CN212922017U - Unmanned aerial vehicle test platform - Google Patents
Unmanned aerial vehicle test platform Download PDFInfo
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- CN212922017U CN212922017U CN202021927439.6U CN202021927439U CN212922017U CN 212922017 U CN212922017 U CN 212922017U CN 202021927439 U CN202021927439 U CN 202021927439U CN 212922017 U CN212922017 U CN 212922017U
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Abstract
An unmanned aerial vehicle test platform relates to the technical field of test devices and comprises a test bench, a load-carrying support, a linear lifting mechanism, a pulley mechanism and a balancing weight; the linear lifting mechanism is connected with the test bench and can lift in a reciprocating mode along the height direction of the test bench; the top of the linear lifting mechanism is rotatably connected with the load support, and the load support is lifted along with the lifting of the linear lifting mechanism; the bottom of the linear lifting mechanism is connected with the test bench and the balancing weight through the pulley mechanism, so that the balancing weight can be lifted along with the lifting of the linear lifting mechanism. An object of the utility model is to provide an unmanned aerial vehicle test platform to solve the test platform elevating movement who exists to a certain extent and increase extra load and lead to unmanned aerial vehicle simulation flight technical problem true inadequately among the prior art.
Description
Technical Field
The utility model relates to a test device technical field particularly, relates to an unmanned aerial vehicle test platform.
Background
Along with the development of unmanned aerial vehicle technology, unmanned aerial vehicle is more and more extensive in the application of each trade for unmanned aerial vehicle's demand is multiplied. For the reliability that improves unmanned aerial vehicle and flight control system's stability, ensure reliable, the safe flight of unmanned aerial vehicle, often need carry out a large amount of test work at unmanned aerial vehicle research and development in-process.
The existing unmanned aerial vehicle test platform can not simulate the lifting motion of an unmanned aerial vehicle or when the lifting motion of the unmanned aerial vehicle is simulated, the test platform is additionally provided with extra load, so that the simulated flight of the unmanned aerial vehicle is not real enough.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle test platform to solve the test platform elevating movement who exists to a certain extent and increase extra load and lead to unmanned aerial vehicle simulation flight technical problem true inadequately among the prior art.
In order to achieve the above object, the present invention provides the following technical solutions:
an unmanned aerial vehicle test platform comprises a test bench, a load support, a linear lifting mechanism, a pulley mechanism and a balancing weight;
the linear lifting mechanism is connected with the test bench and can lift in a reciprocating mode along the height direction of the test bench;
the top of the linear lifting mechanism is rotatably connected with the load support, and the load support can lift along with the lifting of the linear lifting mechanism; the bottom of the linear lifting mechanism is connected with the test bench and the balancing weight through the pulley mechanism, so that the balancing weight can be lifted along with the lifting of the linear lifting mechanism.
In any of the above technical solutions, optionally, the pulley mechanism includes a lifting pulley, a counterweight guide pulley, and a flexible connecting member; the lifting pulley is arranged at the bottom of the linear lifting mechanism, and the counterweight guide pulley is arranged on the test bench;
the head end of the flexible connecting piece is connected with the test bench, and the tail end of the flexible connecting piece sequentially penetrates through the lifting pulley and the counterweight guide pulley and is connected with the counterweight block.
In any of the above technical solutions, optionally, the height of the counterweight guide pulley is not lower than the height of the lifting pulley;
and/or the pulley mechanism further comprises a head pulley arranged on the test bench; the head end of the flexible connecting piece is provided with a connecting ring; the connecting ring is connected with the sliding groove of the head end pulley.
In any of the above technical solutions, optionally, the unmanned aerial vehicle test platform further includes a limiting member for preventing the lifting pulley from moving downward;
the limiting piece can be fixedly connected to the test bench in a sliding mode;
when the lifting pulley abuts against the limiting part, the load support and the test bench are arranged at intervals.
In any of the above technical solutions, optionally, the top of the linear lifting mechanism is rotatably connected to the load-carrying support through a spherical hinge mechanism;
the spherical hinge mechanism can rotate 360 degrees around the axis of the linear lifting mechanism; and/or, on the axis plane of the linear lifting mechanism, the spherical hinge mechanism can rotate, and the rotation angle of the spherical hinge mechanism is not less than +/-45 degrees.
In any of the above technical solutions, optionally, the ball hinge mechanism includes a ball hinge base portion and a ball portion;
the sphere portion is rotatably arranged in a base groove of the spherical hinge base portion, and the depth of the sphere portion arranged in the base groove is at least 1/2 of the diameter of the sphere portion.
