Compact autonomous exploration unmanned aerial vehicle

Abstract

The utility model discloses a compact autonomous exploration unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a rectangular plate, a flight driving mechanism mounted below the rectangular plate and a shell on the upper surface of the flight driving mechanism, a battery is detachably connected in the shell, and an information processor is integrated on the top of the shell. An inclined plate connected with the rectangular plate is fixed to one side of the machine shell, and a radar and a camera are installed on the inclined plate. The flight control electronic speed controller plate is fixed to the bottom wall of the rectangular plate and located in the middle vacancy of the four flight driving mechanisms, and the flight control electronic speed controller plate is electrically connected with the working end of each flight driving mechanism; the upper portion of the power source distribution plate is fixed in the machine shell and located between the battery and the radar, the power source distribution plate downwards penetrates through the rectangular plate, and the power source distribution plate is electrically connected with the battery and distributes electric power for the information processor, the radar, the camera and the flight control electric adjusting plate. And stable flight can be ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and more specifically to a compact autonomous exploration unmanned aerial vehicle. Background Art

[0002] With the rapid development of drone technology, miniaturization, lightness and high performance have become important trends in drone design. There are still some problems with the existing drone structure:

[0003] (1) Due to the space requirements between various components, the traditional design has a large overall size and a heavy weight, making it difficult to adapt to some application scenarios with high space requirements and not conducive to operation in a small space.

[0004] (2) The spatial layout of UAV designs is often uneven. Due to uneven weight distribution or the mutual influence between components, the UAV may have problems with insufficient stability during flight, affecting flight performance and safety, and reducing the overall performance of the UAV.

[0005] (3) Many drones are designed mainly for outdoor environments and lack the ability to fly stably in indoor environments. This is mainly because there are usually more obstacles, light changes, signal interference, etc. in indoor environments, which limit the indoor flight of drones.

[0006] Therefore, how to provide an autonomous exploration drone with a compact structure, miniaturization and lightweight of the overall structure, while ensuring stable flight is a problem that technical personnel in this field urgently need to solve. Utility Model Content

[0007] In view of this, the utility model provides a compact autonomous exploration UAV, aiming to solve the above technical problems.

[0008] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0009] A compact autonomous exploration drone comprising:

[0010] A rectangular plate, wherein the four corners of the rectangular plate each have a connecting beam extending outwards thereof;

[0011] Flight drive mechanism; the number of the flight drive mechanisms is four, and they are respectively connected to the bottom walls of the rectangular plate and the four connecting beams, and the four flight drive mechanisms are connected to each other;

[0012] A casing, wherein the casing is fixed to the upper surface of the rectangular plate, and a battery is detachably connected therein, an information processor is integrated on the top of the casing, an inclined plate connected to the rectangular plate is fixed on one side of the casing, and a radar and a camera are installed on the inclined plate;

[0013] A flight control and electronic speed control board, which is fixed on the bottom wall of the rectangular plate and located within the middle vacant space of the four flight driving mechanisms. The flight control and electronic speed control board is electrically connected to the working end of each flight driving mechanism.

[0014] A power distribution board, the upper part of which is fixed inside the housing and located between the battery and the radar. The power distribution board passes downward through the rectangular plate. The power distribution board is electrically connected to the battery and distributes power to the information processor, the radar, the camera, and the flight control and electronic speed control board.

[0015] By the above technical solution, the present utility model provides a compact autonomous exploration unmanned aerial vehicle. The flight driving mechanism and the housing are respectively installed below the rectangular plate and on the upper surface, reducing the overall size of the unmanned aerial vehicle. At the same time, the battery, the information processor, the radar, and the camera are integrated on the housing, realizing a high degree of integration among components. Meanwhile, the capabilities of autonomous exploration and obstacle avoidance are achieved, and it can also fly indoors. This structural arrangement has the characteristics of being compact and evenly distributed, which can effectively ensure the stable flight of the unmanned aerial vehicle. At the same time, the power distribution board is vertically arranged and penetrates up and down, which can save floor space and reasonably distribute power to other electrical components. This structural arrangement can also achieve a neat layout of each circuit. The structure of the present utility model is compact, and while realizing the miniaturization and lightweight of the overall structure, it can ensure stable flight.

