Staggered wing fuselage structure of unmanned aerial vehicle

Abstract

The staggered-wing fuselage structure of the unmanned aerial vehicle comprises a fuselage, the included angle between the fuselage and the horizontal plane is an acute angle, the side face of the fuselage is provided with a machine arm connecting base, the machine arm connecting base is connected with a machine arm in a hinged mode, the end of the machine arm is provided with a motor, and the motor is connected with a propeller; the vehicle arms comprise the first vehicle arm and the second vehicle arm, the first vehicle arm is hinged to the vehicle arm connecting base at the lower position, and the second vehicle arm is hinged to the vehicle arm connecting base at the higher position. A conventional arrangement mode of a fuselage and arms is modified, a certain included angle of 7-10 degrees is formed between the arms and the fuselage, and therefore it is guaranteed that the first arm and the second arm are located on different horizontal planes, interference cannot be generated after the first arm and the second arm are folded, the length of the arms is the same as that of the fuselage, and the structure is simple. And the folded rollers are fixed on two sides of the fuselage.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and more specifically to a staggered-wing fuselage structure of an unmanned aerial vehicle. Background Art

[0002] At present, when small unmanned aerial vehicles are carried or stored, in order to reduce the occupied space, the arms are usually disassembled and stored separately from the fuselage. When in use, the arms are taken out and installed on the fuselage. Although this method can reduce the occupied space, the disassembly and installation are not convenient, and the use is also rather troublesome. Content of the Utility Model

[0003] To solve the above problems and overcome the deficiencies of the prior art, the utility model provides a staggered-wing fuselage structure of an unmanned aerial vehicle, which includes a fuselage. The angle between the fuselage and the horizontal plane is an acute angle. An arm connection seat is installed on the side of the fuselage. An arm is connected to the arm connection seat in a hinged manner. A motor is arranged at the end of the arm, and the motor is connected with a propeller.

[0004] Furthermore, the arm includes a first arm and a second arm. The first arm is hinged to the arm connection seat at a lower position, and the second arm is hinged to the arm connection seat at a higher position.

[0005] Furthermore, the motor arranged at the end of the first arm is located below the first arm, and the motor arranged at the end of the second arm is located above the second arm.

[0006] Furthermore, a fixed pin seat is arranged on the arm connection seat. A pin shaft is arranged in the fixed pin seat in a movable manner. A pin hole is arranged at the end of the arm. When the arm is unfolded to a fixed position, the pin shaft can be inserted into the pin hole to fix the arm.

[0007] Furthermore, a leg connection seat is installed at the lower part of the fuselage. A leg is connected to the leg connection seat in a hinged manner.

[0008] Furthermore, the leg includes a short leg and a long leg. The short leg is connected to the lower end of the fuselage, and the long leg is connected to the higher end of the fuselage. The lowermost ends of the long leg and the short leg are on the same horizontal plane.

[0009] Furthermore, a GPS component and a camera are also installed on the fuselage.

[0010] Furthermore, a power battery is connected to the upper part of the fuselage through a strap. The power battery is connected with a male plug. A female plug is arranged on the fuselage. The power battery is connected to the fuselage through the male plug and the female plug.

[0011] Furthermore, a flight control main board is installed inside the fuselage. The power battery is electrically connected to the flight control main board. The flight control main board is electrically connected to an electronic speed controller, and the electronic speed controller is electrically connected to the motor.

[0012] The beneficial effects of the present utility model are as follows:

[0013] The conventional settings of the fuselage and the arms are modified, such that the arms form a certain angle with the fuselage, and the angle is 7 to 10 degrees. In this way, it is ensured that the first arm and the second arm are on different horizontal planes, and there will be no interference after the first arm and the second arm are folded. The length of the arms is the same as that of the fuselage, and after folding, they are fixed on both sides of the fuselage. At the same time, the motor of the first arm faces downward, and the motor of the second arm faces upward, and there will be no interference between the motor and the arm. The drone is stored by folding, which is convenient to use and occupies a small space. Description of the Drawings

[0014] Figure 1 It is a three-dimensional structural schematic diagram of the present utility model;

[0015] Figure 2 It is a front view structural schematic diagram of the present utility model;

[0016] In the drawings:

[0017] 1. Fuselage, 2. Arm connection seat, 3. Leg connection seat, 4. First arm, 5. Second arm, 6. Motor, 7. Propeller, 8. Short leg, 9. Long leg, 10. GPS component, 11. Camera, 12. Power battery. Detailed Embodiments

[0018] To make the purpose, technical solutions and advantages of the implementation of the present utility model clearer, the following will combine the attached drawings of the present utility model Figure 1 ~Attached Figure 2 to describe the present utility model in more detail.