The spherical hinge base part is fixedly connected with the top of the linear lifting mechanism; the top of the sphere is fixedly connected with the load support.
In any of the above technical solutions, optionally, the spherical hinge mechanism is fixedly connected to the top of the linear lifting mechanism through a flange;
and/or the spherical hinge mechanism is fixedly connected with the load-bearing support.
In any of the above technical solutions, optionally, the linear lifting mechanism includes a linear slider and a linear guide rail matched with the linear slider;
the linear sliding block is fixedly connected to the test bench;
the top of the linear guide rail is rotatably connected with the load support, and the bottom of the linear guide rail is connected with the test bench and the balancing weight through the pulley mechanism.
In any of the above technical solutions, optionally, the load support includes a load support body, a load support plate, and a height-adjustable load connection stud;
the load support body is rotatably connected with the top of the linear lifting mechanism;
the top of the load support body is fixedly connected with the load connecting stud;
the top of the load connecting stud is detachably connected with the load supporting plate.
In any of the above technical solutions, optionally, the load support is provided with an external power interface and a wire capable of being connected with an external power source, and the external power interface is connected with the wire;
and/or universal casters and/or directional casters are mounted below the test bench.
The beneficial effects of the utility model mainly lie in:
the utility model provides an unmanned aerial vehicle test platform, including test bench, load support, sharp elevating system, pulley mechanism and balancing weight, through the gravity of the lift balanced sharp elevating system of balancing weight and load support etc. for the gravity of sharp elevating system and load support etc. can not bring extra resistance for the unmanned aerial vehicle in flight, has improved test platform simulation flight authenticity.
In order to make the aforementioned and other objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle test platform provided by an embodiment of the present invention;
fig. 2 is a left side view of the drone test platform shown in fig. 1;
fig. 3 is a schematic view of another view structure of the testing platform of the unmanned aerial vehicle according to the embodiment of the present invention;
FIG. 4 is an enlarged partial view of the components above the table of the test rig shown in FIG. 3;
fig. 5 is a partial enlarged view of the spherical hinge mechanism and the flange provided in the embodiment of the present invention;
fig. 6 is a sectional view taken along a-a of the spherical hinge mechanism and the flange plate shown in fig. 5.
Icon: 100-a test bench; 110-a table top; 120-a cross beam; 130-a stringer; 140-a gantry portion; 150-universal caster wheel; 200-load carrier; 210-load carrier body; 220-load support plate; 230-load carrying connecting studs; 300-a linear lifting mechanism; 310-linear slider; 320-a linear guide rail; 400-a pulley mechanism; 410-a lifting pulley; 420-counterweight guide pulleys; 430-a flexible connection; 440-head end pulley; 500-a balancing weight; 600-a stop; 700-a ball hinge mechanism; 710-a ball hinge base portion; 720-a sphere portion; 800-flange plate; 900-external power interface; 910-conducting wire.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of the embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
Examples
Referring to fig. 1 to 6, an unmanned aerial vehicle test platform is provided in the present embodiment, where fig. 1 is a front view of the unmanned aerial vehicle test platform provided in the present embodiment, fig. 2 is a left view of the unmanned aerial vehicle test platform shown in fig. 1, and fig. 3 is a perspective view of the unmanned aerial vehicle test platform; for better clarity of the structure, fig. 4 is a partial enlarged view of the components above the table top of the test bench shown in fig. 3, fig. 5 is a partial enlarged view of the ball hinge mechanism and the flange plate, and fig. 6 is a sectional view of the ball hinge mechanism and the flange plate shown in fig. 5 taken along the direction a-a.
Referring to fig. 1 to 6, the test platform for the unmanned aerial vehicle provided by the embodiment is used for reliability test and flight control debugging of the unmanned aerial vehicle, and can truly simulate the flight of each attitude of the unmanned aerial vehicle. This unmanned aerial vehicle test platform includes test bench 100, load support 200, sharp elevating system 300, pulley mechanism 400 and balancing weight 500. Load support 200 is used for fixed mounting unmanned aerial vehicle.
The linear elevating mechanism 300 is connected to the test stage 100, and the linear elevating mechanism 300 can be reciprocally elevated in the height direction of the test stage 100. Optionally, the height direction of the test stage 100 is a vertical direction. Alternatively, the linear elevating mechanism 300 is elevated in the vertical direction.
