Simulation device for simulating flight attitude of unmanned aerial vehicle

Abstract

The utility model relates to a simulation device for simulating the flight attitude of an unmanned aerial vehicle. The upper end face of the main counterweight table is provided with a bearing shaft and connected with a positioning table through the bearing shaft. The upper end face of the main counterweight table is provided with a plurality of counterweight adjusting assemblies around the center of the main counterweight table. According to the simulation device for simulating the flight attitude of the unmanned aerial vehicle, a plurality of balancing weight bodies arranged on a main balancing weight table can be linearly moved and adjusted; compared with a balance weight fixedly arranged in a citation file, the flight simulation device can allow the unmanned aerial vehicle body to adjust the position of the balance weight according to different flight attitudes and load changes by moving and adjusting the balance weight body, so that flight balance and stability are kept. Meanwhile, by adjusting the position of the balancing weight body, the balancing weight can better adapt to the gravity center position of the unmanned aerial vehicle body in different flight attitudes, so that the flight stability and maneuverability are improved, and the flight attitude simulation data accuracy of the unmanned aerial vehicle body is further enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and specifically relates to a simulation device for simulating the flight attitude of an unmanned aerial vehicle. Background Technique

[0002] An unmanned aerial vehicle (UAV) is an aircraft that can fly without a human pilot. It can cover various types of aircraft, including fixed-wing aircraft, multi-rotor aircraft, and rotorcraft. An unmanned aerial vehicle usually consists of a flight control system, sensors, a communication system, and an engine. The unmanned aerial vehicle can be operated through remote control or a pre-set autonomous flight path; unmanned aerial vehicles have a wide range of applications in military, civilian, and commercial fields, including but not limited to reconnaissance, surveillance, aerial photography, agricultural operations, emergency rescue, scientific research, and cargo transportation. Due to its flexibility and versatility, unmanned aerial vehicles have received increasing attention and applications in various fields.

[0003] Unmanned aerial vehicle flight hover simulation refers to using a simulator or simulation software to simulate the flight state and operation of an unmanned aerial vehicle hovering in the air. This simulation can be carried out on computer software or specialized hardware devices to help pilots practice and familiarize themselves with the operation skills of an unmanned aerial vehicle in the hovering state.

[0004] In a Chinese published patent with a patent number of CN203616587U, it points out a test platform for a rotorcraft with limit protection. In this cited patent, through the mutual cooperation of a base connecting plate, a base arm, a support rod, a spherical bearing, a cross connecting frame, a rod clamping part, and a limit sleeve, an attitude control experiment is effectively carried out, and the maximum deflection angle during the attitude test of the rotorcraft is limited to ensure the safety of the test.

[0005] In the actual use of the above-cited document, although the maximum deflection angle during the attitude test of the rotorcraft is limited, it still has certain disadvantages, that is, it is difficult for the rotorcraft in this cited document to perform large-angle pitch flight simulation and hover and lift flight at different height positions on the test platform, resulting in insufficient simulation data of the aircraft;

[0006] At the same time, as shown in a Chinese published patent with the patent number CN219970003U, although this cited document solves the problem of multi-attitude flight simulation of drones and realizes the stable flight simulation of drones in the hovering attitude, the weight range in this protection structure is difficult to be adaptively adjusted according to the change of the flight attitude of the drone, and the fixedly arranged counterweight blocks limit the adjustment ability of the simulated flight attitude of the drone; when the drone makes attitude adjustments, the fixedly arranged counterweight blocks make it impossible to flexibly adapt to these attitude changes, thus increasing the risk of the simulation device tipping over. At the same time, drones of different sizes require more stable counterweight support during hovering flight simulation. The fixedly arranged counterweight blocks are cumbersome to adjust, and the flight simulation devices in the above two patent documents are difficult to quickly limit different sizes of drones, resulting in difficult rapid positioning of drones during flight simulation. Therefore, a simulation device for simulating the flight attitude of drones is proposed to solve the above problems. Summary of the Utility Model

[0007] Aiming at the deficiencies of the prior art, the utility model provides a simulation device for simulating the flight attitude of drones, which has the advantages of diverse flight postures, stable flight attitude simulation, and adaptability to the flight simulation of drones of different sizes, and solves the problems of easy tipping over in traditional flight attitude simulation, unstable flight attitude simulation, and inconvenient rapid assembly of drones of different models.

