CN217805335U - Unmanned aerial vehicle balance test device - Google Patents
Unmanned aerial vehicle balance test device Download PDFInfo
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- CN217805335U CN217805335U CN202222031389.9U CN202222031389U CN217805335U CN 217805335 U CN217805335 U CN 217805335U CN 202222031389 U CN202222031389 U CN 202222031389U CN 217805335 U CN217805335 U CN 217805335U
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Abstract
The utility model provides an unmanned aerial vehicle balance test device, which comprises a fixing plate and i, fixed plate bottom centre of a circle symmetry is fixed with four support columns, and is equipped with four magnetic induction mechanism of group bottom the fixed plate, the fixation clamp is installed at magnetic induction mechanism top, and the fixed plate bottom corresponds four magnetic induction mechanism's of group position and installs the controller, the fixed plate outside is equipped with the fan, through the position that control electric putter goes up and down to change the fan to the influence of the air current of test different wind direction to unmanned aerial vehicle, for prior art, through the change that utilizes the wire electric current under magnetic field environment, the position of magnetic column is the relative height of each wing direction of surface unmanned aerial vehicle when unmanned aerial vehicle flies, can make clear the equilibrium condition under the unmanned aerial vehicle flight state through detecting each difference in height, test operation is simple and convenient, and the test effect is good, improves the precision, and can test to the balance degree when meeting with the air current under the unmanned aerial vehicle flight state.
Description
Technical Field
The utility model relates to a test equipment technical field specifically is an unmanned aerial vehicle balance test device.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Compared with piloted planes, unmanned planes can be classified into military and civil applications according to application fields. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-photographing, express transportation, disaster rescue, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, and the application of the unmanned aerial vehicle is greatly expanded.
At present, after the unmanned aerial vehicle is produced and assembled, quality sampling inspection needs to be carried out, a balance test is one of detection items, the balance test at present mostly depends on balance under static conditions, the balance condition of the unmanned aerial vehicle in an actual flight state cannot be scientifically and effectively detected, and the balance degree of the unmanned aerial vehicle cannot be tested when the unmanned aerial vehicle encounters air flow in the actual flight process.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a balanced testing arrangement of unmanned aerial vehicle to solve the problem that proposes in the above-mentioned background art, the utility model discloses novel structure drives the fan through the pulley and removes the influence of equidirectional air current to unmanned aerial vehicle flight state equilibrium degree in the simulated air around first ring channel surrounding type, detects the balanced condition under the unmanned aerial vehicle flight state through magnetic induction mechanism.
In order to achieve the above purpose, the present invention is realized by the following technical solution: the utility model provides an unmanned aerial vehicle balance testing arrangement, includes the fixed plate, fixed plate bottom centre of a circle symmetry is fixed with four support columns, and is equipped with four groups of magnetic induction mechanism bottom the fixed plate, the fixation clamp is installed at magnetic induction mechanism top, and the fixed plate bottom corresponds four groups of magnetic induction mechanism's position and installs the controller, the fixed plate outside is equipped with the fan, and the fan can be followed the fixed plate and be the centre of a circle motion.
Furthermore, magnetic induction mechanism includes the sleeve pipe, the sleeve pipe is fixed on fixed plate top surface, and the sleeve pipe top is fixed with the pullover post, the sleeve pipe is pegged graft with pullover post inside slip and is had the bracing piece, and bracing piece top and mount fixed connection, the fixed magnetic pillar that has cup jointed in bracing piece bottom, the position that the intraductal wall of sleeve corresponds the magnetic pillar is fixed with a plurality of magnetic rings.
Furthermore, a plurality of second annular grooves have been seted up to the inside equidistance of cover head post, and the inside slip joint of second annular groove has a plurality of balls, the bracing piece surface and ball sliding contact.
Furthermore, a first annular groove is formed in the side wall of the fixing plate, a sliding block is connected to the position, corresponding to the fan, of the first annular groove in a sliding and clamping mode, a vertical frame is fixed to the outer side of the sliding block, an electric push rod is fixedly mounted at the bottom of one side, away from the fan, of the vertical frame, and the extension end of the electric push rod is fixedly connected with the fan.
Furthermore, the bottom of the vertical frame is rotatably provided with a universal wheel, and the bottom of the universal wheel is flush with the bottom of the support column.
Furthermore, first ring channel inside is fixed with the ring gear, and the slider installs the gear towards ring gear one side inside rotation, gear one side is worn out the slider and is connected with the ring gear meshing, the position fixed mounting that the slider bottom corresponds the gear has micro motor, and micro motor output and gear fixed connection.