The top of the linear elevating mechanism 300 is rotatably connected to the load-carrying support 200, and the load-carrying support 200 is lifted and lowered along with the lifting and lowering of the linear elevating mechanism 300, so that the unmanned aerial vehicle fixed on the load-carrying support 200 is lifted and lowered along with the lifting and lowering of the linear elevating mechanism 300, or the linear elevating mechanism 300 is lifted and lowered along with the lifting and lowering of the unmanned aerial vehicle.
The bottom of the linear elevating mechanism 300 is connected to the test stage 100 and the weight block 500 through the pulley mechanism 400, so that the weight block 500 is lifted by the elevating of the linear elevating mechanism 300. Through the weight block 500 and the pulley mechanism 400, the linear lifting mechanism 300 can be freely lifted and lowered along with the load-bearing support 200 under the condition of basically no extra load or little extra load.
In this embodiment unmanned aerial vehicle test platform, including test bench 100, load support 200, sharp elevating system 300, pulley mechanism 400 and balancing weight 500, through balancing the gravity of sharp elevating system 300 and load support 200 etc. of the lift of balancing weight 500 for the gravity of sharp elevating system 300 and load support 200 etc. can not bring extra resistance for the unmanned aerial vehicle in flight, has improved test platform simulation flight authenticity.
Referring to fig. 1-3, test rig 100 optionally includes a stage portion 140, a table top 110, a cross beam 120, and a stringer 130. The table top 110 is fixedly installed on the top of the table frame 140, and the cross beam 120 and the longitudinal beam 130 are respectively fixed inside the table frame 140.
Optionally, the load carrier 200 is located above the tabletop 110.
Alternatively, the pulley mechanism 400 and the weight 500 are respectively provided inside the stage part 140.
Optionally, a linear lift mechanism 300 may be rotatably coupled to the load support 200 through the table 110.
Referring to fig. 1-3, in an alternative to this embodiment, a pulley mechanism 400 includes a lifting pulley 410, a counterweight guide pulley 420, and a flexible linkage 430; the lifting pulley 410 is arranged at the bottom of the linear lifting mechanism 300, and the counterweight guide pulley 420 is arranged on the test bench 100; optionally, a counterweight guide pulley 420 is attached to the top of the interior of the gantry portion 140.
The head end of the flexible connecting member 430 is connected to the test stage 100, and the tail end of the flexible connecting member 430 passes through the lifting pulley 410 and the counterweight guide pulley 420 in sequence and is connected to the counterweight 500. Through lift pulley 410, counter weight guide pulley 420 and flexonics piece 430 to make pulley mechanism 400 cooperate with balancing weight 500 better, make the gravity of sharp elevating system 300 and load support 200 etc. can not bring extra resistance for the unmanned aerial vehicle in flight, in order to improve test platform simulation flight authenticity.
Alternatively, the lifting sheave 410 is a movable sheave and the counterweight guide sheave 420 is a fixed sheave.
Alternatively, the flexible linkage 430 is a flexible, wrappable linkage of rope, wire or the like.
In an alternative of this embodiment, the height of the counterweight guide sheave 420 is not lower than the height of the lifting sheave 410; that is, the height of the lifting pulley 410 does not exceed the height of the lifting pulley 410 when the lifting pulley 410 is lifted along with the linear lifting mechanism 300, so that the weight block 500 can better balance the gravity of the linear lifting mechanism 300, the load-carrying support 200 and the like.
Referring to fig. 1, in an alternative to this embodiment, the pulley mechanism 400 further includes a head pulley 440 disposed on the test rig 100; the head end of the flexible connector 430 has a connection ring; the connecting ring is connected with the sliding groove of the head end pulley 440, namely the connecting ring is sleeved with the sliding groove of the head end pulley 440; that is, the head end of the flexible connector 430 is connected to the test rig 100 through the connection ring and head end pulley 440. The head end pulley 440 is connected through a connecting ring, so that the angle of the flexible connecting member 430 is finely adjusted through the swing of the head end pulley 440 when the linear lifting mechanism 300 is lifted, thereby reducing or avoiding the resistance of the flexible connecting member 430 to the linear lifting mechanism 300. Optionally, the connecting ring is a rope sleeve at the head end of the flexible connecting member 430, and the rope sleeve is connected with the sliding groove of the head pulley 440.