[0008] To achieve the above object, the utility model provides the following technical solution: A simulation device for simulating the flight attitude of drones, comprising: a main counterweight platform;

[0009] A load-bearing shaft is arranged on the upper end surface of the main counterweight platform and is connected with a positioning platform through the load-bearing shaft;

[0010] A number of counterweight adjustment components are arranged around the center of the upper end surface of the main counterweight platform;

[0011] A load-bearing column is fixedly arranged at the center of the upper end surface of the positioning platform. A screw-driven universal ball is rotatably arranged in the load-bearing column and is rotatably connected with a main rod through the screw-driven universal ball; A flight traction rod is slidably arranged in the main rod;

[0012] A connecting seat is installed on the upper end surface of the flight traction rod. A drone quick-release component is carried on the upper end surface of the connecting seat and is connected with a drone body through the drone quick-release component;

[0013] A connecting block is fixedly arranged at the bottom of the drone body.

[0014] Further, each of the number of counterweight adjustment components includes two positioning base platforms arranged on the upper end surface of the main counterweight platform. Positioning bushings are fixedly arranged on both of the two positioning base platforms, and a connecting screw is threadedly connected between the two positioning bushings.

[0015] Furthermore, the counterweight adjustment assembly further includes a mounting seat disposed on the upper end surface of the main counterweight platform. A threaded sleeve is mounted on the side surface of the mounting seat, and a threaded wire is disposed inside the threaded sleeve; one end of the connecting screw rod penetrates through the positioning bushing and extends to be threadedly connected with the threaded sleeve.

[0016] Furthermore, an adjustment seat is mounted on the mounting seat. Two ball bearings are assembled on the adjustment seat. A threaded lead screw is rotatably disposed between the two ball bearings. A slider seat is externally engaged with the threaded lead screw; a chute is formed on the lower end surface of the mounting seat, and the lower end surface of the slider seat penetrates through the chute and extends to be connected with a counterweight body.

[0017] Furthermore, two side rods are mounted on the adjustment seat. The two side rods are parallel to each other and are disposed on both sides of the slider seat and both penetrate through the slider seat; a reciprocating motor is assembled on one side of the mounting seat, and the output end of the reciprocating motor penetrates through the adjustment seat and is connected with one end of the threaded lead screw.

[0018] Furthermore, the UAV quick-release assembly includes a positioning bottom plate disposed on the upper end surface of the connecting seat. A positioning seat is disposed on the upper end surface of the positioning bottom plate. The positioning seat is arranged in a rectangular box shape and has an opening on one side; four limiting blocks are disposed on the inner bottom wall of the positioning seat. The four limiting blocks are arranged in a rectangular distribution, and a positioning pin is threadedly connected to each limiting block. The positioning pin penetrates through the limiting block and is threadedly connected with the positioning bottom plate; a clamping plate is disposed on each side of the upper end surface of the positioning seat. The two clamping plates are arranged in a U shape and the openings on both sides are oppositely arranged. Positioning bolts are threadedly connected to both clamping plates; the connecting block is fitted between the four limiting blocks.

[0019] Compared with the prior art, the technical solution of the present application has the following beneficial effects:

[0020] In actual use of this simulation device for simulating the flight attitude of a UAV, through the mutual movement cooperation of multiple structures in multiple sets of counterweight adjustment assemblies provided, when the UAV body performs flight attitude simulation, several counterweight bodies arranged on the main counterweight platform can perform linear movement adjustment; compared with the fixed counterweights in the cited documents, the flight simulation device of the present application adjusts the position of the counterweight body through movement adjustment, so that the UAV body can adjust the counterweight position according to different flight attitudes and load changes, thereby maintaining flight balance and stability. At the same time, by adjusting the position of the counterweight body, it is possible to better adapt to the center of gravity position of the UAV body in different flight attitudes, thereby improving flight stability and handling performance, and further enhancing the accuracy of the flight attitude simulation data of the UAV body.

