Double-cavity ducted unmanned aerial vehicle

Abstract

The utility model discloses a double-cavity ducted type unmanned aerial vehicle, which comprises a central mounting seat and a plurality of vehicle arms arranged on the central mounting seat, the vehicle arms are used for fixing a duct and a propeller, the central mounting seat comprises an upper shell, an upper layer plate and a bottom layer plate which are sequentially arranged from top to bottom, and an upper cavity is formed between the upper shell and the upper layer plate; one end of each arm is arranged between the upper-layer plate and the bottom-layer plate, sealing blocks are further arranged at the positions, located between the upper-layer plate and the bottom-layer plate, of the two adjacent arms, a lower cavity is formed among the upper-layer plate, the bottom-layer plate, the sealing blocks and the arms, and the upper cavity and the lower cavity are used for installing electronic elements. According to the utility model, by forming a plurality of cavities, a stronger protection capability can be provided for the unmanned aerial vehicle, the safety of internal electronic components is enhanced, and a larger internal space is provided for the unmanned aerial vehicle.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, especially a double cavity ducted unmanned plane. BACKGROUND

[0002] In recent years, the unmanned plane technology develops rapidly and is widely used in the fields of agriculture, logistics, industrial inspection and the like. However, with the complication and refinement of task requirements, the traditional multi-rotor unmanned plane faces many challenges in structural design, such as insufficient protection of internal components, low space utilization rate and the like. These deficiencies limit the performance of the unmanned plane in long-time flight and harsh environment.

[0003] Most of the current multi-rotor unmanned planes adopt a simplified single-layer shell design, such as the ducted unmanned plane disclosed in Chinese Patent No. 202221244407.5, which forms a single-cavity structure by means of two plate bodies. Although this design has a lower manufacturing cost, the shell has a weak protection capability for internal sensitive electronic components, and when facing harsh weather, collision or other environmental factors, the problem of component damage is prone to occur. In addition, the existing shell structure cannot effectively utilize the internal space, limiting the equipment integration and the functional expansion capability of the unmanned plane. SUMMARY

[0004] The present application proposes a double-cavity ducted unmanned plane to solve the problem of weak protection capability of the single-cavity multi-rotor unmanned plane for internal sensitive electronic components mentioned in the background technology, and when facing harsh weather, collision or other environmental factors, the problem of component damage is prone to occur, and the existing shell structure cannot effectively utilize the internal space, limiting the equipment integration and the functional expansion capability of the unmanned plane.

[0005] The technical solution adopted by the utility model is: a double-cavity ducted unmanned plane, comprising a center mounting seat and a plurality of arms provided on the center mounting seat, the arms being used for fixing ducts and propellers, the center mounting seat comprising an upper shell, an upper layer plate and a bottom layer plate arranged in sequence from top to bottom, an upper cavity being formed between the upper shell and the upper layer plate, one end of each arm being provided between the upper layer plate and the bottom layer plate, and a sealing block being further provided between the upper layer plate and the bottom layer plate at the positions of adjacent two arms, a lower cavity being formed between the upper layer plate, the bottom layer plate, each sealing block and each arm, and the upper cavity and the lower cavity being used for mounting electronic components.

[0006] Further, a first mounting slot and a second mounting slot are further provided at the lower end of the bottom layer plate, the first mounting slot being used for mounting a camera, and the second mounting slot being used for mounting a battery; a wire hole is formed in the bottom layer plate.

[0007] Further, the end of the arm is provided with a groove, the upper end of the groove is screw connected with the upper layer plate, and the lower end of the groove is screw connected with the bottom layer plate; the upper end of the sealing block is screw connected with the upper shell, and the lower end of the sealing block is screw connected with the bottom layer plate, and a wire hole is formed in the sealing block.

[0008] Further, the other end of the arm is provided with a mounting disc, the mounting disc is provided with a duct, the duct is provided with a cross support frame, the cross support frame of the duct is provided with a motor, the output end of the motor is provided with the propeller, and the mounting disc, the duct and the motor are fixedly connected through a plurality of screws.

[0009] Further, the arm is provided with an electronic governor, and the cross support frame is provided with a wire slot for the connecting wires of the motor and the electronic governor to pass through.

[0010] Further, the arm is further provided with a foot stand below.

[0011] Further, the slot of the second mounting groove is provided with a rear cover, and the rear cover is buckle connected or screw connected with the second mounting groove.

[0012] Further, the upper end of the upper shell is provided with a triangular groove for indicating the direction of the head.

[0013] Further, the upper shell is further provided with a GPS cover.