Referring to fig. 1 to 6, in an alternative of this embodiment, the unmanned aerial vehicle test platform includes a limiting member 600 for preventing the lifting pulley 410 from moving downward, that is, the limiting member 600 is used for preventing the linear lifting mechanism 300 from moving downward; optionally, the limiting member 600 is a limiting plate, a limiting block, or another structure.
The limiting member 600 is slidably and fixedly connected to the test bench 100; so as to adjust the position of the position limiting member 600 on the test stage 100. Optionally, the longitudinal beam 130 of the test bench 100 is provided with a limiting sliding groove, the limiting member 600 can be fixedly connected with the longitudinal beam 130 through the limiting sliding groove, and the limiting member 600 can move up and down along the limiting sliding groove.
When the lifting pulley 410 abuts against the stopper 600, the load bracket 200 is spaced apart from the test stage 100. I.e., the load cradle 200 is at a distance from, and does not contact, the test rig 100. Through locating part 600 to guarantee that unmanned aerial vehicle does not collide with test bench 100 when moving in the specified stroke within range on the vertical direction, avoid unmanned aerial vehicle to damage. Optionally, when the lifting pulley 410 abuts against the limiting member 600, the load support 200 is spaced from the table top 110 of the test bench 100 and has a certain distance, so as to avoid collision between the unmanned aerial vehicle and the table top 110 when the unmanned aerial vehicle moves in a specified stroke range in the vertical direction, and avoid damage to the unmanned aerial vehicle.
Referring to fig. 1-6, in an alternative embodiment, the top of the linear lift mechanism 300 is pivotally connected to the load support 200 by a ball-and-socket joint mechanism 700. Through ball pivot mechanism 700 to make load support 200 can rotate in a flexible way, and then can make the nimble test flight of unmanned aerial vehicle, in order to improve the authenticity that test platform simulated flight.
Alternatively, the ball-and-socket mechanism 700 can be rotated 360 ° about the axis of the linear lift mechanism 300.
Alternatively, on the axial plane of the linear elevating mechanism 300, that is, on the vertical plane, the ball hinge mechanism 700 can rotate and the rotation angle of the ball hinge mechanism 700 is not less than ± 45 °. Wherein the axial plane is a plane having the axis of the linear elevating mechanism 300. The rotation angle of the spherical hinge mechanism 700 on the axial plane of the linear lifting mechanism 300 is not less than +/-45 degrees so as to increase the swing angle of the load support 200 along with the unmanned aerial vehicle and truly simulate the flight of the unmanned aerial vehicle.
In this embodiment unmanned aerial vehicle test platform has balanced the gravity of sharp elevating system 300, load support 200 and spherical hinge mechanism 700 etc. through balancing weight 500's lift for the gravity of sharp elevating system 300, load support 200 and spherical hinge mechanism 700 etc. can not bring extra resistance for the unmanned aerial vehicle in flight, has improved test platform simulation flight authenticity. Through the spherical hinge mechanism 700 with a large swing angle, the reality of the simulated flight of the unmanned aerial vehicle test platform is further improved.
Unmanned aerial vehicle test platform passes through sharp elevating system 300 and spherical hinge mechanism 700 to make load support 200 along with unmanned aerial vehicle can carry out the motion of four degrees of freedom, can realize the flight of each attitude angle of unmanned aerial vehicle, greatly improved test platform simulation flight authenticity.
Referring to fig. 5 and 6, in an alternative to the present embodiment, a ball-hinge mechanism 700 includes a ball-hinge base portion 710 and a ball portion 720.
The ball hinge base part 710 is fixedly connected with the top of the linear lifting mechanism 300; the top of the ball portion 720 is fixedly connected to the load bracket 200.
The rotatable setting of spheroid portion 720 is in the base recess of ball pivot base portion 710, and the degree of depth that spheroid portion 720 sets up in the base recess is 1/2 of spheroid portion 720 diameter at least to increase the swing angle of spheroid portion 720 in the base recess of ball pivot base portion 710, and then increase load support 200 along with unmanned aerial vehicle's swing angle.
Referring to fig. 1 to 6, in an alternative embodiment, a spherical hinge mechanism 700 is fixedly connected to the top of the linear lifting mechanism 300 through a flange plate 800; optionally, the spherical hinge mechanism 700 is screwed with the top of the linear lifting mechanism 300 through the flange plate 800; the flange plate 800 is used to improve the connection firmness of the spherical hinge mechanism 700 and the linear lifting mechanism 300.
