Two-in-one combined low-altitude flight unmanned aerial vehicle

Abstract

The invention discloses a two-in-one combined low-altitude flight unmanned aerial vehicle which comprises an unmanned aerial vehicle body and a low-altitude induction box detachably installed at the bottom of the unmanned aerial vehicle body, a swing plate is hinged to a bottom shell of the low-altitude induction box, and the lower end of the swing plate is connected with a contact pin. A first electric cylinder connected with the upper end of the swing plate is installed in the low-altitude induction box, a counter-force plate is installed at the rear end of the first electric cylinder, and a tension sensor is installed between the counter-force plate and the first electric cylinder. The two-in-one combined low-altitude flight unmanned aerial vehicle is used for low-altitude flight, and the flight safety of the unmanned aerial vehicle during low-altitude flight is improved.

Description

Technical Field

[0001] The present invention relates to the field of low-altitude flying unmanned aerial vehicles, and in particular to a two-in-one combined low-altitude flying unmanned aerial vehicle. Background Art

[0002] With the development of the low-altitude economy, the application scenarios of drones are becoming more and more diverse, with operational scenarios accounting for the largest proportion, such as agricultural operations, logistics distribution, and surveying and mapping. At the same time, security and consumer applications are also gradually emerging, such as emergency rescue, security monitoring, fire fighting, etc. These applications not only improve operational efficiency and safety, but also promote the transformation and upgrading of traditional industries.

[0003] For example, in the application of low-altitude drones for river patrols, the drone needs to fly at a relatively low altitude close to the water surface. When there are floating objects on the water surface, low-protruding obstacles, or the drone is flying too low, the drone needs to be raised. However, current low-altitude flying drones cannot achieve automatic perception and raising operations, which can result in slow response and damage to the drone. Summary of the invention

[0004] The purpose of the present invention is to provide a two-in-one combined low-altitude flying UAV, which is used for low-altitude flight and increases the flight safety of the UAV during low-altitude flight.

[0005] In order to achieve the above-mentioned objectives, the present invention provides a two-in-one combined low-altitude flying UAV, comprising a UAV body and a low-altitude sensing box detachably mounted on the bottom of the UAV body, a swing plate hinged at the bottom shell of the low-altitude sensing box, a feeler foot connected to the lower end of the swing plate, a first electric cylinder connected to the upper end of the swing plate installed in the low-altitude sensing box, a reaction plate installed at the rear end of the first electric cylinder, and a tension sensor installed between the reaction plate and the first electric cylinder.

[0006] Preferably, a strip hole is provided on the bottom shell of the low-altitude induction box, the swing plate is rotatably installed in the middle of the strip hole through a first pin shaft, a first guide hole is provided at the upper end of the strip hole, and a second pin shaft sliding in the first guide hole is provided at the axial end of the first electric cylinder.

[0007] Preferably, a telescopic pull-out plate is provided at the lower end of the swing plate, a third pin is provided at the upper end of the telescopic pull-out plate, a second guide hole for passing the third pin is provided on the side of the swing plate, an external thread is provided at the outer end of the third pin, and a nut is sleeved on the external thread.

[0008] Preferably, the contact foot comprises a connecting section extending obliquely backward and a contact section extending vertically downward, and the upper end of the connecting section is fixedly connected to the lower end of the telescopic pull-out plate.

[0009] Preferably, a breaking mark is provided at the connection between the connecting section and the telescopic pull-out plate.

[0010] Preferably, an inspection port is provided in the middle of the upper end of the low-altitude induction box.

[0011] Preferably, a first magnetic block is arranged at the upper end of the low-altitude induction box around the inspection port, and a second magnetic block cooperating with the first magnetic block is arranged at the bottom of the drone body.

[0012] Preferably, a rotor assembly is installed on the extension arm of the drone body;

[0013] The main motor of the rotor assembly is hingedly arranged at the end of the extension arm, and the main motor is connected to a driving mechanism capable of driving the main motor to swing forward and backward.

[0014] Preferably, the driving mechanism comprises a third pin shaft connected to the main motor, a cam is provided on an outer sleeve of the third pin shaft, and a distal end of the cam is connected to a second electric cylinder via a fourth pin shaft.

[0015] Preferably, the second electric cylinder is electrically connected to a processor in a main body of the drone, and the first electric cylinder is connected to the processor by wireless connection or coupling.

[0016] According to the above technical solution, the two-in-one combined low-altitude flying UAV in the present invention is used for low-altitude flight, which increases the flight safety of the UAV during low-altitude flight.

[0017] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the following specific embodiments, they are used to explain the present invention but do not constitute a limitation of the present invention. In the accompanying drawings:

[0019] Figure 1 It is a structural diagram of a preferred embodiment of a two-in-one combined low-altitude flying UAV;

[0020] Figure 2 is a partial enlarged structural schematic diagram of a preferred embodiment of a rotor assembly;

[0021] Figure 3 It is a partial enlarged structural schematic diagram of a preferred implementation scheme at the swing plate.