[0014] The utility model discloses a center mounting seat is set up to a plurality of components, adopts the way of splicing of upper shell, upper layer plate and bottom layer plate to form a plurality of cavities, and the setting of the plurality of cavities can provide more powerful protection for the unmanned plane, and the double-cavity shell effectively isolates the impact and environmental interference of the outside world, enhances the safety of internal electronic components, especially in high-risk tasks and complex flight environment, can better guarantee the normal operation of equipment, in addition, the design of double-cavity structure also provides greater internal space for the unmanned plane, is favorable to integrate more sensors, communication equipment or other modules, expands the task ability and application scene of the unmanned plane. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical scheme in the embodiment of the utility model, the following will briefly introduce the drawing needed to be used in the embodiment or prior art description, obviously, the drawing in the following description is only some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained according to these drawings without creative labor.

[0016] Figure 1 It is the whole structure schematic diagram of the utility model.

[0017] Figure 2This is an overall exploded view of the present invention.

[0018] Figure 3 This is an exploded view of the motor, duct, and boom of this utility model.

[0019] Figure 4 This is an exploded view of the machine arm and sealing block of this utility model.

[0020] Figure 5 This is a schematic diagram of the lower cavity of this utility model in conjunction with an explosion.

[0021] Figure 6 This is a schematic diagram of the upper cavity of this utility model in conjunction with an explosion.

[0022] Figure 7 This is an exploded view of the camera, bottom plate, and back cover in this utility model.

[0023] 1. GPS cover; 2. Duct; 3. Motor cover; 4. Motor; 5. Propeller; 6. Arm; 7. ESC; 8. Tripod; 9. Camera; 10. Sealing block; 11. Bottom plate; 12. Top plate; 13. Rear cover; 14. Top shell; 15. Groove; 16. First mounting slot; 17. Second mounting slot; 18. Insert; 19. Waist-shaped hole; 20. Mounting plate; 21. Cable tray; 22. Cross support bracket; 23. Center mounting base. Detailed Implementation

[0024] To make the technical problems, technical solutions, and beneficial effects of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0025] Combined with appendix Figures 1-7 The present invention provides a dual-cavity ducted unmanned aerial vehicle (UAV) with a main body, including a central mounting base 23, and several arms 6 fixed on the central mounting base 23 in a circular array around the central mounting base 23. One end of the arms 6 is connected to the central mounting base 23, and the other end of the arms 6 is used to connect the duct 2 and the propeller 5.

[0026] Specifically, in conjunction with the appendix Figure 2 , 5As shown in Figure 6, the central mounting base 23 includes an upper shell 14, an upper plate 12, and a lower plate 11. The upper shell 14, upper plate 12, and lower plate 11 form two cavities. These cavities of the central mounting base 23 are used to install electronic components. The upper plate 12 is provided on the upper opening at the lower end of the upper shell 14, so that an upper cavity is formed between the upper shell 14 and the upper plate 12. A GPS positioning module can be installed in the upper cavity. A GPS cover 1 is also connected to the upper shell 14. A triangular groove is provided on the front side of the upper end of the upper shell 14 to indicate the direction of the machine head; the arm 6 The front end is provided with a groove 15. The upper end of the groove 15 is screwed to the upper plate 12, and the lower end of the groove 15 is screwed to the bottom plate 11. A sealing block 10 is inserted between the front ends of two adjacent arms 6. The sealing block 10 is provided with a wire hole. The upper end of the sealing block 10 is screwed to the upper shell 14, and the lower end of the sealing block 10 is screwed to the bottom plate 11. The upper plate 12, the bottom plate 11, the sealing blocks 10, and the arms 6 form a lower cavity. The upper cavity and the lower cavity are used to install electronic components (such as a central controller, GPS positioning module, etc.).

[0027] Furthermore, such as Figure 7 As shown, a first mounting slot 16 and a second mounting slot 17 are provided at the lower end of the bottom plate 11. The first mounting slot 16 is used to install the camera 9, and the second mounting slot 17 is used to install the battery. A wire hole is provided on the bottom plate 11 for the camera 9 and the battery to make electrical and signal connections with other electronic components. A back cover 13 is provided at the opening of the second mounting slot 17 to protect the battery. The back cover 13 is snapped or screwed to the second mounting slot 17. In this embodiment, a insert 18 is provided on the back cover 13, and a waist-shaped hole 19 is provided on the insert 18. A waist-shaped hole 19 of the same size is provided on the side wall of the second mounting slot 17. The screw connection is achieved by inserting a screw into the insert 18 and the waist-shaped hole 19 on the second mounting slot 17. Alternatively, a matching snap structure can be provided on the side wall of the insert 18 and the second mounting slot 17 to achieve quick snap-fit.