[0016] Preferably, in the above-mentioned compact autonomous exploration unmanned aerial vehicle, the outside of the battery is wrapped with a battery housing. One end face of the battery housing has a convex block, and the inner side wall of the housing has a mounting groove corresponding to the convex block. The convex block is correspondingly clamped with the mounting groove. A handle is fixed on the end face of the battery housing far from the convex block. Through the docking of the convex block on the battery housing with the mounting groove, and combined with the structural arrangement of the handle, the rapid installation and disassembly of the battery can be realized, which is convenient for replacement.

[0017] Preferably, in the above-mentioned compact autonomous exploration unmanned aerial vehicle, each flight driving mechanism includes a ducted fan ring, a driving motor, and a fan blade. The ducted fan ring is fixed below the rectangular plate by a first fastener. The driving motor is fixed on the bottom wall of the connecting beam. The fan blade is fixedly connected to the power output end of the driving motor and is located inside the ducted fan ring. The four ducted fan rings are arranged in a square shape, which not only optimizes the overall layout but also ensures the stable flight of the unmanned aerial vehicle.

[0018] Preferably, in the above-mentioned compact autonomous exploration UAV, the connecting beams are respectively a first connecting beam, a second connecting beam, a third connecting beam, and a fourth connecting beam. The ends of the first connecting beam and the second connecting beam far from the rectangular plate are connected by a bent connecting rod, and there is a gap between the bent connecting rod and the end face of the rectangular plate. This structural setting realizes the lightweight of the overall structure. At the same time, the gap between the bent connecting rod and the end face of the rectangular plate corresponds to and communicates with the two duct rings on the side close to the bent connecting rod. During flight, the aerodynamic efficiency of the fan blades is improved, the flight power and stability are enhanced, and the gap between the bent connecting rod and the rectangular plate optimizes the internal space layout of the UAV and provides installation space for other components.

[0019] Preferably, in the above-mentioned compact autonomous exploration UAV, one end of the inclined plate is fixedly connected to the housing, and the other end is fixed to the bent connecting rod. A radar mounting bracket is fixed on the inclined plate, the radar is embedded in the radar mounting bracket, a bracket is fixed on the radar mounting bracket, and the camera is mounted on the bracket. This structural setting is stable and realizes the integration of the camera and the radar at the same time.

[0020] Preferably, in the above-mentioned compact autonomous exploration UAV, an angle is formed between the radar and the rectangular plate, and the angle is 15° to 35°. The setting of the inclined plate makes there be an inclined angle with the radar, expanding the detection vision, detection range, and improving the obstacle avoidance ability.

[0021] Preferably, in the above-mentioned compact autonomous exploration UAV, shock-absorbing columns are installed at the four corners of the inclined plate, and the tops of the four shock-absorbing columns are fixedly connected to the bottom wall of the radar mounting bracket. The structural setting of the shock-absorbing columns reduces the influence of vibrations during flight on the radar and the camera, extends the service life, and at the same time, the shock-absorbing design helps to reduce the blurring and jitter during camera shooting and improves the quality of images and videos.

[0022] Preferably, in the above-mentioned compact autonomous exploration UAV, a first connecting plate is fixed between two adjacent duct rings, and a protective shell is sleeved outside the flight control and electronic speed controller board. The protective shell is fastened to the first connecting plate by a second fastener. The protective shell plays a protective role for the flight control and electronic speed controller board, and fastening the protective shell to the first connecting plate by the second fastener enhances the structural strength of the lower part of the UAV.

[0023] Preferably, in the above-mentioned compact autonomous exploration drone, an optical flow meter and a data transmission line are installed on the bottom wall of the protective shell. Two symmetric shock mounts are fixed on the bottom wall of the protective shell. The distance between the bottom end of the shock mount and the bottom wall of the protective shell is greater than the distance between the optical flow meter and the data transmission line and the bottom wall of the protective shell. The installation of the optical flow meter helps the drone to perform precise position and attitude control, improving flight stability. The data transmission line is responsible for data transmission, ensuring unobstructed communication between the drone and the ground control station. The shock mounts play a role in shock absorption and can protect the optical flow meter and the data transmission line.

[0024] Preferably, in the above-mentioned compact autonomous exploration drone, a GPS locator is installed at one end of the housing away from the radar, and the GPS locator has a USB interface. Installing the GPS locator on the side of the housing away from the radar can effectively avoid signal interference with the radar, making the detection information more accurate. The GPS locator provides accurate geographical location information for the drone, which helps to achieve autonomous navigation and precise landing. The USB interface facilitates users to charge the GPS locator or perform data transmission, improving the flexibility and convenience of the drone.

