Flight control device and unmanned aerial vehicle

Abstract

The utility model discloses a flight control device and an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a shell and further comprises a guide rod fixedly connected to the bottom of the shell, a mounting plate is slidably connected to the guide rod, and a buffer assembly is arranged between the mounting plate and the guide rod; the foot stool is fixedly connected to the bottom of the mounting plate, and the end part of the foot stool is rotationally connected with a limiting plate; according to the utility model, on one hand, impact force generated when the shell falls can be buffered, kinetic energy generated when the shell falls can be absorbed, and counter-acting force can be provided, so that components in the shell can be buffered, the amplitude of vibration can be reduced, and the components in the shell can be protected; and on the other hand, a guide rod can slide on a threaded groove, and in the sliding process, a limiting plate on the guide rod can automatically rotate to press the ground, so that the stability of the shell in contact with the ground is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a flight control device and an unmanned aerial vehicle. Background Art

[0002] Unmanned aerial vehicles, or UAVs for short, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are operated completely or intermittently autonomously by onboard computers. Unmanned aerial vehicles use radio remote control equipment and self-equipped program control devices to achieve control functions and complete preset tasks. In the civilian sector, the "UAV+" model has been formed and is widely used in non-manned industries such as aerial photography, surveying and mapping, disaster relief and rescue, agriculture, film and television shooting, monitoring, and express delivery.

[0003] After searching, the Chinese patent publication number CN207725600U discloses a UAV, including: blades, a hub, a propeller shaft, a swing arm, a swing arm shaft, a fuselage, a tripod, an aerial photography tripod and an aerial photography lens: the blades are arranged on both sides of the hub, and the blades are connected to the hub by an embedded manner; the hub is arranged on the upper part of the propeller shaft, and the hub is connected to the propeller shaft by a hub-shaft manner; the propeller shaft is arranged at the lower part of the hub, and the propeller shaft is connected to the swing arm by an embedded manner; the swing arm is arranged on the outside of the fuselage, and the swing arm is connected to the swing arm shaft by a hub-shaft manner; the tripod is arranged at the lower part of the fuselage, and the tripod is connected to the fuselage by bolts; the aerial photography tripod is arranged on the lower side of the fuselage, and the aerial photography tripod is connected to the fuselage by bolts.

[0004] In the above scheme, an impact force will be generated when the drone lands. Excessive impact force can easily cause vibration to the components inside the drone, causing damage. In addition, the drone slows down during landing, and due to inertia, the drone will shake to a certain extent when it contacts the ground. Utility Model Content

[0005] The purpose of the utility model is to solve the problem in the prior art that when a drone lands, impact force is generated. If the impact force is too large, it is easy to vibrate the components inside the drone and cause damage. In addition, when the drone lands, the speed slows down. Under the action of inertia, the drone will shake to a certain extent when it contacts the ground. A flight control device and a drone are proposed.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] A drone comprises a shell, and also comprises: a guide rod fixedly connected to the bottom of the shell, wherein a mounting plate is slidably connected to the guide rod, and a buffer assembly is arranged between the mounting plate and the guide rod; a tripod fixedly connected to the bottom of the mounting plate, and the end of the tripod is rotatably connected to a limit plate.

[0008] In order to facilitate buffering of the mounting plate, preferably, the buffer assembly includes a limit spring sleeved on the guide rod, and two ends of the limit spring are respectively fixedly connected to the housing and the mounting plate.

[0009] In order to facilitate the rotation of the guide rod during the movement, the end of the tripod is further fixedly connected to a guide cylinder, a threaded groove is opened on the inner wall of the guide cylinder, a guide rod is arranged in the guide cylinder, a ball is fixedly connected to the guide rod, the ball is slidably connected in the threaded groove, and the limit plate is fixedly connected to the guide rod.

[0010] In order to facilitate pushing the guide rod, preferably, a second airbag is provided in the guide cylinder, and the exterior of the second airbag abuts against the bottom of the guide rod.

[0011] In order to facilitate the supply of gas to the second airbag, preferably, a placement frame is fixedly connected to the mounting plate, the placement frame is provided with the first airbag, a pressure block is fixedly connected to the bottom of the outer shell, the pressure block extends into the placement frame and is fixedly connected to the outside of the first airbag, and the first airbag is connected to the second airbag.