Optionally, the ball-joint mechanism 700 is fixedly connected to the load-bearing support 200. Optionally, the ball-and-socket joint mechanism 700 is bolted to the load carrier 200.
Referring to fig. 1 to 3, in an alternative of the present embodiment, a linear elevating mechanism 300 includes a linear slider 310 and a linear guide 320 engaged with the linear slider 310; optionally, the linear slide 310 is sleeved on the outer circumference of the linear guide 320.
The linear slider 310 is fixedly connected to the test stage 100; optionally, the linear slide 310 is fixedly attached to the longitudinal beam 130.
The top of the linear guide 320 is rotatably connected to the load-bearing bracket 200, and the bottom of the linear guide 320 is connected to the test stage 100 and the weight block 500 through the pulley mechanism 400. Optionally, the bottom of the linear guide 320 connects the test rig 100 and the counterweight 500 via a lifting pulley 410. Through straight line slider 310 and linear guide 320 to make the lift resistance of straight line elevating system 300 littleer, so that unmanned aerial vehicle receives self gravity and does not have other resistance in vertical direction basically, can be more true simulation unmanned aerial vehicle's flight.
Referring to FIG. 4, in an alternative of this embodiment, the load bracket 200 includes a load bracket body 210, a load support plate 220, and an adjustable height load attachment stud 230.
The load support body 210 is rotatably connected with the top of the linear lifting mechanism 300; optionally, the load carrier body 210 is connected to the linear lift mechanism 300 via a ball joint mechanism 700 and a flange 800.
The top of the load bracket body 210 is fixedly connected with a load connecting stud 230. The load connecting stud 230 may be used directly to fixedly connect the drone.
The top of the load connecting stud 230 is detachably connected to the load support plate 220. The load support plate 220 may be directly used to fixedly connect the drone. Through load stub 230 and load backup pad 220 to connect fixed different unmanned aerial vehicle and test, prevent that unmanned aerial vehicle from appearing unusually in the test process and leading to falling into the machine. When connecting the drone, the load connecting stud 230 or the load support plate 220 may be selected according to the connection position of the drone.
Optionally, the load support plate 220 is fixedly coupled to the load coupling stud 230 by a nut.
Referring to fig. 1 to 6, in an alternative of the present embodiment, the load support 200 is provided with an external power interface 900 and a wire 910 capable of being connected with an external power source, and the external power interface 900 is connected with the wire 910; through external power source interface 900 and wire 910 to can provide the electric energy for unmanned aerial vehicle, and then it is long when improving the unmanned aerial vehicle test, with the requirement that satisfies the long-time reliability flight test of unmanned aerial vehicle.
In the prior art, the test of the unmanned aerial vehicle requires a platform which has low space requirement and can test the posture adjustment capability of the unmanned aerial vehicle. When the existing unmanned aerial vehicle test platform simulates the lifting motion of an unmanned aerial vehicle, the extra load of a mechanism is overlarge, so that the simulated flight of the unmanned aerial vehicle is not real enough; meanwhile, the degree of freedom of an existing unmanned aerial vehicle test platform supporting a flat plate is too low, and the unmanned aerial vehicle test platform is difficult to simulate large attitude angle flight of the unmanned aerial vehicle. In this embodiment unmanned aerial vehicle test platform, test platform's extra load is less when simulation unmanned aerial vehicle elevating movement, and simulation unmanned aerial vehicle flight that can be true, long-time feasibility test can prevent again simultaneously that unmanned aerial vehicle from appearing unusually in the test procedure and leading to falling into the plane.
Referring to fig. 1-6, in an alternative to the present embodiment, a universal caster 150 and/or a directional caster is mounted below the test rig 100; that is, the universal caster 150 is installed under the test stage 100, or the directional caster is installed under the test stage 100, or the universal caster 150 and the directional caster are installed under the test stage 100. Via the casters 150 or directional casters to facilitate movement of the test rig 100.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle test platform is characterized by comprising a test bench, a load-carrying support, a linear lifting mechanism, a pulley mechanism and a balancing weight;
the linear lifting mechanism is connected with the test bench and can lift in a reciprocating mode along the height direction of the test bench;
the top of the linear lifting mechanism is rotatably connected with the load support, and the load support can lift along with the lifting of the linear lifting mechanism; the bottom of the linear lifting mechanism is connected with the test bench and the balancing weight through the pulley mechanism, so that the balancing weight can be lifted along with the lifting of the linear lifting mechanism.