[0021] In actual use, the simulation device for simulating the flight attitude of an unmanned aerial vehicle (UAV) enables quick assembly of UAV bodies of different sizes on the UAV quick-release assembly through the mutual movement and cooperation of multiple structures within the UAV quick-release assembly and the clamping cooperation between the connection block and the UAV quick-release assembly. Compared with the flight simulation device in the cited document, the flight simulation device of the present application can quickly replace and assemble UAV bodies of different sizes and models through the provided UAV quick-release assembly, enabling flexible selection of different UAV bodies for simulation during flight attitude simulation, thus achieving diverse flight attitude simulations. At the same time, through quick clamping, real-time adjustment and testing of different flight parameters and simulation scenarios can be achieved in a short time. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 FIG. is a schematic diagram of the overall installation structure of the present utility model;

[0023] Figure 2 FIG. is a schematic diagram of the installation structure of the weight adjustment assembly of the present utility model on the main weight platform;

[0024] Figure 3 FIG. is a schematic diagram of the overall installation structure of the weight adjustment assembly of the present utility model;

[0025] Figure 4 FIG. is a schematic diagram of the separation structure between the UAV quick-release assembly and the UAV body of the present utility model.

[0026] In the figures: 1, main weight platform; 2, positioning platform; 3, weight adjustment assembly; 31, positioning seat; 32, positioning bushing; 33, connecting screw; 34, mounting seat; 35, threaded sleeve; 36, adjusting seat; 37, ball bearing; 38, threaded lead screw; 39, slider seat; 310, chute; 311, weight block body; 312, side rod; 313, reciprocating motor; 4, load-bearing column; 5, universal ball with screw; 6, main rod; 7, flight traction rod; 71, connecting seat; 8, UAV quick-release assembly; 81, positioning base plate; 82, positioning seat; 83, clamping plate; 84, positioning bolt; 85, limiting block; 86, positioning dowel pin; 9, UAV body; 91, connection block. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0028] Please refer to Figures 1-4, A simulation device for simulating the flight attitude in this embodiment includes a main counterweight platform 1;

[0029] A load-bearing shaft is provided on the upper end surface of the main counterweight platform 1, and a positioning platform 2 is connected through the load-bearing shaft;

[0030] A number of counterweight adjustment components 3 are arranged around the center of the upper end surface of the main counterweight platform 1;

[0031] A load-bearing column 4 is fixedly provided at the center of the upper end surface of the positioning platform 2. A screw-driven universal ball 5 is rotatably arranged in the load-bearing column 4, and a main rod 6 is rotatably connected through the screw-driven universal ball 5; A flight traction rod 7 is slidably arranged in the main rod 6;

[0032] A connecting seat 71 is installed on the upper end surface of the flight traction rod 7. A drone quick-release component 8 is carried on the upper end surface of the connecting seat 71, and a drone body 9 is connected through the drone quick-release component 8;

[0033] A connecting block 91 is fixedly provided at the bottom of the drone body 9.

[0034] In this embodiment, through the mutual movement and cooperation of multiple structures in the multiple groups of counterweight adjustment components 3 provided, when the drone body 9 simulates the flight attitude, a number of counterweight block bodies 311 arranged on the main counterweight platform 1 can be linearly moved and adjusted; Compared with the fixed counterweights in the cited document, the flight simulation device of the present application adjusts the position of the counterweight block body 311, so that the drone body 9 can adjust the counterweight position according to different flight attitudes and load changes, thereby maintaining flight balance and stability. At the same time, by adjusting the position of the counterweight block body 311, it is possible to better adapt to the center of gravity position of the drone body 9 in different flight attitudes, thereby improving flight stability and handling performance, and further enhancing the accuracy of the flight attitude simulation data of the drone body 9.

[0035] Furthermore, through the mutual movement and cooperation of multiple structures in the drone quick-release component 8 provided, under the clamping cooperation between the connecting block 91 and the drone quick-release component 8, drone bodies 9 of different sizes can be quickly assembled on the drone quick-release component 8; Compared with the flight simulation device in the cited document, the flight simulation device of the present application can quickly replace and assemble drone bodies 9 of different sizes and models through the provided drone quick-release component 8, so that different drone bodies 9 can be flexibly selected for simulation in the flight attitude simulation, thereby realizing diverse flight attitude simulations. At the same time, through quick clamping, real-time adjustment and testing of different flight parameters and simulation scenarios can be achieved in a short time.