[0012] A flight control device, wherein a flight control system and a GPS module are arranged in a shell of a UAV.

[0013] Compared with the prior art, the utility model provides a flight control device and a UAV, which have the following beneficial effects:

[0014] 1. The drone uses a limit spring mounted on the guide rod to buffer the impact force generated when the shell falls, absorb the kinetic energy generated when the shell falls, and provide a reaction force, thereby buffering the components in the shell and reducing the amplitude of vibration to protect the components inside the shell;

[0015] 2. The drone slides on the threaded groove through the guide rod, and during the sliding process, the limit plate on the guide rod will automatically rotate and press the ground. At this time, the limit plate will contact the ground to improve the stability of the shell when it contacts the ground.

[0016] The parts not involved in the device are the same as the existing technology or can be implemented by the existing technology. On the one hand, the utility model can buffer the impact force generated when the shell falls, absorb the kinetic energy generated when the shell falls, and provide a reaction force, so as to buffer the components in the shell and reduce the amplitude of vibration to protect the components inside the shell. On the other hand, the guide rod can be used to slide on the threaded groove, and during the sliding process, the limit plate on the guide rod will automatically rotate and press the ground. At this time, the limit plate will contact the ground, thereby improving the stability of the shell when it contacts the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a structural schematic diagram of a UAV shell proposed by the utility model;

[0018] Figure 2 A partial schematic diagram of a UAV proposed by the utility model;

[0019] Figure 3 This is a schematic diagram of a UAV tripod proposed by the utility model;

[0020] Figure 4 This is a schematic structural diagram of a cross-section of a guide tube of an unmanned aerial vehicle proposed in the utility model;

[0021] Figure 5 The utility model is a structural schematic diagram of a guide rod of a UAV.

[0022] In the figure: 1, shell; 101, guide rod; 102, pressure block; 2, mounting plate; 201, limit spring; 3, placement frame; 4, first airbag; 5, tripod; 6, guide cylinder; 601, threaded groove; 7, guide rod; 701, limit plate; 702, ball; 8, second airbag. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0024] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are 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 direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.

[0025] Example:

[0026] Reference Figure 1-Figure 5 A UAV comprises a shell 1, on which a connecting rod is arranged, on which a motor and a propeller are arranged, and the motor and the propeller are the power system of the UAV, and the motor provides power to drive the propeller to rotate, thereby generating lift and thrust, so that the shell 1 can fly, and components are arranged inside the shell 1 to cooperate with the motor and the propeller to work.

[0027] A guide rod 101 is fixedly connected to the bottom of the shell 1, and a mounting plate 2 is slidably connected to the guide rod 101. A limit spring 201 is sleeved on the guide rod 101, and both ends of the limit spring 201 are fixedly connected to the shell 1 and the mounting plate 2 respectively.

[0028] In addition, a tripod 5 is fixedly connected to the bottom of the mounting plate 2. The tripod 5 is used to support the housing 1 so that it can be placed on the ground and can also protect the bottom components of the housing 1 from damage.

[0029] The end of the tripod 5 is also fixedly connected to a guide cylinder 6, a threaded groove 601 is provided on the inner wall of the guide cylinder 6, a guide rod 7 is provided in the guide cylinder 6, a ball 702 is fixedly connected to the guide rod 7, the ball 702 is slidably connected in the threaded groove 601, and then the limit plate 701 is fixedly connected to the guide rod 7, and the threaded groove 601 and the ball 702 are provided in two groups, please refer to Figure 4 and Figure 5 as shown in .

[0030] Here, a second airbag 8 is also arranged in the guide cylinder 6, and the outside of the second airbag 8 is against the bottom of the guide rod 7, a placement frame 3 is fixedly connected to the mounting plate 2, a first airbag 4 is arranged in the placement frame 3, and the bottom of the first airbag 4 is fixedly connected to the mounting plate 2, a pressure block 102 corresponding to the cavity of the placement frame 3 is fixedly connected to the bottom of the outer shell 1, and the pressure block 102 extends into the placement frame 3 and is fixedly connected to the top of the first airbag 4, and then the first airbag 4 is connected to the second airbag 8.