2. An unmanned aerial vehicle test platform as defined in claim 1, wherein the pulley mechanism comprises a lifting pulley, a counterweight guide pulley, and a flexible connection; the lifting pulley is arranged at the bottom of the linear lifting mechanism, and the counterweight guide pulley is arranged on the test bench;
the head end of the flexible connecting piece is connected with the test bench, and the tail end of the flexible connecting piece sequentially penetrates through the lifting pulley and the counterweight guide pulley and is connected with the counterweight block.
3. An unmanned aerial vehicle test platform as claimed in claim 2, wherein the height of the counterweight guide pulley is not less than the height of the lifting pulley;
and/or the pulley mechanism further comprises a head pulley arranged on the test bench; the head end of the flexible connecting piece is provided with a connecting ring; the connecting ring is connected with the sliding groove of the head end pulley.
4. The UAV testing platform of claim 2, further comprising a stop for stopping the lifting pulley from moving downward;
the limiting piece can be fixedly connected to the test bench in a sliding mode;
when the lifting pulley abuts against the limiting part, the load support and the test bench are arranged at intervals.
5. An unmanned aerial vehicle test platform as claimed in any one of claims 1-4, wherein the top of the linear elevating mechanism is rotatably connected to the load-carrying support via a ball-and-socket joint mechanism;
the spherical hinge mechanism can rotate 360 degrees around the axis of the linear lifting mechanism; and/or, on the axis plane of the linear lifting mechanism, the spherical hinge mechanism can rotate, and the rotation angle of the spherical hinge mechanism is not less than +/-45 degrees.
6. An unmanned aerial vehicle test platform as claimed in claim 5, wherein the ball-hinge mechanism comprises a ball-hinge base portion and a ball portion;
the sphere part is rotatably arranged in a base groove of the spherical hinge base part, and the depth of the sphere part arranged in the base groove is at least 1/2 of the diameter of the sphere part;
the spherical hinge base part is fixedly connected with the top of the linear lifting mechanism; the top of the sphere is fixedly connected with the load support.
7. An unmanned aerial vehicle test platform according to claim 5, wherein the spherical hinge mechanism is fixedly connected with the top of the linear lifting mechanism through a flange plate;
and/or the spherical hinge mechanism is fixedly connected with the load-bearing support.
8. An unmanned aerial vehicle test platform as claimed in any one of claims 1-4, wherein the linear lift mechanism comprises a linear slide and a linear guide cooperating with the linear slide;
the linear sliding block is fixedly connected to the test bench;
the top of the linear guide rail is rotatably connected with the load support, and the bottom of the linear guide rail is connected with the test bench and the balancing weight through the pulley mechanism.
9. An unmanned aerial vehicle test platform as claimed in any of claims 1-4, wherein the load support comprises a load support body, a load support plate and a height adjustable load connection stud;
the load support body is rotatably connected with the top of the linear lifting mechanism;
the top of the load support body is fixedly connected with the load connecting stud;
the top of the load connecting stud is detachably connected with the load supporting plate.
10. An unmanned aerial vehicle test platform according to any one of claims 1-4, wherein the load support is provided with an external power interface and a wire capable of being connected with an external power supply, and the external power interface is connected with the wire;
and/or universal casters and/or directional casters are mounted below the test bench.
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| CN202021927439.6U CN212922017U (en) | 2020-09-04 | 2020-09-04 | Unmanned aerial vehicle test platform |
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| CN202021927439.6U CN212922017U (en) | 2020-09-04 | 2020-09-04 | Unmanned aerial vehicle test platform |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230052429A1 (en) * | 2021-08-06 | 2023-02-16 | Shanghai Autoflight Co., Ltd. | Unmanned Aerial Vehicle (UAV) Test Bench |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230052429A1 (en) * | 2021-08-06 | 2023-02-16 | Shanghai Autoflight Co., Ltd. | Unmanned Aerial Vehicle (UAV) Test Bench |
| US11674867B2 (en) * | 2021-08-06 | 2023-06-13 | Shanghai Autoflight Co., Ltd. | Unmanned aerial vehicle (UAV) test bench |
| US20230288292A1 (en) * | 2021-08-06 | 2023-09-14 | Shanghai Autoflight Co., Ltd. | Method of Testing an Unmanned Aerial Vehicle (UAV) Using a Test Bench |
| US11982588B2 (en) * | 2021-08-06 | 2024-05-14 | Shanghai Autoflight Co., Ltd. | Method of testing an unmanned aerial vehicle (UAV) using a test bench |
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