[0036] It should be noted that the counterweight adjustment assembly 3 is electrically controlled. In actual applications, in cooperation with the main counterweight platform 1 set for the main load-bearing of the device, the counterweight range of the set counterweight adjustment assembly 3 can be adjusted in a timely manner according to the flight attitude simulation of the UAV body 9, and at the same time, the counterweight adjustment assembly 3 can adapt to different load conditions. For example, when the UAV body 9 carries different types of sensors or devices, the position of the counterweight can be adjusted to balance the center of gravity of the UAV body 9 to ensure stable flight.

[0037] Please refer to Figures 1-3 , in order to stabilize the overall attitude of the simulation device and prevent the simulation device from tipping over when the UAV body 9 adjusts its attitude, several counterweight adjustment assemblies 3 in this embodiment each include two positioning bases 31 arranged on the upper end surface of the main counterweight platform 1. Positioning sleeves 32 are fixedly provided on both of the two positioning bases 31, and a connecting screw 33 is threadedly connected between the two positioning sleeves 32; the counterweight adjustment assembly 3 further includes a mounting seat 34 arranged on the upper end surface of the main counterweight platform 1. A threaded sleeve 35 is installed on the side of the mounting seat 34, and a threaded wire is arranged inside the threaded sleeve 35; one end of the connecting screw 33 penetrates through the positioning sleeve 32 and extends to be threadedly connected with the threaded sleeve 35; an adjustment seat 36 is installed on the mounting seat 34, and two ball bearings 37 are assembled on the adjustment seat 36. A threaded lead screw 38 is rotatably arranged between the two ball bearings 37, and a slider seat 39 is externally engaged with the threaded lead screw 38; a chute 310 is opened on the lower end surface of the mounting seat 34, and the lower end surface of the slider seat 39 penetrates through the chute 310 and extends to be connected with a counterweight block body 311.

[0038] In this embodiment, during actual adjustment and use, the set counterweight block body 311 can be linearly moved and adjusted within the stroke range of the threaded lead screw 38. Through the movement adjustment of the counterweight block bodies 311 in several groups of counterweight adjustment assemblies 3, the flight simulation device of the present application allows the UAV body 9 to adjust the counterweight position according to different flight attitudes and load changes, so as to maintain flight balance and stability. At the same time, the installation cooperation between the positioning bases 31 and the positioning sleeves 32 arranged on the upper end surface of the main counterweight platform 1 enables the positioning sleeve 32 to provide a more stable installation for the mounting seat 34, so that when the counterweight is adjusted, the overall anti-pulling performance of the set counterweight adjustment assembly 3 is better, so that the counterweight can be better installed, further improving the installation stability of the flight simulation device of the present application.

[0039] Furthermore, in a preferred embodiment, the set positioning base 31 is installed on the main counterweight platform 1 by bolts, and the set adjustment seat 36 is installed on the mounting seat 34 by bolts.

[0040] It should be noted that considering the stability of the UAV body 9 in the flight attitude, and at the same time in order to improve the precise adjustment of the counterweight range, in a preferred embodiment, such as in the embodimentFigure 3 As shown in Figure 3 , two side rods 312 are installed on the adjusting seat 36. The two side rods 312 are arranged in parallel on both sides of the slider seat 39 and both penetrate through the slider seat 39. On one side of the mounting seat 34, a reciprocating motor 313 is assembled. The output end of the reciprocating motor 313 penetrates through the adjusting seat 36 and is connected to one end of the threaded lead screw 38.

[0041] In this embodiment, the provided reciprocating motor 313 can be used to control the rotation of the threaded lead screw 38. The power connection mode of the provided reciprocating motor 313 is prior art, and the control circuit can be realized by simple programming of those skilled in the art, which belongs to the common knowledge in the field. Only its use is involved without modification, so the control method and circuit connection will not be described in detail.

