A protective device for fixed-wing unmanned aerial vehicle

Abstract

The present invention discloses a protective device for a fixed-wing UAV, comprising a housing with a top cover, a steel filter screen and a stretching device are arranged inside the housing, and a parachute is installed on the steel filter screen; the stretching device comprises a connecting rod, a rubber head is sleeved on the upper end of the connecting rod, and the rubber head is in close contact with the inner wall of the housing and is slidably connected; an iron block is fixed to the bottom of the connecting rod, and an electromagnet is fixed to the bottom wall of the housing, and a control component for detecting the flight state of the UAV and controlling the electromagnet is connected to the electromagnet; the side wall of the connecting rod is also provided with an external pressing rod passing through the housing, and the side wall of the housing is provided with a slide groove for the external pressing rod to slide along the axial direction of the connecting rod; the connecting rod is located below the external pressing rod and is sleeved with a spring, and the bottom of the spring contacts the bottom wall of the housing; when the electromagnet absorbs the iron block, the spring is in a compressed state. The present invention can reduce the impact force of the fixed-wing UAV when it falls to a certain extent, thereby achieving the effect of protecting the UAV.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicles, and in particular to a protective device for a fixed-wing unmanned aerial vehicle. Background Art

[0002] As the drone industry continues to mature, the functions of drones are gradually becoming more complete, and drones are beginning to be used in various fields and industries to provide assistance. Fixed-wing drones are often used for entertainment teaching, large-scale terrain surveys, aerial surveys, soil and water conservation reconnaissance, etc. due to their technical characteristics such as fast flight speed, long range, large reconnaissance and cruising range, and stability during flight. However, fixed-wing drones also have many defects at present. Fixed-wing drones have a high control difficulty coefficient, high cost, complex structure, and high crash rate. In addition, the take-off and landing of fixed-wing drones are often restricted by conditions such as runways and external environments. They cannot hover in the air, and they are expensive, difficult to operate, and the probability of landing and crashing is relatively high. Therefore, the design of a protective device for fixed-wing drones is particularly important when fixed-wing drones fail or provide landing protection. Based on the existing scientific and technological foundation, I proposed a design of a protective device for fixed-wing drones by drawing on the descent principle of parachutes, and monitoring the angular velocity and gravity acceleration of fixed-wing drones. If the fixed-wing drone is in a crash state, the protective device will immediately pop up the parachute to ensure the safe landing of the drone. Summary of the invention

[0003] In order to solve the above problems, the present invention provides a safer and more convenient protective device for a fixed-wing UAV. The technical solution of the present invention is as follows:

[0004] A protective device for a fixed-wing unmanned aerial vehicle comprises a shell with a top cover; a steel filter screen and a stretching device are arranged inside the shell, and a parachute is installed on the steel filter screen; the stretching device comprises a connecting rod, a rubber head is sleeved on the upper end of the connecting rod, and the rubber head is tightly attached to the inner wall of the shell and is slidably connected; an iron block is fixed to the bottom of the connecting rod, and an electromagnet is fixed to the bottom wall of the shell, and a control component for detecting the flight status of the unmanned aerial vehicle and controlling the electromagnet is connected to the electromagnet; an external pressing rod passing through the shell is also arranged on the side wall of the connecting rod, and a sliding groove for the external pressing rod to slide along the axial direction of the connecting rod is arranged on the side wall of the shell; a spring is sleeved on the connecting rod below the external pressing rod, and the bottom of the spring contacts the bottom wall of the shell; and when the electromagnet absorbs the iron block, the spring is in a compressed state.

[0005] Furthermore, the shell is made of carbon fiber material, and one side of the top cover is hinged to the shell, and the other side is clamped to the shell.

[0006] Furthermore, a limiting groove is provided on the inner wall of the shell, and the steel filter is installed in the limiting groove.

[0007] Furthermore, the control component includes a flight status monitoring sensor, an STC51 single chip microcomputer and a power supply.

[0008] Furthermore, the flight status monitoring sensor includes an angle sensor and a gravity acceleration sensor.

[0009] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0010] When the flight status monitoring sensor in the control component detects that the fixed-wing UAV has a tendency to crash, the single-chip microcomputer controls the electromagnet to cut off the power, and the connecting rod moves upward, squeezing the air in the device, pushing open the top cover, and allowing the landing parachute to automatically open, thus protecting the fixed-wing UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 Schematic diagram of the internal structure of this embodiment;

[0012] Figure 2 This is the external structure diagram of this embodiment.

[0013] Figure numerals: 1. Shell; 2. External pressing rod; 3. Top cover; 4. Steel filter; 5. Limiting ring; 6. Rubber head; 7. Connecting rod; 8. Spring; 9. Iron block; 10. Electromagnet; 11. Control component. DETAILED DESCRIPTION

[0014] The specific implementation modes of the present invention are further described below in conjunction with the accompanying drawings to make the technical solutions of the present invention easier to understand and grasp.

