阅读说明：本技术 一种固定翼无人机的保护装置 (Fixed wing unmanned aerial vehicle's protection device ) 是由 史文芳 孟令兵 于 2019-12-03 设计创作，主要内容包括：本发明公开了一种固定翼无人机的保护装置,包括带有顶盖的壳体,所述壳体内部设置有钢制滤网和拉伸装置,钢制滤网上安装有降落保护伞；拉伸装置包括连接杆,连接杆上端套设橡胶头,橡胶头和壳体内壁紧贴且为滑动连接；连接杆底部固定有铁块,而壳体的底壁固定有电磁铁,电磁铁上连接有用于检测无人机飞行状态并控制电磁铁的控制组件；连接杆的侧壁还设置有穿过壳体的外部按压杆,并且壳体侧壁设置有供外部按压杆沿连接杆轴向滑动的滑槽；连接杆位于外部按压杆的下方套设有弹簧,弹簧底部抵触壳体底壁；当电磁铁吸附铁块时,弹簧处于压缩状态。本发明在一定程度上可以减少固定翼无人机在坠落时的冲击力,从而达到保护无人机的效果。(The invention discloses a protective device of a fixed wing unmanned aerial vehicle, which comprises a shell with a top cover, wherein a steel filter screen and a stretching device are arranged in the shell, and a parachute is arranged on the steel filter screen; the stretching device comprises a connecting rod, the upper end of the connecting rod is sleeved with a rubber head, and the rubber head is tightly attached to the inner wall of the shell and is in sliding connection with the inner wall of the shell; an iron block is fixed at the bottom of the connecting rod, an electromagnet is fixed at the bottom wall of the shell, and a control assembly for detecting the flight state of the unmanned aerial vehicle and controlling the electromagnet is connected to the electromagnet; the side wall of the connecting rod is also provided with an external pressing rod which penetrates through the shell, and the side wall of the shell is provided with a sliding groove for the external pressing rod to slide along the axial direction of the connecting rod; a spring is sleeved below the external pressing rod of the connecting rod, and the bottom of the spring is abutted against the bottom wall of the shell; when the electromagnet adsorbs the iron block, the spring is in a compressed state. The invention can reduce the impact force of the fixed wing unmanned aerial vehicle when falling to a certain extent, thereby achieving the effect of protecting the unmanned aerial vehicle.)

1. A protection device of a fixed wing unmanned aerial vehicle is characterized by comprising a shell with a top cover, wherein a steel filter screen and a stretching device are arranged in the shell, and a parachute is arranged on the steel filter screen; the stretching device comprises a connecting rod, the upper end of the connecting rod is sleeved with a rubber head, and the rubber head is tightly attached to the inner wall of the shell and is in sliding connection with the inner wall of the shell; an iron block is fixed at the bottom of the connecting rod, an electromagnet is fixed at the bottom wall of the shell, and a control assembly for detecting the flight state of the unmanned aerial vehicle and controlling the electromagnet is connected to the electromagnet; the side wall of the connecting rod is also provided with an external pressing rod penetrating through the shell, and the side wall of the shell is provided with a sliding groove for the external pressing rod to slide along the axial direction of the connecting rod; a spring is sleeved below the external pressing rod of the connecting rod, and the bottom of the spring is abutted against the bottom wall of the shell; and when the electromagnet adsorbs the iron block, the spring is in a compressed state.

2. The device as claimed in claim 1, wherein the housing is made of carbon fiber, and one side of the top cover is hinged to the housing and the other side is clamped to the housing.

3. The device as claimed in claim 1, wherein the inner wall of the housing is provided with a limiting groove, and the steel screen is mounted in the limiting ring.

4. The apparatus of claim 1, wherein the control unit comprises a flight status monitor sensor, an STC51 single chip microcomputer, and a power source.

5. The apparatus of claim 1, wherein the flight condition monitoring sensor comprises an angle sensor and a gravitational acceleration sensor.

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a protection device of a fixed-wing unmanned aerial vehicle.

Background

Along with the continuous maturity of unmanned aerial vehicle trade, unmanned aerial vehicle's function is also healthy gradually, also begins to use unmanned aerial vehicle to provide help in each field trade. The fixed wing unmanned aerial vehicle is frequently used for entertainment teaching, large-range terrain surveying, aerial surveying, water and soil conservation reconnaissance and other works due to the technical characteristics of high flying speed, long range, large reconnaissance cruising range, stability in the flying process and the like. But fixed wing unmanned aerial vehicle also has a lot of defects at present, and fixed wing unmanned aerial vehicle is great because of controlling the degree of difficulty coefficient, with higher costs, structure complicacy, crash accident rate height. And the take-off and landing of the fixed-wing unmanned aerial vehicle are often limited by conditions such as a runway and an external environment, the fixed-wing unmanned aerial vehicle cannot hover in the air, the price is high, the operation difficulty is high, and the probability of accident of landing and crash is high. Therefore, the design of the protection device of the fixed-wing unmanned aerial vehicle is particularly important when the fixed-wing unmanned aerial vehicle breaks down or provides landing protection. On combining current science and technology basis, I provide a fixed wing unmanned aerial vehicle's protection device design by using for reference the decline principle of parachute, through the monitoring to fixed wing unmanned aerial vehicle angular velocity and acceleration of gravity. If fixed wing unmanned aerial vehicle is in when the crash state, protection device can pop out the fender umbrella immediately, guarantees unmanned aerial vehicle's safe descending.