Furthermore, an output end connector is fixed at the bottom of the fixing plate and electrically connected with the controller through an electric wire, and the magnetic ring is electrically connected with the controller through an electric wire.
The utility model has the advantages that: the utility model discloses an unmanned aerial vehicle balance testing device, which comprises a fixed plate; a support column; a first annular groove; a ring gear; an output end connector; a controller; a magnetic induction mechanism; a sleeve; a magnetic column; a magnetic ring; a support bar; sleeving a head column; a second annular groove; a ball bearing; a fixing clip; a fan; erecting; an electric push rod; a universal wheel; a slider; a gear; a micro motor.
1. This balanced testing arrangement of unmanned aerial vehicle passes through under the effect of magnetic induction mechanism, be taken from the intraductal upwards removal of cover through bracing piece and magnetic column, receive the electromagnetic induction principle, produce the induced electromotive force, by current detector detection current size, can combine fixed magnetic field length and wire resistance numerical value to obtain the moving distance data of magnetic column, thereby obtain the real-time altitude data of each horn of unmanned aerial vehicle, contrast each altitude value, can judge level or tilt state under the unmanned aerial vehicle flight state.
2. This balanced testing arrangement of unmanned aerial vehicle passes through under the effect of slider, gear and ring gear, drives the vertical frame and surrounds the fixed plate under the effect of universal wheel and be circular motion to can simulate the influence of not equidirectional air current to unmanned aerial vehicle flight state.
3. This balanced testing arrangement of unmanned aerial vehicle changes the position of fan through control electric putter lift to the influence of the air current of different wind directions to unmanned aerial vehicle is tested.
4. This balanced testing arrangement of unmanned aerial vehicle reduces the frictional force of bracing piece and cover first post through the ball to make the bracing piece when reciprocating the resistance littleer, further improved the test accuracy, trompil in the middle of the first post of cover, the bracing piece passes the trompil position, has reduced the diameter that the bracing piece passed the hole from the sleeve pipe, has carried out certain restriction to the bracing piece horizontal direction swing, is favorable to improving the test accuracy.
5. This balanced testing arrangement of unmanned aerial vehicle is for prior art, through the change that utilizes the wire electric current under magnetic field environment, the position of magnetic column is the relative height of each wing direction of surface unmanned aerial vehicle when unmanned aerial vehicle flies, can make clear the balanced condition under the unmanned aerial vehicle flight state through detecting each difference in height, test operation is simple and convenient, test effect is good, improves the precision, and can test to the equilibrium when meeting with the air current under the unmanned aerial vehicle flight state.
Drawings
Fig. 1 is a schematic view of the overall top structure of the unmanned aerial vehicle balance testing device of the present invention;
fig. 2 is a schematic view of the overall bottom structure of the unmanned aerial vehicle balance testing device of the present invention;
fig. 3 is one of the schematic structural diagrams of the magnetic induction mechanism of the balance testing device for unmanned aerial vehicles according to the present invention;
fig. 4 is a second schematic structural view of a magnetic induction mechanism of the unmanned aerial vehicle balance testing device of the present invention;
fig. 5 is the utility model relates to an unmanned aerial vehicle balance test device's slider and first ring channel connection schematic diagram.
In the figure: 1. a fixing plate; 11. a support column; 12. a first annular groove; 13. a ring gear; 14. an output end connector; 15. a controller; 2. a magnetic induction mechanism; 21. a sleeve; 22. a magnetic column; 23. a magnetic ring; 24. a support bar; 25. a sleeve head column; 26. a second annular groove; 27. a ball bearing; 3. a fixing clip; 4. a fan; 41. erecting; 42. an electric push rod; 43. a universal wheel; 44. a slider; 441. a gear; 442. a micro-motor.
Detailed Description
In order to make the utility model realize, the technical means, the creation characteristics, the achievement purpose and the efficacy are easy to understand and understand, the utility model is further explained by combining the specific implementation mode.
Referring to fig. 1 to 5, the present invention provides a technical solution: the utility model provides an unmanned aerial vehicle balance test device, includes fixed plate 1, 1 bottom centre of a circle symmetry of fixed plate is fixed with four support columns 11, and fixed plate 1 bottom is equipped with four groups of magnetic induction mechanism 2, fixation clamp 3 is installed at 2 tops of magnetic induction mechanism, and the position that fixed plate 1 bottom corresponds four groups of magnetic induction mechanism 2 installs controller 15, the fixed plate 1 outside is equipped with fan 4, and fan 4 can be along fixed plate 1 and be centre of a circle motion, the N and the S position of magnetic ring 23 are located the inboard and the outside of magnetic ring 23 respectively, the N and the S position of magnetic column 22 are located the outside and inboard respectively, the magnetic ring 23 is the same with the magnetic pole direction of the relative one side of magnetic column 22, install unmanned aerial vehicle inside four fixation clamps 3, when unmanned aerial vehicle flies, through magnetic induction mechanism 2 effect down, detect the electric current size by the current detector, can combine fixed magnetic field length and wire resistance numerical value to obtain the displacement data of magnetic column 22, thereby obtain the real-time altitude data of each horn of unmanned aerial vehicle, contrast each altitude value, can judge the level or the tilt state under the unmanned aerial vehicle flight state, rotate through control fan 4 around fixed plate 1 afterwards, simulate the air current in fixed plate, thereby detect the different flight stability under the unmanned aerial vehicle.