[0022] Description of Reference Numerals

[0023] 1-UAV body; 2-low altitude induction box; 3-inspection port; 4-bottom shell; 5-tension sensor; 6-first electric cylinder; 7-bar hole; 8-extension arm; 9-rotor assembly; 10-cam; 11-second electric cylinder; 12-swing plate; 13-first guide hole; 14-second guide hole; 15-nut; 16-telescopic pull-out plate; 17-connecting section; 18-contact section. DETAILED DESCRIPTION

[0024] The specific implementation of the present invention is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described herein is only used to illustrate and explain the present invention, and is not used to limit the present invention.

[0025] In the present invention, unless otherwise stated, directional words contained in terms such as "up, down, left, right, front, back, inside, outside" merely represent the orientation of the terms in normal usage, or are common names understood by those skilled in the art, and should not be regarded as limitations on the terms.

[0026] See also Figure 1-3 The two-in-one combined low-altitude flying UAV shown in the figure includes a UAV body 1 and a low-altitude sensing box 2 detachably mounted on the bottom of the UAV body 1, a swing plate 12 is hinged at the bottom shell 4 of the low-altitude sensing box 2, and a feeler is connected to the lower end of the swing plate 12. A first electric cylinder 6 connected to the upper end of the swing plate 12 is installed in the low-altitude sensing box 2, a reaction plate is installed at the rear end of the first electric cylinder 6, and a tension sensor 5 is installed between the reaction plate and the first electric cylinder 6.

[0027] Through the implementation of the above technical solution, the two-in-one combined low-altitude flying drone is used for low-altitude flight, which increases the flight safety of the drone during low-altitude flight. When using the two-in-one combined low-altitude flying drone, the two-in-one combined low-altitude flying drone can be optionally installed to the bottom of the drone body 1. When the flight altitude is low enough from the target below, the tentacles located below first contact the target, and squeeze the target. After the tension sensor 5 senses the tension, the first electric cylinder 6 is activated to extend, so that the upper end of the swing plate 12 is pushed and rotated around the middle hinge of the swing plate 12, so that the lower end of the tentacles flips back and releases contact with the target. The drone then raises itself a certain distance to maintain a low-altitude flight at a certain safe height from the target.

[0028] In this embodiment, in order to further provide a specific structure of a low-altitude induction box 2, a strip hole 7 is provided on the bottom shell 4 of the low-altitude induction box 2, the swing plate 12 is rotatably installed in the middle of the strip hole 7 through a first pin shaft, and a first guide hole 13 is provided at the upper end of the strip hole 7, and a second pin shaft sliding in the first guide hole 13 is provided at the axial end of the first electric cylinder 6.

[0029] When the first electric cylinder 6 is extended, the swing plate 12 rotates around the first pin shaft. When the swing plate 12 rotates, the second pin shaft pushes the swing plate 12 and guides it to slide in the first guide hole 13 .

[0030] In this embodiment, a telescopic pull-out plate 16 is provided at the lower end of the swing plate 12, a third pin is provided at the upper end of the telescopic pull-out plate 16, a second guide hole 14 for passing the third pin is provided on the side of the swing plate 12, an external thread is provided at the outer end of the third pin, and a nut 15 is sleeved on the external thread.

[0031] Through such an arrangement, the height position of the contact foot can be adjusted according to different usage environments.

[0032] In this embodiment, in order to further provide a contact foot structure, the contact foot includes a connecting section 17 extending obliquely backward and a contact section 18 extending vertically downward, and the upper end of the connecting section 17 is fixedly connected to the lower end of the telescopic pull-out plate 16.

[0033] Through such a configuration, an obtuse angle is formed between the connecting section 17 and the telescopic pull-out plate 16 to prevent the feeler from affecting the flight of the drone body 1 when encountering excessive squeezing force. In addition, by configuring the contact section 18 to extend vertically downward, the contact with the target object can be increased.

[0034] In this embodiment, a break mark is provided at the connection between the connecting section 17 and the telescopic pull plate 16. With such a setting, when the feeler is subjected to a pressure greater than a set pressure, the break mark will be broken, thereby overcoming the influence of the contact pressure on the drone body 1.

[0035] In this embodiment, an inspection port 3 is provided in the middle of the upper end of the low-altitude induction box 2. The inspection port 3 is provided to facilitate the inspection of the internal components of the low-altitude induction box 2. When the low-altitude induction box 2 is installed at the bottom of the drone body 1, the inspection port 3 is closed, and has a good sealing effect.

[0036] In this embodiment, a first magnetic block is disposed at the upper end of the low-altitude induction box 2 around the inspection port 3, and a second magnetic block that cooperates with the first magnetic block is disposed at the bottom of the drone body 1. The cooperation between the first magnetic block and the second magnetic block allows the two to be connected by magnetic attraction, providing a connection method that is easy to disassemble.