[0025] As can be seen from the above technical solutions, compared with the prior art, the present utility model discloses a compact autonomous exploration drone, which has the following beneficial effects:

[0026] 1. By installing the driving flight mechanism and the housing under and on the upper surface of the rectangular plate respectively, the overall size of the drone is reduced. At the same time, the battery, information processor, radar and camera are integrated on the housing, realizing high integration, compact structure and light weight, which is convenient for carrying and deployment.

[0027] 2. Through the setting of the inclined plate, the viewing angle range and detection range of the radar can be expanded, and autonomous obstacle avoidance can be realized, greatly reducing the collision risk during flight and enhancing flight safety.

[0028] 3. The present utility model realizes modular design, can be independently replaced and maintained, and reduces the overall maintenance cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained according to the provided drawings without creative efforts.

[0030] Figure 1The attached drawing is a schematic structural diagram of the compact autonomous exploration drone provided by the present utility model;

[0031] Figure 2 The attached drawing is a schematic structural diagram of the flight drive mechanism provided by the present utility model;

[0032] Figure 3 The attached drawing is a schematic structural diagram of the installation groove provided by the present utility model;

[0033] Figure 4 The attached drawing is a schematic structural diagram of the battery provided by the present utility model;

[0034] Figure 5 The attached drawing is a schematic structural diagram of the rectangular plate and the connecting beam provided by the present utility model;

[0035] Figure 6 The attached drawing is a schematic structural diagram of the flight control and electronic speed control board and the power distribution board provided by the present utility model;

[0036] Figure 7 The attached drawing is a schematic structural diagram of the optical flow meter and the data transmission line provided by the present utility model.

[0037] Wherein:

[0038] 1 - rectangular plate;

[0039] 11 - connecting beam; 111 - first connecting beam; 112 - second connecting beam; 113 - third connecting beam; 114 - fourth connecting beam; 115 - bent connecting rod; 116 - extension rod;

[0040] 2 - flight drive mechanism;

[0041] 21 - ducted ring; 211 - first connecting plate; 212 - second connecting plate; 22 - drive motor; 23 - fan blade; 24 - first fastener;

[0042] 3 - housing;

[0043] 31 - battery; 311 - battery housing; 312 - bump; 313 - handle; 32 - information processor; 33 - inclined plate; 331 - radar; 332 - camera; 333 - radar mounting bracket; 334 - shock absorber column; 34 - installation groove;

[0044] 4 - flight control and electronic speed control board;

[0045] 5 - power distribution board;

[0046] 6 - protective shell;

[0047] 61 - second fastener; 62 - shock absorber seat;

[0048] 7 - optical flow meter;

[0049] 8 - Data transmission line;

[0050] 9 - GPS locator. Specific implementation manner

[0051] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0052] See attached Figure 1 to attached Figure 7 , the embodiments of the present invention disclose a compact autonomous exploration drone, including:

[0053] Rectangular plate 1, and connecting beams 11 extending outward are provided at the four corners of the rectangular plate 1;

[0054] Flight drive mechanism 2; the number of the flight drive mechanisms 2 is four, and they are respectively connected to the bottom walls of the rectangular plate 1 and the four connecting beams 11, and the four flight drive mechanisms 2 are connected to each other;

[0055] Housing 3, the housing 3 is fixed on the upper surface of the rectangular plate 1, and a battery 31 is detachably connected inside it. An information processor 32 is integrated on the top of the housing 3. An inclined plate 33 connected to the rectangular plate 1 is fixed on one side of the housing 3, and a radar 331 and a camera 332 are installed on the inclined plate 33;

[0056] Flight control and electronic speed control board 4, the flight control and electronic speed control board 4 is fixed on the bottom wall of the rectangular plate 1 and is located in the middle vacancy of the four flight drive mechanisms 2, and the flight control and electronic speed control board 4 is electrically connected to the working end of each flight drive mechanism 2;

[0057] Power distribution board 5, the upper part of the power distribution board 5 is fixed inside the housing 3 and is located between the battery 31 and the radar 331. The power distribution board 5 passes through the rectangular plate 1 downward, and the power distribution board 5 is electrically connected to the battery 31 and distributes power to the information processor 32, the radar 331, the camera 332 and the flight control and electronic speed control board 4.