Disclosure of Invention

In order to solve the problems, the invention provides a safer and more convenient protection device for a fixed-wing unmanned aerial vehicle, and the technical scheme of the invention is as follows:

a protection device of a fixed wing unmanned aerial vehicle comprises a shell with a top cover; a steel filter screen and a stretching device are arranged in the shell, and a parachute is arranged on the steel filter screen; the stretching device comprises a connecting rod, the upper end of the connecting rod is sleeved with a rubber head, and the rubber head is tightly attached to the inner wall of the shell and is in sliding connection with the inner wall of the shell; an iron block is fixed at the bottom of the connecting rod, an electromagnet is fixed at the bottom wall of the shell, and a control assembly for detecting the flight state of the unmanned aerial vehicle and controlling the electromagnet is connected to the electromagnet; the side wall of the connecting rod is also provided with an external pressing rod penetrating through the shell, and the side wall of the shell is provided with a sliding groove for the external pressing rod to slide along the axial direction of the connecting rod; a spring is sleeved below the external pressing rod of the connecting rod, and the bottom of the spring is abutted against the bottom wall of the shell; and when the electromagnet adsorbs the iron block, the spring is in a compressed state.

Furthermore, the shell is made of carbon fiber materials, one side of the top cover is hinged to the shell, and the other side of the top cover is connected with the shell in a clamping mode.

Further, the inner wall of the shell is provided with a limiting groove, and the steel filter screen mounting groove is in the limiting groove.

Further, the control assembly comprises a flight state monitoring sensor, an STC51 single chip microcomputer and a power supply.

Further, the flight state monitoring sensor comprises an angle sensor and a gravity acceleration sensor.

Compared with the prior art, the invention adopting the technical scheme has the following technical effects:

when detecting that fixed wing unmanned aerial vehicle has the trend of falling through the flight condition monitoring sensor among the control assembly, the power off of single chip microcomputer control electro-magnet, connecting rod upward movement, thereby the air in the extrusion device is broken the top cap and is let the automatic parachute-opening of parachute-protection, protects fixed wing unmanned aerial vehicle.

Drawings

FIG. 1 is a schematic view of the internal structure of the present embodiment;

fig. 2 is an external structural view of the present embodiment.

Reference numerals: 1. a housing; 2. an external pressing lever; 3. a top cover; 4. a steel filter screen; 5. a limiting ring; 6. a rubber head; 7. a connecting rod; 8. a spring; 9. an iron block; 10. an electromagnet; 11. and a control component.

Detailed Description

The following detailed description of the embodiments of the present invention is provided in order to make the technical solution of the present invention easier to understand and understand.

With reference to fig. 1 and 2, the present embodiment provides a protection device for a fixed-wing drone, comprising a casing 1 with a top cover 3; the shell 1 is made of carbon fiber materials, one side of the top cover 3 is hinged to the shell 1, and the other side of the top cover is connected with the shell 1 in a clamping mode.

The casing 1 is inside to be provided with steel filter screen 4 and stretching device, 1 inner wall of casing is provided with the spacing groove, 4 mounting grooves spacing rings 5 of steel filter screen are interior. Install the parachute on the steel filter screen 4, should descend for use can the automatic parachute opening's of the circumstances under the pressure of withdrawal that has on the market current parachute.

The stretching device comprises a connecting rod 7, the upper end of the connecting rod 7 is sleeved with a rubber head 6, and the rubber head 6 is tightly attached to the inner wall of the shell 1 and is in sliding connection with the inner wall; an iron block 9 is fixed at the bottom of the connecting rod 7, an electromagnet 10 is fixed at the bottom wall of the shell 1, and a control assembly 11 for detecting the flight state of the unmanned aerial vehicle and controlling the electromagnet 10 is connected to the electromagnet 10; the control assembly 11 comprises a flight state monitoring sensor, an STC51 single chip microcomputer and a power supply. The flight state monitoring sensor comprises 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 penetrating through the shell 1, and the side wall of the shell 1 is provided with a sliding groove for the external pressing rod 2 to slide along the axial direction of the connecting rod 7; a spring 8 is sleeved below the external pressing rod 2 of the connecting rod 7, and the bottom of the spring 8 is abutted against the bottom wall of the shell 1; and when the electromagnet 10 attracts the iron block 9, the spring 8 is in a compressed state.

The working principle is as follows: when the parachute landing protection device is used, the power switch of the device is turned on to electrify the electromagnet 10, the top cover 3 is opened, the parachute is folded, the tail of the parachute is placed downwards on the steel filter screen 4, the rope of the parachute is fixed on the steel filter screen 3, and then the parachute is sealed by the top cover 3. Then, the external pressing lever 2 is pressed downward by a hand press to bring the iron block 9 into close contact with the electromagnet 10, and the external pressing lever 2 is released when the electromagnet 10 and the iron block 9 are attracted. The device is fixed at the tail of the fixed-wing unmanned aerial vehicle and can be used.

When flight state monitoring sensor (angle sensor and acceleration of gravity sensor) in the control assembly 11 detected fixed wing unmanned aerial vehicle's angle or decurrent acceleration sudden change, single chip microcomputer control electro-magnet 10 outage, compressed steel spring 8 promotes the outside according to pressure bar 2 upward movement, the rubber head 6 extrusion casing 1 inside air of connecting rod 7 anterior segment, the rapid opening of parachute when top cap 3 is washed away by compressed gas, thereby let fixed wing unmanned aerial vehicle safety landing, realize the protection to fixed wing unmanned aerial vehicle.

The above are only typical examples of the present invention, and besides, the present invention may have other embodiments, and all the technical solutions formed by equivalent substitutions or equivalent changes are within the scope of the present invention as claimed.