face of the outer rotating disc.

3. Advantageous effects

Compared with the prior art, the invention has the advantages that:

(1) this scheme is in the flip ring outside through the ball, and the resistance that produces when the reduction outer lane that can be fine rotates, supplementary gyro wheel in the flip ring inner circle adoption can cooperate jointly with the ball, stable support nature when providing the flip ring upset, when letting unmanned aerial vehicle overturn and rotate, can be more smooth to reduce the influence of mechanical revolution mechanic helping hand to the unmanned aerial vehicle test.

(2) This scheme, through letting sucking disc and the laminating of unmanned aerial vehicle fuselage, and through external suction device, take the air in the sucking disc out, can fix the unmanned aerial vehicle body, the shrink pole carries out the adaptable different unmanned aerial vehicle model of structural contraction, this kind of fixed mode can let the unmanned aerial vehicle wing be in the outside, can furthest's reduction the device fixed part to unmanned aerial vehicle's interference and influence, guarantee the degree of accuracy of data acquisition and information, when unmanned aerial vehicle continuation of the journey electric quantity is not enough simultaneously, also can play the guard action to unmanned aerial vehicle, avoid the accident of crash to appear in outdoor test.

(3) This scheme, fixed unmanned aerial vehicle's last grip block of utilization with lower grip block drives the ascending vertical removal of lift ejector pin to let the lift ejector pin contact with top force dish bottom gradually, the top force dish receives vertical ascending power rebound, it is tensile finally to drive the lift spring, and let the atress dish pulling pressure detection sensor that the linking rod is connected test, pressure and the pulling force numerical value that the accessible recorded from this, calculate the speed that unmanned aerial vehicle rises and descends, but the ascending speed of flight of this kind of mode precision measurement unmanned aerial vehicle.

(4) This scheme, through the spout restriction that the displacement slide bar is along with receiving the arc driving lever, and change the current position, the displacement slide bar relocation, and through slide bar restriction moving direction, when the displacement slide bar removes, through the fixed pulling frame in top, the movable joint deflection is connected in the pulling, can simulate in the real scene, the influence of the wind-force of equidirectional when dividing the flight to unmanned aerial vehicle balance ability, and carry out the contrast experiment with the data of measuring when the windless flight state, so that according to the anti-wind limit of unmanned aerial vehicle, carry out appropriate adjustment to unmanned aerial vehicle screw and fuselage equilibrium, and convenient reasonable according to experiment data carries out appropriate adjustment.

(5) This scheme, through small-size motor driving motor gear, it rotates together with the outer carousel to drive the rolling disc, the arc driving lever that the outer carousel outside is connected rotates together, rotatory in-process, the screens hole in the outer carousel outside can be at spacing speed reduction under the spring screens pole effect, when small-size motor no longer drives, the outer carousel no longer receives the steering effort drive, make spring screens pole and current position correspond, or nearest screens hole block, play limiting displacement, this structure utilizes the drive, when adjustable unmanned aerial vehicle side receives wind-force influence, the test of unmanned aerial vehicle self balancing ability, so that test out unmanned aerial vehicle correlation performance, can normally fly under what kind of environmental condition.

Drawings

FIG. 1 is a schematic front perspective view of the present invention;

FIG. 2 is a schematic view of a frame support structure of the present invention;

FIG. 3 is a schematic view of the inner side of the orbital ring of the present invention;

FIG. 4 is a schematic view of the internal structure of the base platform of the present invention;

FIG. 5 is a schematic diagram of a flip balance testing end structure according to the present invention;

FIG. 6 is a schematic diagram of an upper clamping plate structure according to the present invention;

FIG. 7 is an enlarged view of A of FIG. 1 according to the present invention;

fig. 8 is a schematic structural view of the lifting pressure detecting end of the present invention.