[0019] The following description is used to disclose the present utility model so that those skilled in the art can implement the present utility model. The preferred embodiments described below are only examples, and those skilled in the art can think of other obvious variations. The basic principles defined in the following description can be applied to other implementation schemes, variation schemes, improvement schemes, equivalent schemes, and other technical schemes that do not deviate from the spirit and scope of the present utility model.

[0020] A structure of a drone's staggered wing fuselage 1 provided by the present utility model includes a fuselage 1. The angle between the fuselage 1 and the horizontal plane is an acute angle. An arm connection seat 2 is installed on the side of the fuselage 1. An arm is connected to the arm connection seat 2 in a hinged manner. A motor 6 is arranged at the end of the arm, and the motor 6 is connected to a propeller 7. The arm includes a first arm 4 and a second arm 5. The first arm 4 is hinged to the arm connection seat 2 at a lower position, and the second arm 5 is hinged to the arm connection seat 2 at a higher position. The motor 6 arranged at the end of the first arm 4 is located below the first arm 4, and the motor 6 arranged at the end of the second arm 5 is located above the second arm 5. A fixed pin seat is arranged on the arm connection seat 2, and a pin shaft is arranged in the fixed pin seat in a movable manner. A pin hole is arranged at the end of the arm. When the arm is unfolded to a fixed position, the pin shaft can be inserted into the pin hole to fix the arm. A leg connection seat 3 is installed at the lower part of the fuselage 1, and a leg is connected to the leg connection seat 3 in a hinged manner. The leg includes a short leg 8 and a long leg 9. The short leg 8 is connected to the lower end of the fuselage 1, and the long leg 9 is connected to the higher end of the fuselage 1. The lowermost ends of the long leg 9 and the short leg 8 are on the same horizontal plane. A GPS component 10 and a camera 11 are also installed on the fuselage 1. A power battery 12 is connected to the upper part of the fuselage 1 through a strap. The power battery 12 is connected with a male plug, and a female plug is arranged on the fuselage 1. The power battery 12 is connected to the fuselage 1 through the male plug and the female plug. A flight control main board is installed inside the fuselage 1. The power battery 12 is electrically connected to the flight control main board, the flight control main board is electrically connected to an electronic speed controller, and the electronic speed controller is electrically connected to the motor 6.

[0021] The embodiments of the present utility model are as follows:

[0022] The structure of the drone's staggered wing fuselage 1 includes a fuselage 1. The angle between the fuselage 1 and the horizontal plane is an acute angle, and the angle is 7 to 10 degrees. An arm connection seat 2 is installed on the side of the fuselage 1. There are 4 arm connection seats 2, which are respectively on both sides of the fuselage 1. The arm connection seat 2 is in a horizontal position, so an angle of 7 to 10 degrees is also formed between the arm connection seat 2 and the fuselage 1, which ensures that the first arm 4 and the second arm 5 are on different horizontal planes, and no interference will occur when the first arm 4 and the second arm 5 are folded.

[0023] An arm is connected to the arm connection seat 2 in a hinged manner, and the arm can be folded. The length of the arm is the same as the length of the fuselage 1. After folding, it is fixed on both sides of the fuselage 1. The arm includes a first arm 4 and a second arm 5. Except for the different placement positions, the first arm 4 and the second arm 5 have no difference in length and diameter. The first arm 4 is hinged to the arm connection seat 2 at a lower position, and the second arm 5 is hinged to the arm connection seat 2 at a higher position.

[0024] The motor 6 provided at the end of the first arm 4 is located below the first arm 4, and the motor 6 provided at the end of the second arm 5 is located above the second arm 5. The motor 6 of the first arm 4 faces downward, and the motor 6 of the second arm 5 faces upward. There will be no interference between the motor 6 and the arm. The motor 6 is provided at the end of the arm, and the motor 6 is connected to a propeller 7. The propeller 7 includes two blades. When unfolded, the angle between the two blades is 180 degrees. When stored, the two blades can be folded.