[0058] To further optimize the above technical solution, the outside of the battery 31 is wrapped with a battery housing 311. A convex block 312 is provided on the end face of one end of the battery housing 311. The inner side wall of the housing 3 has a mounting groove 34 corresponding to the convex block. The convex block 312 is correspondingly clamped with the mounting groove 34. A handle 313 is fixed on the end face of the battery housing 311 away from the convex block 312.

[0059] To further optimize the above technical solution, the power distribution board 5 is provided with connection interfaces, and the connection interfaces are electrically connected to the positive and negative electrodes of the battery 31 through cables or wires.

[0060] To further optimize the above technical solution, each flight drive mechanism 2 includes a ducted ring 21, a drive motor 22, and a fan blade 23. The ducted ring 21 is fixed below the rectangular plate 1 through a first fastener 24. The drive motor 22 is fixed on the bottom wall of the connecting beam 11. The fan blade 23 is fixedly connected to the power output end of the drive motor 22 and is located inside the ducted ring 21.

[0061] To further optimize the above technical solution, a second connecting plate 212 is also fixed between two adjacent ducted rings 21. The two side edges of the rectangular plate 1 have extension rods 116 extending outward therefrom. The second connecting plate 212 located between the first connecting beam 111 and the fourth connecting beam 114 and the second connecting plate 212 located between the second connecting beam 112 and the third connecting beam 113 are both fastened to the extension rod 116 through the first fastener 24. The second connecting plate 212 located between the first connecting beam 111 and the second connecting beam 112 is fastened to the bent connecting rod 115 through the first fastener 24. One end edge of the rectangular plate 1 away from the bent connecting rod 115 is fastened to the second connecting plate 212 and the GPS locator 9 located between the third connecting beam 113 and the fourth connecting beam 114 through the first fastener 24.

[0062] To further optimize the above technical solution, the connecting beam 11 is respectively the first connecting beam 111, the second connecting beam 112, the third connecting beam 113, and the fourth connecting beam 114. One end of the first connecting beam 111 and the second connecting beam 112 away from the rectangular plate 1 are connected through a bent connecting rod 115, and there is a gap between the bent connecting rod 115 and the end face of the rectangular plate 1.

[0063] To further optimize the above technical solution, one end of the inclined plate 33 is fixedly connected to the housing 3, and the other end is fixed to the bent connecting rod 115. A radar mounting bracket 333 is fixed on the inclined plate 33. The radar 331 is embedded in the radar mounting bracket 333. A bracket is fixed on the radar mounting bracket 333, and the camera 332 is mounted on the bracket.

[0064] To further optimize the above technical solution, an angle is formed between the radar 331 and the rectangular plate 1, and the angle is 15° to 35°.

[0065] To further optimize the above technical solution, shock-absorbing columns 334 are installed at the four corners of the inclined plate 33, and the tops of the four shock-absorbing columns 334 are fixedly connected to the bottom wall of the radar mounting bracket 333.

[0066] To further optimize the above technical solution, a first connecting plate 211 is fixed between two adjacent duct rings 21. A protective shell 6 is provided outside the flight control ESC board 4, and the protective shell 6 is fastened to the first connecting plate 211 through a second fastener 61.

[0067] To further optimize the above technical solution, an optical flow meter 7 and a data transmission line 8 are installed on the bottom wall of the protective shell 6. Both the optical flow meter 7 and the data transmission line 8 are electrically connected to the power distribution board 5 and the information processor. On the bottom wall of the protective shell 6, shock mounts 62 are fixed in pairs symmetrically. The distance between the bottom end of the shock mount 62 and the bottom wall of the protective shell 6 is greater than the distance between the optical flow meter 7 and the data transmission line 8 and the bottom wall of the protective shell 6.

[0068] To further optimize the above technical solution, a GPS locator 9 is installed at one end of the housing 3 away from the radar 331, and the GPS locator 9 has a USB interface 91.

[0069] To further optimize the above technical solution, the information processor 32 can receive data fed back by electrical components such as the radar, camera, and data transmission line, record and analyze it, and at the same time feedback it to the control end to make corresponding data adjustments, etc.

[0070] In this specification, the various embodiments are described in a progressive manner. The key point of each embodiment is the difference from other embodiments. The same or similar parts among the various embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the description of the method part.