In this embodiment, the magnetic induction mechanism 2 includes the sleeve pipe 21, the sleeve pipe 21 is fixed on the surface of the top of the fixed plate 1, and the top of the sleeve pipe 21 is fixed with the pullover post 25, the sleeve pipe 21 and the pullover post 25 are internally inserted and connected in a sliding manner to form the support rod 24, and the top of the support rod 24 is fixedly connected with the fixing frame, the magnetic post 22 is fixedly connected to the bottom of the support rod 24, the inner wall of the sleeve pipe 21 is fixed with a plurality of magnetic rings 23 corresponding to the magnetic post 22, the bottom of the fixed plate 1 is fixed with the output end connector 14, and the output end connector 14 is electrically connected with the controller 15 through an electric wire, the magnetic rings 23 are electrically connected with the controller 15 through an electric wire, when the unmanned aerial vehicle flies and floats, the support rod 24 is taken up to move upwards from the sleeve pipe 21, the magnetic post 22 connected to the bottom of the support rod 24 is synchronously driven to move, when the magnetic post 22 moves, the magnetic post is subjected to the electromagnetic induction principle to generate induced electromotive force, the current is detected by the current detector, that the fixed magnetic field length and the wire resistance value can be combined to obtain the moving distance data of the magnetic post 22, thereby obtaining the real-time height data of each arm of the unmanned aerial vehicle, and comparing each altitude value, and judging the level or the inclined state of the unmanned aerial vehicle.
This embodiment, a plurality of second annular grooves 26 have been seted up to the inside equidistance of pullover post 25, and the inside slip joint of second annular groove 26 has a plurality of balls 27, 24 surfaces of bracing piece and 27 sliding contact of ball, ball 27 reduce the frictional force of bracing piece 24 and pullover post 25 to make bracing piece 24 resistance when reciprocating littleer, further improved the test accuracy, trompil in the middle of pullover post 25, bracing piece 24 passes the trompil position, reduced the diameter that bracing piece 24 passed the hole from sleeve pipe 21, certain restriction has been carried out to the swing of bracing piece 24 horizontal direction, be favorable to improving the test accuracy.
In this embodiment, first annular groove 12 has been seted up on the lateral wall of fixed plate 1, and the inside position slip joint that corresponds fan 4 of first annular groove 12 has slider 44, the slider 44 outside is fixed with perpendicular frame 41, the one side bottom fixed mounting that perpendicular frame 41 kept away from fan 4 has electric putter 42, and electric putter 42's extension end and fan 4 fixed connection, perpendicular frame 41 bottom is rotated and is installed universal wheel 43, and universal wheel 43 bottom and support column 11 bottom keep flushing, first annular groove 12 is inside to be fixed with ring gear 13, and slider 44 is installed towards ring gear 13 one side inside rotation gear 441, slider 44 is worn out to gear 441 one side and is connected with ring gear 13 meshing, slider 44 bottom corresponds the position fixed mounting of gear 441 and has micro motor 442, and micro motor 442 output and gear 441 fixed connection open micro motor 442, micro motor 442 drives gear 441 to rotate, gear 441 and ring gear 13 combine, and because under slider 44 and the effect of first annular groove 12 slip joint, slider 44 drives frame 41 and makes the circular motion under the effect of universal wheel 43 under the fixed plate 1 to can simulate the air current influence of different directions to unmanned aerial vehicle's air current, the unmanned aerial vehicle control through the lift control of unmanned aerial vehicle 4, the lift position is not influenced by the unmanned aerial vehicle.