[0031] When the shell 1 needs to land after taking off, the speed slows down during landing, and under the action of inertia, the shell 1 will shake to a certain extent when it contacts the ground. At this time, the limit spring 201 mounted on the guide rod 101 can be used to buffer the impact force generated when the shell 1 falls, absorb the kinetic energy generated when the shell 1 falls, and provide a reaction force, thereby buffering the components in the shell 1 and reducing the amplitude of vibration to protect the components inside the shell 1.

[0032] At the same time, when the shell 1 falls, the tripod 5 first contacts the ground, and then under the action of inertia, the pressure block 102 at the bottom of the mounting plate 2 will squeeze the first airbag 4 in the placement frame 3. At this time, the first airbag 4 will absorb a part of the kinetic energy generated when the shell 1 falls, and at the same time, the gas in the first airbag 4 will be transported to the second airbag 8 in the guide tube 6. At this time, the second airbag 8 will push the guide rod 7 to slide on the thread groove 601, and in the process of sliding, the limit plate 701 on the guide rod 7 will automatically rotate and press the ground. At this time, the limit plate 701 will contact the ground to improve the stability of the shell 1 when it contacts the ground. When it lands steadily on the ground, the gas in the second airbag 8 will automatically return to the first airbag 4. At this time, the position of the guide rod 7 can be manually rotated and reset as needed. The purpose of inflating the second airbag 8 is to apply a force to the guide rod 7 when the tripod 5 contacts the ground, thereby limiting the position of the limit plate 701.

[0033] Embodiment 2:

[0034] Reference Figure 1 A flight control device is provided with a flight control system and a GPS module in a housing 1. The flight control system is the core control device for the flight of a UAV, and includes a flight controller and related sensors. The flight controller is an embedded system that is responsible for receiving remote control instructions, processing sensor data, and controlling the flight status of the UAV. Sensors include accelerometers, gyroscopes, compasses, etc., which are used to sense the attitude, speed, direction and other parameters of the UAV. The GPS module is used to obtain the location information of the UAV, helping the UAV to locate, navigate and fly automatically. The GPS module can provide accurate location data, enabling the UAV to perform route planning, automatic return and other functions.

[0035] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A drone, comprising a housing (1), characterized in that: Also includes: A guide rod (101) fixedly connected to the bottom of the housing (1), Wherein, a mounting plate (2) is slidably connected to the guide rod (101), and a buffer assembly is provided between the mounting plate (2) and the guide rod (101); A foot stand (5) is fixedly connected to the bottom of the mounting plate (2), and an end of the foot stand (5) is rotatably connected to a limiting plate (701).

2. The drone according to claim 1, characterized in that: The buffer assembly comprises a limit spring (201) sleeved on the guide rod (101), and two ends of the limit spring (201) are respectively fixedly connected to the housing (1) and the mounting plate (2).

3. The drone according to claim 1, characterized in that: The end of the tripod (5) is fixedly connected to a guide cylinder (6), the inner wall of the guide cylinder (6) is provided with a threaded groove (601), a guide rod (7) is arranged in the guide cylinder (6), a ball (702) is fixedly connected to the guide rod (7), the ball (702) is slidably connected in the threaded groove (601), and the limit plate (701) is fixedly connected to the guide rod (7).

4. The drone according to claim 3, characterized in that: A second air bag (8) is arranged inside the guide cylinder (6), and the outside of the second air bag (8) is fixedly connected to the bottom of the guide rod (7).

5. The drone according to claim 4, characterized in that: A placement frame (3) is fixedly connected to the mounting plate (2), a first airbag (4) is arranged in the placement frame (3), a pressing block (102) is fixedly connected to the bottom of the housing (1), the pressing block (102) extends into the placement frame (3) and is fixedly connected to the outside of the first airbag (4), and the first airbag (4) is connected to the second airbag (8).

6. A flight control device, applied to the unmanned aerial vehicle according to claim 1, characterized in that: A flight control system and a GPS module are arranged in the housing (1).

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