The reference numbers in the figures illustrate:

1. a base seat stand; 2. a hinged seat; 3. connecting the movable joint; 4. a wind measuring cover plate; 5. an airflow fan; 6. a support bar; 7. fixing the rod end; 8. an orbital ring; 9. a support plate; 10. a top fixing ring; 11. connecting the cover plate; 12. testing fan blades; 13. a lifting pressure detection end; 14. turning over the balance test end; 15. a force-bearing plate; 16. a horizontal beam; 17. an inner ring groove; 18. an inner rail arc plate; 19. an inner groove roller; 20. an auxiliary rod; 21. rotating the fixed ring end; 22. the outer wall of the bottom shaft; 23. a slide bar; 24. a slider; 25. a seat fixing plate; 26. a displacement slide bar; 27. an arc-shaped deflector rod; 28. an outer turntable; 29. rotating the disc; 30. a motor gear; 31. a small-sized motor; 32. a position clamping hole; 33. a spring retention post; 34. a flipping ring; 35. an inner auxiliary roller; 36. a transverse plate; 37. a ball bearing; 38. a frame ring; 39. a guide bar; 40. a sliding guide piece; 41. a fixed block; 42. an upper clamping plate; 43. a lift ejector rod; 44. a lower clamping plate; 45. a retracting lever; 46. a suction cup; 47. a displacement block slot; 48. pulling the frame; 49. a pressure detection sensor; 50. a lift spring; 51. a disc connecting rod; 52. and (4) a jacking disc.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention.

Referring to fig. 1-8, an indoor adjusting device for an unmanned aerial vehicle flight test includes a base seat platform 1, a hinge seat 2 fixedly connected to an edge of a top end of the base seat platform 1, a connecting movable joint 3 rotatably connected to two sides of the hinge seat 2, a wind measuring cover plate 4 fixedly connected to a terminal of the connecting movable joint 3, an airflow fan 5 fixedly connected to a side surface of the wind measuring cover plate 4, a support rod 6 fixedly connected to a top surface of the base seat platform 1, a fixed rod end 7 fixedly connected to a top end of the support rod 6, a track ring 8 fixedly connected to a side surface of the fixed rod end 7, a support plate 9 fixedly connected to an outer side surface of the track ring 8, and a top fixed ring 10 fixedly connected to a top end of the support plate 9;

the inboard of the solid ring 10 of top is provided with the lift pressure detection end 13 that is used for detecting unmanned aerial vehicle lift data, and the inboard of track ring 8 is provided with the balanced test end 14 of upset that is used for testing unmanned aerial vehicle upset ability, and the inboard of track ring 8 is provided with the interior rail arc board 18 that is used for testing unmanned aerial vehicle level and turns to the equilibrium, and base seat 1 is inside to be provided with the test flabellum 12 that uses simulation unmanned aerial vehicle received the decline resistance scene when descending.

Referring to fig. 2 and 3, inner ring groove 17 has been seted up to the medial surface of track ring 8, inner ring groove 17 and inner rail arc board 18 sliding connection, inner groove gyro wheel 19 has all been connected with in the both sides rotation of inner rail arc board 18, inner groove gyro wheel 19 is laminated with the contact of inner ring groove 17, the whole of inner rail arc board 18 is the arc, inner rail arc board 18 is when rotating, the movable position of inner rail arc board 18 is restricted through the inner ring groove 17 of outer lane, and support through inner rail arc board 18 and horizontal beam pole 16, tightly laminate inner groove gyro wheel 19 and the medial surface of inner ring groove 17 of inner rail arc board 18 side, can promote the smooth degree in the aspect of unmanned aerial vehicle steering test.

Referring to fig. 3, track ring 8's side intermediate position fixed connection has horizontal beam pole 16, horizontal beam pole 16's side fixedly connected with sublance 20, horizontal beam pole 16 all adopts the polyethylene material with sublance 20, and horizontal beam pole 16 is hollow structure with sublance 20, horizontal beam pole 16's the other end fixedly connected with changes solid ring end 21, horizontal beam pole 16's internally mounted has direction sensor, direction sensor utilizes the earth induction to judge the azimuth direction, can be when horizontal beam pole 16 rotates, mode through data, data display when flying unmanned aerial vehicle comes out, whole frame adopts empty shape structure, burden when can alleviateing unmanned aerial vehicle test flight, and the holistic weight of device.