When the device is used, the unmanned aerial vehicle is installed inside the four fixing clamps 3, when the unmanned aerial vehicle flies and floats, the supporting rod 24 is taken up to move upwards from the sleeve 21, the magnetic column 22 connected to the bottom of the supporting rod 24 is synchronously driven to move, when the magnetic column 22 moves, an induction electromotive force is generated by the electromagnetic induction principle, the current detector detects the magnitude of current, the moving distance data of the magnetic column 22 can be obtained by combining fixed magnetic field length and lead resistance values, so that real-time height data of each arm of the unmanned aerial vehicle can be obtained, the horizontal or inclined state of the unmanned aerial vehicle in the flying state can be judged by comparing the height values, the micro motor 442 is started, the micro motor 442 drives the gear 441 to rotate, the gear 441 is combined with the gear ring 13, and under the sliding clamping action of the sliding block 44 and the first annular groove 12, the sliding block 44 drives the vertical frame 41 to do circular motion around the fixing plate 1 under the action of the universal wheels 43, so that the influence of airflows in different directions on the flying state of the unmanned aerial vehicle can be simulated, the unmanned aerial vehicle can be changed by controlling the lifting of the electric push rod 42, and the influence of airflows in different wind directions on the unmanned aerial vehicle can be tested.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above, it will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, but that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. The utility model provides an unmanned aerial vehicle balance testing device, includes fixed plate (1), its characterized in that: fixed plate (1) bottom centre of a circle symmetry is fixed with four support columns (11), and fixed plate (1) bottom is equipped with four magnetic induction mechanism of group (2), fixation clamp (3) are installed at magnetic induction mechanism (2) top, and the position that fixed plate (1) bottom corresponds four magnetic induction mechanism of group (2) installs controller (15), fixed plate (1) outside is equipped with fan (4), and fan (4) can be followed fixed plate (1) and do the centre of a circle motion.
2. The balance testing device of the unmanned aerial vehicle according to claim 1, wherein: magnetic induction mechanism (2) are including sleeve pipe (21), sleeve pipe (21) are fixed on fixed plate (1) top surface, and sleeve pipe (21) top is fixed with pullover post (25), sleeve pipe (21) and pullover post (25) inside slip are pegged graft and are had bracing piece (24), and bracing piece (24) top and mount fixed connection, bracing piece (24) bottom is fixed to have cup jointed magnetic column (22), the rigidity that sleeve pipe (21) inner wall corresponds magnetic column (22) has a plurality of magnetic rings (23).
3. The balance testing device of the unmanned aerial vehicle according to claim 2, wherein: a plurality of second annular grooves (26) have been seted up to pullover post (25) inside equidistance, and the inside slip joint of second annular groove (26) has a plurality of balls (27), bracing piece (24) surface and ball (27) sliding contact.
4. The balance testing device of the unmanned aerial vehicle according to claim 1, wherein: first ring channel (12) have been seted up on fixed plate (1) lateral wall, and the inside position slip joint that corresponds fan (4) of first ring channel (12) has slider (44), the slider (44) outside is fixed with perpendicular frame (41), one side bottom fixed mounting that fan (4) were kept away from in perpendicular frame (41) has electric putter (42), and electric putter (42)'s extension end and fan (4) fixed connection.
5. The unmanned aerial vehicle balance test device of claim 4, wherein: the bottom of the vertical frame (41) is rotatably provided with a universal wheel (43), and the bottom of the universal wheel (43) is flush with the bottom of the support column (11).
6. The balance testing device of the unmanned aerial vehicle of claim 5, wherein: first ring channel (12) inside is fixed with ring gear (13), and slider (44) install gear (441) towards ring gear (13) one side inside rotation, slider (44) and ring gear (13) meshing connection are worn out to gear (441) one side, the position fixed mounting that corresponds gear (441) in slider (44) bottom has micro motor (442), and micro motor (442) output and gear (441) fixed connection.
7. The balance testing device of the unmanned aerial vehicle according to claim 2, wherein: an output end connector (14) is fixed to the bottom of the fixing plate (1), the output end connector (14) is electrically connected with the controller (15) through an electric wire, and the magnetic ring (23) is electrically connected with the controller (15) through an electric wire.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202222031389.9U CN217805335U (en) | 2022-08-03 | 2022-08-03 | Unmanned aerial vehicle balance test device |
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| CN202222031389.9U CN217805335U (en) | 2022-08-03 | 2022-08-03 | Unmanned aerial vehicle balance test device |
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| CN217805335U true CN217805335U (en) | 2022-11-15 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116659726A (en) * | 2023-07-25 | 2023-08-29 | 安徽羲禾航空科技有限公司 | Aviation propeller thrust measurement equipment and measurement method |
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2022
- 2022-08-03 CN CN202222031389.9U patent/CN217805335U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116659726A (en) * | 2023-07-25 | 2023-08-29 | 安徽羲禾航空科技有限公司 | Aviation propeller thrust measurement equipment and measurement method |
| CN116659726B (en) * | 2023-07-25 | 2023-10-31 | 安徽羲禾航空科技有限公司 | Aviation propeller thrust measurement equipment and measurement method |
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