[0042] Further, when the threaded lead screw 38 rotates, it is laterally limited by the two side rods 312 at this time, so that the slider seat 39 engaged with the outside of the threaded lead screw 38 can drive the counterweight body 311 to move linearly along the stroke range of the threaded lead screw 38, and the counterweight body 311 is adjusted by linear movement.

[0043] Please refer to Figures 1-2 、 Figure 4 Figure 4 , in order to quickly assemble the UAV bodies 9 of different models, thereby improving the applicable range of the simulation device of the present application, the UAV quick-release assembly 8 in this embodiment includes a positioning bottom plate 81 arranged on the upper end surface of the connecting seat 71. A positioning seat 82 is arranged on the upper end surface of the positioning bottom plate 81. The positioning seat 82 is arranged in a rectangular box shape and has an opening on one side. Four limiting blocks 85 are arranged on the inner bottom wall of the positioning seat 82. The four limiting blocks 85 are arranged in a rectangular distribution, and a positioning pin 86 is threadedly connected to each limiting block 85. The positioning pin 86 penetrates through the limiting block 85 and is threadedly connected to the positioning bottom plate 81. On both sides of the upper end surface of the positioning seat 82, a clamping plate 83 is respectively arranged. The two clamping plates 83 are arranged in a U shape and the openings on both sides are opposite to each other. A positioning bolt 84 is threadedly connected to each of the two clamping plates 83. The connecting block 91 is fitted between the four limiting blocks 85.

[0044] In this embodiment, by placing the connecting block 91 at the bottom of the UAV body 9 within the surrounding range of the positioning seat 82 and making the connecting block 91 located between the four limiting blocks 85, then the user tightens the positioning bolt 84 until the end of the positioning bolt 84 abuts against the side surface of the connecting block 91. At this time, through the surrounding limit of the connecting block 91 by the limiting blocks 85 and the tight abutment limit of the connecting block 91 by the two positioning bolts 84, the UAV body 9 can be stably installed on the UAV quick-release assembly 8.

[0045] The working principle of the above embodiment is:

[0046] First step, in actual use, the configured counterweight adjustment assembly 3 can be used to cooperate with the main counterweight platform 1 and the positioning platform 2 to adjust the overall counterweight of the flight simulation device. After the counterweight adjustment is completed, the user can then assemble the drone body 9 onto the drone quick-release assembly 8, thereby achieving the installation of the drone body 9 on the flight towing rod 7. At this time, through the universal rotation between the load-bearing column 4 and the screw-equipped universal ball 5, and the sliding connection between the main rod 6 and the flight towing rod 7, when the drone body 9 starts, the user can drive the drone body 9 to perform large-angle pitch flight simulation, multi-directional roll attitude, and hovering attitude simulation flights on the flight attitude simulation device of the present application. At the same time, through the sliding connection between the main rod 6 and the flight towing rod 7, the drone body 9 can also perform a lifting attitude simulation, and at this time, the flight height depends on the maximum extended length between the main rod 6 and the flight towing rod 7.

[0047] Second step, when the drone body 9 is performing hovering flight and flight simulation in other attitudes, the user can adjust the counterweight adjustment assembly 3 to achieve the adjustment of the counterweight range. During this period, the user connects the reciprocating motor 313 to a power source and controls it. Through the rotational connection between the reciprocating motor 313 and the threaded lead screw 38, the threaded lead screw 38 can rotate accordingly. At this time, restricted laterally by the two side rods 312, the slider seat 39 engaged with the outside of the threaded lead screw 38 can drive the counterweight block body 311 to move linearly along the travel range of the threaded lead screw 38, and the counterweight block body 311 is adjusted by linear movement.

[0048] Third step: When the user quickly assembles the drone body 9 using the drone quick-release assembly 8, the user places the connection block 91 at the bottom of the drone body 9 within the surrounding range of the positioning seat 82, and at the same time positions the connection block 91 between the four limit blocks 85. Subsequently, the user tightens the positioning bolt 84 until the end of the positioning bolt 84 abuts against the side of the connection block 91. At this time, through the surrounding limit of the connection block 91 by the limit blocks 85 and the tight abutment limit of the connection block 91 by the two positioning bolts 84, the drone body 9 can be stably installed on the drone quick-release assembly 8. At the same time, through the loosening adjustment of the positioning bolt 84, drone bodies 9 of different sizes and models can be quickly assembled on the drone quick-release assembly 8.