Referring to fig. 4, a rotating disc 29 is rotatably connected to the outer side of the bottom end of the bottom shaft outer wall 22, a tooth track is formed on the outer side of the rotating disc 29, a motor gear 30 is engaged with the outer side of the rotating disc 29, a small motor 31 is fixedly connected to the outer side of the bottom shaft outer wall 22, an outer rotating disc 28 is fixedly connected to the outer side of the rotating disc 29, an arc-shaped shift lever 27 is fixedly connected to the outer side of the outer rotating disc 28, the arc-shaped shift lever 27 and the displacement slide bar 26 form a sliding structure, clamping holes 32 are formed in the outer side of the outer rotating disc 28 and are equidistantly distributed, a spring clamping rod 33 is arranged on the outer side of the outer rotating disc 28, the small motor 31 drives the motor gear 30 to drive the rotating disc 29 and the outer rotating disc 28 to rotate together, the arc-shaped shift lever 27 connected to the outer side of the outer rotating disc 28 rotates together, during the rotation, the clamping holes 32 on the outer side of the outer rotating disc 28 act as a lower limit of the spring clamping rod 33 to decelerate, when the small motor 31 is not driven, outer rotor 28 no longer receives the power drive that turns to for spring screens pole 33 corresponds with the current position, or nearest screens hole 32 block plays the deceleration effect, and this structure utilizes the drive, and when adjustable unmanned aerial vehicle side was influenced by wind-force, unmanned aerial vehicle self balance ability's test, so that test out unmanned aerial vehicle correlation performance, can normally fly under what kind of environmental condition.

Referring to fig. 5, the turning balance testing end 14 includes a turning ring 34, a frame ring 38, lift ejector rods 43, an upper clamping plate 42 and a lower clamping disc 44, the turning ring 34 is fixedly connected to the side of the turning ring end 21, the frame ring 38 is rotatably connected to the side of the turning ring 34, the turning ring 34 is distributed on two sides of the frame ring 38, the lift ejector rods 43 penetrate through the side surfaces of two ends of the frame ring 38, the upper clamping plate 42 is fixedly connected to the end of one lift ejector rod 43, and the lower clamping disc 44 is fixedly connected to the end of the other lift ejector rod 43.

Referring to fig. 5, the inboard of change ring 34 is provided with interior auxiliary roller 35, interior auxiliary roller 35 constitutes to rotate with frame ring 38 and is connected, the arc wall has been seted up in the outside of change ring 34, frame ring 38's both ends side fixedly connected with diaphragm 36, the circular slot has been seted up on the surface of diaphragm 36, be provided with ball 37 under the circular slot of diaphragm 36, ball 37 agrees with the arc slot mutually, ball 37 is in the change ring 34 outside, the resistance that produces when the reduction outer lane that can be fine rotates, auxiliary roller 35 in the 34 inner circles adoption of change ring, can cooperate jointly with ball 37, stable support nature when providing change ring 34 upset, when letting unmanned aerial vehicle overturn and rotate, can be more in the same direction as smooth, in order to reduce the influence of mechanical revolution mechanic to unmanned aerial vehicle test.

Referring to fig. 5 and 6, the upper clamping plate 42 and the lower clamping plate 44 are fixedly connected at both ends thereof with a fixing block 41, a clamping block groove is formed in the side surface of the fixing block 41, the shape of the side surface of the clamping block groove is gradually reduced from both ends to the middle part, a clamping block with the same section shape is arranged at the inner side of the clamping block groove, a sliding guide sheet 40 is fixedly connected to the side surface of the fixing block 41, the sliding guide sheet 40 is slidably connected with a guide rod 39, the guide rod 39 is fixedly connected with the frame ring 38, a contraction rod 45 is fixedly connected to the bottom side surface of the upper clamping plate 42, a suction cup 46 is arranged at the tail end of the contraction rod 45, the upper clamping plate 42 and the lower clamping plate 44 have the same overall structure, when fixing the unmanned aerial vehicle, the suction cup 46 is attached to the body of the unmanned aerial vehicle, air in the suction cup 46 is drawn out through an external suction device, the unmanned aerial vehicle body can be fixed, the contraction rod 45 can be contracted to different unmanned aerial vehicle types, this kind of fixed mode can let the unmanned aerial vehicle wing be in the outside, and the accuracy degree of data collection and information is guaranteed to the interference and the influence of the fixed part of reduction the device that can furthest to unmanned aerial vehicle, when unmanned aerial vehicle continuation of the journey electric quantity is not enough, also can play the guard action to unmanned aerial vehicle simultaneously, avoids the accident of crash to appear in outdoor test.