[0015] Reference Figure 1 and Figure 2 The present embodiment provides a protective device for a fixed-wing UAV, including a shell 1 with a top cover 3; the shell 1 is made of carbon fiber material, and one side of the top cover 3 is hinged to the shell 1, and the other side is clamped to the shell 1.

[0016] The housing 1 is provided with a steel filter 4 and a stretching device, the inner wall of the housing 1 is provided with a limit groove, and the steel filter 4 is installed in the limit ring 5. A parachute is installed on the steel filter 4, and the parachute can be selected from the existing parachute on the market that can automatically open when the pressure is removed.

[0017] The stretching device includes a connecting rod 7, a rubber head 6 is sleeved on the upper end of the connecting rod 7, and the rubber head 6 is tightly attached to the inner wall of the shell 1 and is slidably connected; an iron block 9 is fixed to the bottom of the connecting rod 7, and an electromagnet 10 is fixed to the bottom wall of the shell 1, and a control component 11 for detecting the flight state of the drone and controlling the electromagnet 10 is connected to the electromagnet 10; the control component 11 includes a flight state monitoring sensor, an STC51 single-chip microcomputer and a power supply. The flight state monitoring sensor includes an angle sensor and a gravity acceleration sensor. The side wall of the connecting rod 7 is also provided with an external pressing rod 2 passing through the shell 1, and the side wall of the shell 1 is provided with a slide groove for the external pressing rod 2 to slide along the axial direction of the connecting rod 7; the connecting rod 7 is located below the external pressing rod 2 and is sleeved with a spring 8, and the bottom of the spring 8 contacts the bottom wall of the shell 1; and when the electromagnet 10 adsorbs the iron block 9, the spring 8 is in a compressed state.

[0018] Working principle: When in use, turn on the power switch of the device to energize the electromagnet 10, open the top cover 3, fold the parachute and place it with the tail facing down on the steel filter 4, fix the rope of the parachute on the steel filter 3, and then seal the parachute with the top cover 3. Then, press the external pressing rod 2 downward by hand to make the iron block 9 close to the electromagnet 10, and release the external pressing rod 2 when the electromagnet 10 and the iron block 9 are adsorbed. Fix the device to the tail of the fixed-wing drone and it can be used.

[0019] When the flight status monitoring sensors (angle sensors and gravity acceleration sensors) in the control component 11 detect a sudden change in the angle or downward acceleration of the fixed-wing UAV, the single-chip microcomputer controls the electromagnet 10 to cut off the power, and the compressed steel spring 8 pushes the external pressing rod 2 to move upward. The rubber head 6 at the front section of the connecting rod 7 squeezes the air inside the shell 1, and the top cover 3 is opened by the compressed gas while the landing parachute opens rapidly, allowing the fixed-wing UAV to land safely, thereby protecting the fixed-wing UAV.

[0020] Of course, the above are only typical examples of the present invention. In addition, the present invention may also have many other specific implementations. All technical solutions formed by equivalent replacement or equivalent transformation fall within the scope of protection required by the present invention.

Claims

1. A protective device for a fixed-wing UAV, characterized in that: It comprises a shell with a top cover, wherein a steel filter screen and a stretching device are arranged inside the shell, and a parachute is installed on the steel filter screen; the stretching device comprises a connecting rod, and a rubber head is sleeved on the upper end of the connecting rod, and the rubber head is tightly attached to the inner wall of the shell and is slidably connected; an iron block is fixed to the bottom of the connecting rod, and an electromagnet is fixed to the bottom wall of the shell, and a control component for detecting the flight status of the drone and controlling the electromagnet is connected to the electromagnet; an external pressing rod passing through the shell is also arranged on the side wall of the connecting rod, and a sliding groove for the external pressing rod to slide axially along the connecting rod is arranged on the side wall of the shell; the connecting rod is sleeved with a spring below the external pressing rod, and the bottom of the spring contacts the bottom wall of the shell; and when the electromagnet absorbs the iron block, the spring is in a compressed state, The shell is made of carbon fiber material, and one side of the top cover is hinged to the shell, and the other side is clamped to the shell. The inner wall of the shell is provided with a limiting groove, and the steel filter is internally installed with a groove limiting ring.

2. A protective device for a fixed-wing UAV as claimed in claim 1, characterized in that: The control component includes a flight status monitoring sensor, an STC51 single chip microcomputer and a power supply.

3. A protective device for a fixed-wing UAV as claimed in claim 2, characterized in that: The flight status monitoring sensor includes an angle sensor and a gravity acceleration sensor.

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