[0037] In this embodiment, a rotor assembly 9 is installed on the extension arm 8 of the drone body 1; the main motor of the rotor assembly 9 is hingedly arranged at the end of the extension arm 8, and the main motor is connected to a driving mechanism that can drive it to swing back and forth.

[0038] Through such a structure, when the tentacles contact the target object and generate squeezing force, the driving mechanism works to push the main motor to produce a certain inclination angle, so that the front end of the drone body 1 can be quickly lifted to a certain angle, allowing the drone body 1 to quickly escape the danger of hitting the target object.

[0039] In this embodiment, in order to further provide a driving mechanism, the driving mechanism includes a third pin shaft connected to the main motor, the third pin shaft is outerly provided with a cam 10, and the far end of the cam 10 is connected to the second electric cylinder 11 through a fourth pin shaft.

[0040] The rear end of the second electric cylinder 11 is rotatably connected to the end of the extension arm 8 , so that when the second electric cylinder 11 is extended or shortened, the second electric cylinder 11 can rotate accordingly.

[0041] In this embodiment, the second electric cylinder 11 is electrically connected to a processor in the drone body 1 , and the first electric cylinder 6 is connected to the processor via a wireless connection or coupling.

[0042] Through such a setting, the processor can globally control the first electric cylinder 6 and the second electric cylinder 11 so that the two can work in coordination.

[0043] The preferred embodiments of the present invention are described in detail above in conjunction with the accompanying drawings. However, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, a variety of simple modifications can be made to the technical solution of the present invention, and these simple modifications all belong to the protection scope of the present invention.

[0044] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, the present invention will not further describe various possible combinations.

[0045] In addition, various embodiments of the present invention may be arbitrarily combined, and as long as they do not violate the concept of the present invention, they should also be regarded as the contents disclosed by the present invention.

Claims

1. A two-in-one low-altitude flying drone, characterized in that: The invention comprises an unmanned aerial vehicle (UAV) body (1) and a low-altitude induction box (2) detachably mounted on the bottom of the UAV body (1), wherein a swing plate (12) is hingedly connected to a bottom shell (4) of the low-altitude induction box (2), the lower end of the swing plate (12) is connected to a feeler, a first electric cylinder (6) connected to the upper end of the swing plate (12) is mounted in the low-altitude induction box (2), a reaction plate is mounted at the rear end of the first electric cylinder (6), and a tension sensor (5) is mounted between the reaction plate and the first electric cylinder (6).

2. The two-in-one combined low-altitude flying drone according to claim 1, characterized in that: A strip hole (7) is provided on the bottom shell (4) of the low-altitude induction box (2); the swing plate (12) is rotatably mounted in the middle of the strip hole (7) via a first pin shaft; a first guide hole (13) is provided at the upper end of the strip hole (7); and a second pin shaft is provided at the shaft end of the first electric cylinder (6) and slides in the first guide hole (13).

3. The two-in-one combined low-altitude flying drone according to claim 1, characterized in that: A telescopic pull-out plate (16) is provided at the lower end of the swing plate (12), a third pin is provided at the upper end of the telescopic pull-out plate (16), a second guide hole (14) for passing the third pin is provided on the side of the swing plate (12), an external thread is provided at the outer end of the third pin, and a nut (15) is sleeved on the external thread.

4. The two-in-one combined low-altitude flying drone according to claim 3 is characterized in that: The contact foot comprises a connecting section (17) extending obliquely backward and a contact section (18) extending vertically downward, and the upper end of the connecting section (17) is fixedly connected to the lower end of the telescopic pull-out plate (16).

5. The two-in-one combined low-altitude flying UAV according to claim 4 is characterized in that: A fracture indentation is provided at the connection between the connection section (17) and the telescopic pull-out plate (16).

6. The two-in-one combined low-altitude flying drone according to claim 1, characterized in that: An inspection port (3) is provided in the middle of the upper end of the low-altitude induction box (2).

7. The two-in-one combined low-altitude flying UAV according to claim 6, characterized in that: A first magnetic block is arranged at the upper end of the low-altitude induction box (2) and around the inspection port (3), and a second magnetic block cooperating with the first magnetic block is arranged at the bottom of the drone body (1).

8. The two-in-one combined low-altitude flying UAV according to claim 1, characterized in that: A rotor assembly (9) is installed on the extension arm (8) of the drone body (1); The main motor of the rotor assembly (9) is hingedly arranged at the end of the extension arm (8), and the main motor is connected to a driving mechanism capable of driving it to swing forward and backward.

9. The two-in-one combined low-altitude flying UAV according to claim 8, characterized in that: The driving mechanism comprises a third pin shaft connected to the main motor, a cam (10) is disposed on the outer sleeve of the third pin shaft, and a distal end of the cam (10) is connected to a second electric cylinder (11) via a fourth pin shaft.

10. The two-in-one combined low-altitude flying UAV according to claim 9, characterized in that: The second electric cylinder (11) is electrically connected to a processor in the drone body (1), and the first electric cylinder (6) is connected to the processor via a wireless connection or coupling.

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