Referring to fig. 4 and 7, a displacement block groove 47 is formed on the surface of the base seat platform 1, a pulling frame 48 is slidably connected to the inner side of the displacement block groove 47, the other end of the pulling frame 48 is movably connected with the connecting movable joint 3, a sliding block 24 is fixedly connected to the bottom side of one end of the pulling frame 48, a sliding rod 23 is slidably connected to the inner side of the sliding block 24, one end of the sliding rod 23 is fixedly connected with the bottom shaft outer wall 22, the other end of the sliding rod 23 is fixedly connected with a fixed seat plate 25, the fixed seat plate 25 is fixedly connected with the base seat platform 1, a displacement sliding rod 26 is fixedly connected to the bottom end of the sliding rod 24, when the arc-shaped shift lever 27 rotates, the displacement sliding rod 26 is limited by the sliding groove of the arc-shaped shift lever 27 to change the current position, the displacement sliding rod 26 changes the position and is limited by the sliding rod 23, when the displacement sliding rod 26 moves, the connecting movable joint 3 is pulled to deflect by the pulling frame 48 fixed above, and then the turned angle of control connection movable joint 3, control the orientation angle of air current fan 5, the multi-angle is adjusted, can simulate among the real scene, the influence of the wind-force of equidirectional not balancing ability when flying to unmanned aerial vehicle branch, and carry out the contrast experiment with the data that measure when no wind flight state, so that according to the anti wind limit of unmanned aerial vehicle, carry out appropriate adjustment to unmanned aerial vehicle screw and fuselage equilibrium, and convenient reasonable according to experimental data suitably adjust the adjustment

Referring to fig. 8, at least three connecting cover plates 11 are fixedly connected to the inner side of the top fixing ring 10, a connecting plate rod 51 is connected to the intersection of the connecting cover plates 11 in a sliding manner, a top force plate 52 is fixedly connected to the bottom end of the connecting plate rod 51, the connecting plate rod 51 passes through the intersection of the connecting cover plates 11 to form a sliding structure, a force-receiving plate 15 is fixedly connected to the top end of the connecting plate rod 51, at least three pressure detecting sensors 49 are fixedly connected to the bottom surface of the force-receiving plate 15, the pressure detecting sensors 49 are fixedly connected to the connecting cover plates 11, the force-receiving plate 52 is located right above the lift force ejector rods 43, a lift force spring 50 is arranged on the outer side of the connecting plate rod 51, the lift force spring 50 is fixedly connected to the connecting cover plates 11, when the unmanned aerial vehicle ascends the laboratory, the upper clamping plate 42 and the lower clamping plate 44 which fix the unmanned aerial vehicle are used to drive the lift force ejector rods 43 to move vertically upwards, and the lift force ejector rods 43 gradually contact with the bottom of the force plate 52, jacking force dish 52 receives vertical ascending power rebound, finally drives lift spring 50 tensile to let the atress dish 15 pulling pressure detection sensor 49 that links a set pole 51 and connect test, the ascending speed with the decline of unmanned aerial vehicle is calculated out to pressure and the pulling force numerical value that the accessible was surveyed from this, and this kind of mode can be accurate the speed of measuring unmanned aerial vehicle ascending flight.