[0049] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A simulation device for simulating the flight posture of an unmanned aerial vehicle, characterized in that: It includes a main counterweight platform (1); The upper end surface of the main counterweight platform (1) is provided with a load-bearing shaft and is connected to a positioning platform (2) via the load-bearing shaft; The upper end surface of the main counterweight platform (1) is provided with a plurality of counterweight adjustment components (3) around the center of the circle; A load-bearing column (4) is fixedly provided at the center of the upper end surface of the positioning platform (2); a universal ball with a screw (5) is rotatably provided in the load-bearing column (4) and is rotatably connected to a main rod (6) through the universal ball with a screw (5); a flight traction rod (7) is slidably provided in the main rod (6); A connecting seat (71) is installed on the upper end surface of the flight traction rod (7), and a UAV quick-release assembly (8) is carried on the upper end surface of the connecting seat (71) and is connected to a UAV body (9) via the UAV quick-release assembly (8); A connecting block (91) is fixedly provided at the bottom of the drone body (9).

2. The device for simulating the flight posture of an unmanned aerial vehicle according to claim 1, characterized in that: The plurality of counterweight adjustment assemblies (3) each comprise two positioning bases (31) arranged on the upper end surface of the main counterweight platform (1), a positioning sleeve (32) being fixedly provided on the two positioning bases (31), and a connecting screw (33) being threadedly connected between the two positioning sleeves (32).

3. The device for simulating the flight posture of an unmanned aerial vehicle according to claim 2, characterized in that: The counterweight adjustment assembly (3) further comprises a mounting seat (34) arranged on the upper end surface of the main counterweight platform (1), a threaded sleeve (35) being mounted on the side of the mounting seat (34), and a threaded line being arranged inside the threaded sleeve (35); one end of the connecting screw (33) passes through the positioning sleeve (32) and extends to be threadedly connected with the threaded sleeve (35).

4. The device for simulating the flight posture of an unmanned aerial vehicle according to claim 3, characterized in that: An adjusting seat (36) is installed on the mounting seat (34), and two ball bearings (37) are assembled on the adjusting seat (36). A threaded screw (38) is rotatably arranged between the two ball bearings (37), and a slider seat (39) is meshed with the outside of the threaded screw (38); a sliding groove (310) is provided on the lower end surface of the mounting seat (34), and the lower end surface of the slider seat (39) passes through the sliding groove (310) and is extended to be connected with a counterweight block body (311).

5. The device for simulating the flight posture of an unmanned aerial vehicle according to claim 4, characterized in that: Two side rods (312) are installed on the adjustment seat (36), and the two side rods (312) are arranged in parallel on both sides of the slider seat (39) and both penetrate the slider seat (39); a reciprocating motor (313) is assembled on one side of the mounting seat (34), and the output end of the reciprocating motor (313) penetrates the adjustment seat (36) and is connected to one end of the threaded screw (38).

6. The device for simulating the flight posture of an unmanned aerial vehicle according to claim 1, characterized in that: The drone quick-release assembly (8) comprises a positioning base plate (81) arranged on the upper end surface of the connecting seat (71), the upper end surface of the positioning base plate (81) is provided with a positioning seat (82), the positioning seat (82) is arranged in a rectangular box body and has an opening on one side; the inner bottom wall of the positioning seat (82) is provided with four limit blocks (85), the four limit blocks (85) are arranged in a rectangular distribution, and each of the limit blocks (85) is threadedly connected with a positioning screw (86), the positioning screw (86) passes through the limit block (85) and is threadedly connected with the positioning base plate (81); a clamping plate (83) is respectively arranged on both sides of the upper end surface of the positioning seat (82), the two clamping plates (83) are arranged in a U shape and the openings on both sides are arranged opposite to each other, and the two clamping plates (83) are threadedly connected with a positioning bolt (84); the connecting block (91) is embedded between the four limit blocks (85).

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