[0028] Furthermore, in conjunction with the appendix Figure 2 , 3As shown, the other end of the arm 6 is provided with a mounting disc 20, the duct 2 is arranged on the mounting disc 20, the lower end of the duct 2 is provided with a cross support frame 22, the motor 4 is arranged on the cross support frame 22 of the duct 2, the output end of the motor 4 is provided with a motor 4 cover 3, the output shaft of the motor 4 is fixedly connected with the propeller 5 through the motor 4 cover 3, and corresponding positioning holes are arranged on the mounting disc 20, the cross support frame 22 of the duct 2 and the motor 4, and the positioning holes between the mounting disc 20, the duct 2 and the motor 4 are fixedly connected through a plurality of screws; and the electric governor 7 is arranged on the arm 6, and the wire slot 21 for the connecting wires of the motor 4 and the electric governor 7 to pass through is arranged on the cross support frame 22, the motor speed is controlled through the electric governor 7, and the lift and the roll attitude of the unmanned aerial vehicle are adjusted.

[0029] The utility model discloses to the center mounting seat 23 has carried out multi-component setting, adopts the way of splicing of upper shell 14, upper layer board 12 and bottom layer board 11 to constitute multi-cavity, and the setting of multi-cavity can provide more powerful protection ability for unmanned aerial vehicle, and the double-cavity shell effectively isolates the impact and environmental interference of outside, and the safety of internal electronic components is enhanced, especially in high-risk task and complex flight environment, can better guarantee the normal operation of equipment, in addition, the design of double-cavity structure also provides greater internal space for unmanned aerial vehicle, and it is favorable to integrate more sensors, communication equipment or other modules, and expand the task ability and application scene of unmanned aerial vehicle.

[0030] Specifically, the utility model combines the ducted six-rotor layout, compared with the traditional four-rotor unmanned aerial vehicle, the six-rotor has stronger load capacity and higher flight stability, the six-rotor design not only can improve the thrust output of unmanned aerial vehicle, but also can continue to maintain stable flight when a certain rotor fails, and the safety and reliability of the system are enhanced, and the ducted rotor structure makes the aerodynamic efficiency of the unmanned aerial vehicle improve, the flight stability is enhanced, simultaneously reduces the noise generated during flight and improves the safety.

[0031] The above only describes the preferred embodiment of the utility model, and does not limit the utility model, and any modification, equivalent replacement and improvement made within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. A twin-cavity ducted drone, characterized in that, The application relates to a center mounting base and a plurality of arms arranged on the center mounting base, the arms being used for fixing a duct and a propeller, the center mounting base comprising an upper shell, an upper layer plate and a bottom layer plate arranged in sequence from top to bottom, an upper cavity being formed between the upper shell and the upper layer plate, one end of the arm being arranged between the upper layer plate and the bottom layer plate, and sealing blocks being arranged between the upper layer plate and the bottom layer plate at positions of adjacent arms, the upper layer plate, the bottom layer plate, the sealing blocks and the arms forming a lower cavity, and the upper cavity and the lower cavity being used for mounting electronic components.

2. The dual-cockpit ducted drone of claim 1, wherein, The bottom layer plate is provided with a first mounting groove and a second mounting groove at a lower end, the first mounting groove being used for mounting a camera, and the second mounting groove being used for mounting a battery; and a wire hole is formed in the bottom layer plate.

3. The dual-cockpit ducted drone of claim 1, wherein, The end of the arm is provided with a groove, the upper end of the groove being screw-connected with the upper layer plate, and the lower end of the groove being screw-connected with the bottom layer plate; the upper end of the sealing block is screw-connected with the upper shell, and the lower end of the sealing block is screw-connected with the bottom layer plate, and a wire hole is formed in the sealing block.

4. The dual-cockpit ducted drone of claim 3, wherein, The other end of the arm is provided with a mounting disc, the mounting disc being provided with a duct, a cross-shaped support frame being arranged in the duct, a motor being arranged on the cross-shaped support frame of the duct, the output end of the motor being provided with the propeller, and the mounting disc, the duct and the motor being fixedly connected through a plurality of screws.

5. The dual-cockpit ducted drone of claim 4, wherein, An electronic governor is arranged on the arm, and a wire slot is arranged on the cross-shaped support frame for the connection wires of the motor and the electronic governor.

6. The dual-cockpit ducted drone of claim 4, wherein, A foot stand is further arranged below the arm.

7. The dual-cockpit ducted drone of claim 2, wherein, The second mounting groove is provided with a rear cover, the rear cover being buckle-connected or screw-connected with the second mounting groove.

8. The dual-cockpit ducted drone of claim 1, wherein, A triangular slot is arranged at the upper end of the upper shell for indicating the direction of the head.

9. The dual-cockpit ducted drone of claim 1, wherein, A GPS cover is further arranged on the upper shell.

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