When in use: firstly, when fixing the unmanned aerial vehicle, the unmanned aerial vehicle is placed between the upper clamping plate 42 and the lower clamping plate 44, the suction cup 46 is attached to the body of the unmanned aerial vehicle, the air in the suction cup 46 is extracted through the external suction device, so that the body of the unmanned aerial vehicle can be fixed, after the two are completely fastened, the grooves formed by oppositely combining the trapezoids on the side surfaces of the upper clamping plate 42 and the lower clamping plate 44 are matched with the blocks with the same shape of the combined surface, then the small motor 31 drives the motor gear 30 to drive the rotating disc 29 and the outer rotating disc 28 to rotate together, the arc deflector rod 27 connected with the outer side of the outer rotating disc 28 rotates together after the rotation, when the arc deflector rod 27 rotates, the displacement slide bar 26 is limited by the sliding groove of the arc deflector rod 27 to change the current position, the displacement slide bar 26 changes the position, the moving direction is limited by the slide bar 23, and the displacement slide bar 26 moves through the pulling frame 48 fixed above, the connecting movable joint 3 is pulled to deflect, the rotating angle of the connecting movable joint 3 is further controlled, the orientation angle of the airflow fan 5 is controlled, the balls 37 are located on the outer side of the overturning ring 34, resistance generated when the outer ring rotates can be well reduced, the inner ring of the overturning ring 34 adopts the inner auxiliary roller 35 which can be matched with the balls 37 together to provide stable support performance when the overturning ring 34 overturns, finally, the azimuth direction is judged by using geomagnetic induction through a direction sensor, data during flying of the unmanned aerial vehicle can be displayed in a data mode when the horizontal beam rod 16 rotates, when the unmanned aerial vehicle ascends a laboratory, the lifting force mandril 43 is driven to vertically move upwards by using the upper clamping plate 42 and the lower clamping plate 44 which are used for fixing the unmanned aerial vehicle, the mandril 43 is gradually contacted with the bottom of the jacking plate 52, the jacking plate 52 is driven to move upwards by vertical upward force, and finally, the lifting force spring 50 is driven to stretch, and let atress dish 15 pulling pressure detection sensor 49 that linking rod 51 is connected test, pressure and pulling force numerical value from this accessible survey calculate unmanned aerial vehicle speed that rises and descend.

The foregoing is only a preferred embodiment of the present invention; the scope of the invention is not limited thereto. Any person skilled in the art should be able to cover the technical scope of the present invention by equivalent or modified solutions and modifications within the technical scope of the present invention.

Claims

1. The utility model provides an indoor adjusting device is used in unmanned aerial vehicle flight test, includes base seat platform (1) the articulated seat of top edge fixedly connected with (2) of base seat platform (1), the both sides of articulated seat (2) are rotated and are connected with and connect movable joint (3), the terminal fixedly connected with of connecting movable joint (3) surveys wind apron (4), the side fixedly connected with air current fan (5) of surveying wind apron (4), the top surface fixedly connected with bracing piece (6) of base seat platform (1), the solid rod end of top fixedly connected with (7) of bracing piece (6), its characterized in that: a track ring (8) is fixedly connected to the side surface of the fixed rod end (7), a support plate (9) is fixedly connected to the outer side surface of the track ring (8), and a top fixed ring (10) is fixedly connected to the top end of the support plate (9);

the inboard of top solid ring (10) is provided with lift pressure detection end (13) that are used for detecting unmanned aerial vehicle lift data, the inboard of track ring (8) is provided with upset balance test end (14) that are used for testing unmanned aerial vehicle upset ability, the inboard of track ring (8) is provided with interior rail arc board (18) that are used for testing unmanned aerial vehicle level and turn to the equilibrium, base seat platform (1) inside is provided with and is used for simulating test flabellum (12) that unmanned aerial vehicle received the decline resistance scene when descending.

2. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: inner ring groove (17) have been seted up to the medial surface of track ring (8), inner ring groove (17) with inner rail arc board (18) sliding connection, the both sides of inner rail arc board (18) are all rotated and are connected with inside groove gyro wheel (19), inside groove gyro wheel (19) with inner ring groove (17) contact laminating, the whole of inner rail arc board (18) is the arc.

3. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: the utility model discloses a track ring, including track ring (8), side intermediate position fixed connection of track ring (8) has horizontal beam pole (16), the side fixedly connected with sublance (20) of horizontal beam pole (16), horizontal beam pole (16) all adopt the polyethylene material with sublance (20), and horizontal beam pole (16) and sublance (20) are hollow structure, the other end fixedly connected with of horizontal beam pole (16) changes solid ring end (21), the internally mounted of horizontal beam pole (16) has direction sensor.

4. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: the overturning balance testing end (14) comprises an overturning ring (34), a frame ring (38), a lifting ejector rod (43), an upper clamping plate (42) and a lower clamping disc (44), wherein the overturning ring (34) is fixedly connected to the side face of the overturning ring end (21), the frame ring (38) is rotatably connected to the side face of the overturning ring (34), the overturning ring (34) is distributed on two sides of the frame ring (38), the lifting ejector rod (43) penetrates through the side faces of the two ends of the frame ring (38), one of the lifting ejector rod (43) is fixedly connected with the upper clamping plate (42), and the other lifting ejector rod (43) is fixedly connected with the lower clamping disc (44).

5. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 4, wherein: the inboard of upset ring (34) is provided with interior auxiliary roller (35), interior auxiliary roller (35) with frame ring (38) constitute and rotate the connection, the arc wall has been seted up in the outside of upset ring (34), the both ends side fixedly connected with diaphragm (36) of frame ring (38), the circular slot has been seted up on the surface of diaphragm (36), be provided with ball (37) under the circular slot of diaphragm (36), ball (37) with the arc groove agrees with mutually.

6. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: go up grip block (42) with the equal fixedly connected with fixed block (41) in both ends of lower grip block (44), the fixture block groove has been seted up to the side of fixed block (41), fixture block groove side shape is dwindled to the middle part width by both ends gradually, fixture block inslot side is provided with the fixture block that cross sectional shape is the same, the side fixedly connected with slip guide plate (40) of fixed block (41), slip guide plate (40) sliding connection has guide bar (39), guide bar (39) with frame ring (38) fixed connection, the end side fixedly connected with shrink pole (45) of going up grip block (42), the end of shrink pole (45) is provided with sucking disc (46), go up grip block (42) with grip block (44) overall structure is the same down.

7. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: the inner side of the top fixing ring (10) is fixedly connected with at least three connecting cover plates (11), the intersection of the connecting cover plate (11) is connected with a connecting disc rod (51) in a sliding way, the bottom end of the connecting disc rod (51) is fixedly connected with a jacking disc (52), the connecting disc rod (51) passes through the intersection of the connecting cover plate (11) and forms a sliding structure with the connecting cover plate, the top end of the connecting disc rod (51) is fixedly connected with a stress disc (15), the bottom surface of the stress disc (15) is fixedly connected with at least three pressure detection sensors (49), the pressure detection sensor (49) is fixedly connected with the connecting cover plate (11), the jacking force disc (52) is positioned right above the lifting force mandril (43), the outer side of the disc connecting rod (51) is provided with a lifting force spring (50), the lifting spring (50) is fixedly connected with the connecting cover plate (11).

8. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 1, wherein: the surface of base seat platform (1) is seted up displacement block groove (47), the inboard sliding connection in displacement block groove (47) has pull frame (48), the other end of pull frame (48) constitutes swing joint with connection movable joint (3), the one end bottom side fixedly connected with sliding block (24) of pull frame (48), the inboard sliding connection of sliding block (24) has slide bar (23), wherein one end fixedly connected with bottom shaft outer wall (22) of slide bar (23), the other end fixedly connected with solid bedplate (25) of slide bar (23), solid bedplate (25) and base seat platform (1) fixed connection, the bottom fixedly connected with displacement slide bar (26) of slide bar (24).

9. The indoor adjusting device for the unmanned aerial vehicle flight test of claim 8, wherein: the gear rack is characterized in that a rotating disc (29) is rotatably connected to the outer side of the bottom end of the bottom shaft outer wall (22), a gear way is formed in the outer side of the rotating disc (29), a motor gear (30) is connected to the outer side of the rotating disc (29) in a meshed mode, a small motor (31) is fixedly connected to the outer side of the bottom shaft outer wall (22), an outer rotating disc (28) is fixedly connected to the outer side of the rotating disc (29), an arc-shaped driving lever (27) is fixedly connected to the outer side of the outer rotating disc (28), the arc-shaped driving lever (27) and a displacement sliding rod (26) form a sliding structure, clamping holes (32) distributed at equal intervals are formed in the outer side of the outer rotating disc (28), and a spring clamping rod (33) is arranged on the outer side of the outer rotating disc (28).