[0071] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A compact autonomous exploration drone, characterized in that: include: A rectangular plate (1), wherein the four corners of the rectangular plate (1) each have a connecting beam (11) extending outwards thereof; A flight drive mechanism (2); the number of the flight drive mechanisms (2) is four, and they are respectively connected to the bottom walls of the rectangular plate (1) and the four connecting beams (11), and the four flight drive mechanisms (2) are connected to each other; A casing (3), the casing (3) being fixed on the upper surface of the rectangular plate (1), and having a battery (31) detachably connected thereto, an information processor (32) being integrated at the top of the casing (3), an inclined plate (33) connected to the rectangular plate (1) being fixed on one side of the casing (3), and a radar (331) and a camera (332) being mounted on the inclined plate (33); A flight control electric adjustment board (4), the flight control electric adjustment board (4) is fixed on the bottom wall of the rectangular plate (1) and is located in the middle space of the four flight drive mechanisms (2), and the flight control electric adjustment board (4) is electrically connected to the working end of each of the flight drive mechanisms (2); A power distribution board (5), the upper part of which is fixed in the housing (3) and is located between the battery (31) and the radar (331), the power distribution board (5) passes downward through the rectangular plate (1), the power distribution board (5) is electrically connected to the battery (31), and distributes power to the information processor (32), the radar (331), the camera (332) and the flight control electric adjustment board (4).

2. A compact autonomous exploration drone according to claim 1, characterized in that: The battery (31) is wrapped with a battery shell (311) on the outside, and a protrusion (312) is provided on the end surface of one end of the battery shell (311). The inner wall of the housing (3) has a mounting groove (34) corresponding to the protrusion, and the protrusion (312) is correspondingly engaged with the mounting groove (34). A handle (313) is fixed on the end surface of the battery shell (311) away from the protrusion (312).

3. A compact autonomous exploration drone according to claim 1, characterized in that: Each of the flight drive mechanisms (2) comprises a duct (21), a drive motor (22) and a fan blade (23); the duct (21) is fixed below the rectangular plate (1) via a first fastener (24); the drive motor (22) is fixed on the bottom wall of the connecting beam (11); the fan blade (23) is fixedly connected to the power output end of the drive motor (22) and is located on the inner side of the duct (21).

4. A compact autonomous exploration drone according to claim 1, characterized in that: The connecting beams (11) are respectively a first connecting beam (111), a second connecting beam (112), a third connecting beam (113) and a fourth connecting beam (114); the ends of the first connecting beam (111) and the second connecting beam (112) away from the rectangular plate (1) are connected via a bent connecting rod (115); and a gap is provided between the bent connecting rod (115) and the end surface of the rectangular plate (1).

5. A compact autonomous exploration drone according to claim 4, characterized in that: One end of the inclined plate (33) is fixedly connected to the housing (3), and the other end is fixed to the bent connecting rod (115); a radar mounting frame (333) is fixed to the inclined plate (33); the radar (331) is embedded in the radar mounting frame (333); a bracket is fixed to the radar mounting frame (333); and the camera (332) is mounted on the bracket.

6. A compact autonomous exploration drone according to claim 4, characterized in that: An angle is formed between the radar (331) and the rectangular plate (1), and the angle is 15° to 35°.

7. A compact autonomous exploration drone according to claim 5, characterized in that: Shock-absorbing columns (334) are installed at the four corners of the inclined plate (33), and the top ends of the four shock-absorbing columns (334) are fixedly connected to the bottom wall of the radar mounting frame (333).

8. A compact autonomous exploration drone according to claim 3, characterized in that: A first connecting plate (211) is fixed between two adjacent duct coils (21), and a protective shell (6) is provided on the outer side cover of the flight control electric adjustment board (4), and the protective shell (6) is fastened to the first connecting plate (211) via a second fastener (61).

9. A compact autonomous exploration drone according to claim 8, characterized in that: An optical flow meter (7) and a data transmission line (8) are mounted on the bottom wall of the protective shell (6); two symmetrical shock-absorbing seats (62) are fixed on the bottom wall of the protective shell (6); the distance between the bottom end of the shock-absorbing seat (62) and the bottom wall of the protective shell (6) is greater than the distance between the optical flow meter (7) and the data transmission line (8) and the bottom wall of the protective shell (6).

10. A compact autonomous exploration drone according to claim 1, characterized in that: A GPS locator (9) is installed at one end of the housing (3) away from the radar (331), and the GPS locator (9) has a USB interface (91).

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