[0025] A fixed pin seat is provided on the arm connection seat 2, and a pin shaft is movably provided in the fixed pin seat. A pin hole is provided at the end of the arm. When the arm is unfolded to the fixed position, the pin shaft can be inserted into the pin hole to fix the arm.

[0026] The lower part of the fuselage 1 is equipped with a leg connection seat 3, and legs are connected to the leg connection seat 3 in a hinged manner. The legs include two short legs 8 and two long legs 9. The short legs 8 are connected to the lower end of the fuselage 1, and the long legs 9 are connected to the higher end of the fuselage 1. The lowermost ends of the long legs 9 and the short legs 8 are on the same horizontal plane.

[0027] The upper part of the fuselage 1 is connected with a power battery 12 through a strap, which is convenient for disassembly and replacement. The power battery 12 is connected with a male plug, and a female plug is provided on the fuselage 1. The power battery 12 is connected to the fuselage 1 through the male plug and the female plug, and connection can be facilitated in this way.

[0028] A flight control main board is installed inside the fuselage 1. The flight control main board is electrically connected to the GPS component 10 and the camera 11. The power battery 12 is electrically connected to the flight control main board. The flight control main board is electrically connected to an electronic speed controller, and the electronic speed controller is electrically connected to the motor 6. An altimeter, a magnetic compass, a flight controller, an acceleration sensor, a gyroscope and a remote control receiver are also provided on the flight control main board.

[0029] Those skilled in the art should understand that in the disclosure of the specification, the orientation or positional relationship indicated by the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limiting the present invention.

[0030] It can be understood that the term "one" should be understood as "at least one" or "one or more". That is, in one embodiment, the number of one element can be one, and in other embodiments, the number of this element can be multiple. The term "one" should not be construed as limiting the quantity.

[0031] Those skilled in the art should understand that the embodiments of the present utility model described above and shown in the accompanying drawings are only examples and do not limit the present utility model. The advantages of the present utility model have been fully and effectively realized. The functions and structural principles of the present utility model have been demonstrated and explained in the embodiments, and without departing from the principles, any deformation or modification of the embodiments of the present utility model is possible.

Claims

1. A UAV staggered wing fuselage structure, characterized by: The invention comprises a fuselage, wherein the angle between the fuselage and the horizontal plane is an acute angle, an arm connecting seat is installed on the side of the fuselage, an arm is connected to the arm connecting seat in an articulated manner, a motor is arranged at the end of the arm, and the motor is connected to a propeller.

2. The UAV staggered-wing fuselage structure according to claim 1 is characterized in that: The machine arm comprises a first machine arm and a second machine arm, wherein the first machine arm is hinged to a machine arm connecting seat at a lower position, and the second machine arm is hinged to an machine arm connecting seat at a higher position.

3. The UAV staggered-wing fuselage structure according to claim 2 is characterized in that: The motor disposed at the end of the first arm is located below the first arm, and the motor disposed at the end of the second arm is located above the second arm.

4. The UAV staggered-wing fuselage structure according to claim 2 is characterized in that: A fixed pin seat is arranged on the machine arm connecting seat, a pin shaft is movably arranged in the fixed pin seat, a pin hole is arranged at the end of the machine arm, and when the machine arm is unfolded to a fixed position, the pin shaft can be inserted into the pin hole to fix the machine arm.

5. The UAV staggered-wing fuselage structure according to claim 1 is characterized in that: A leg connecting seat is installed at the lower part of the fuselage, and the leg connecting seat is connected with the legs in a hinged manner.

6. The UAV staggered-wing fuselage structure according to claim 5, characterized in that: The legs include a short leg and a long leg, the short leg is connected to a lower end of the fuselage, the long leg is connected to a higher end of the fuselage, and the lowest ends of the long leg and the short leg are on the same horizontal plane.

7. The UAV staggered-wing fuselage structure according to claim 1 is characterized in that: A GPS component and a camera are also installed on the fuselage.

8. The UAV staggered-wing fuselage structure according to claim 1, characterized in that: The upper part of the fuselage is connected to a power battery via a strap, the power battery is connected to a male plug, a female plug is arranged on the fuselage, and the power battery is connected to the fuselage via the male plug and the female plug.

9. The UAV staggered-wing fuselage structure according to claim 8, characterized in that: A flight control mainboard is installed inside the fuselage, the power battery is electrically connected to the flight control mainboard, the flight control mainboard is electrically connected to an electronic speed regulator, and the electronic speed regulator is electrically connected to the motor.

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