CN215361867U

CN215361867U - Parachute device for emergency situation of unmanned aerial vehicle aircraft

Info

Publication number: CN215361867U
Application number: CN202120470574.0U
Authority: CN
Inventors: 吉玮
Original assignee: Suzhou Hangan Intelligent Technology Co ltd
Current assignee: Suzhou Hangan Intelligent Technology Co ltd
Priority date: 2021-03-04
Filing date: 2021-03-04
Publication date: 2021-12-31
Anticipated expiration: 2031-03-04

Abstract

The utility model discloses a parachute device for an unmanned aerial vehicle aircraft in emergency, which relates to the field of unmanned aerial vehicles and comprises a shell, wherein an insert rod is fixedly arranged in the middle of the lower end face of a baffle, a sleeve is sleeved at the lower end of the insert rod, the insert rod can slide in the sleeve, a first compression spring is fixedly connected between the insert rod and the sleeve, a transverse plate is fixedly arranged at the bottom end of the sleeve, a sliding block is arranged on the sliding rod in a sliding mode, a reset spring is fixedly arranged between the sliding block and the inner wall of a square groove, a movable plate is arranged at the lower end of the transverse plate, and two connecting rods are hinged to the upper end face of the movable plate. Switch controller can open the cap, and when the fusing copper wire, first compression spring can be ejecting with the sleeve, and when unmanned aerial vehicle contact ground, the connecting rod can drive slider extrusion reset spring to drive diaphragm and the first compression spring of sleeve extrusion, decompose the impulsive force between unmanned aerial vehicle and the ground, the injury that the impact force when effectual solution unmanned aerial vehicle and ground contact led to the fact the organism.

Description

Parachute device for emergency situation of unmanned aerial vehicle aircraft

Technical Field

The utility model relates to the field of unmanned aerial vehicles, in particular to a parachute device for an unmanned aerial vehicle aircraft in an emergency.

Background

Unmanned aerial vehicle wide application is in fields such as communication relay, emergency rescue, environmental monitoring and aerial photography but unmanned aerial vehicle is under abominable environment or when breaking down in the flight process, and therefore the unmanned aerial vehicle that the cost is not low probably crashes.

At present to the frequent crash of unmanned aerial vehicle, usually for unmanned aerial vehicle equipped with the parachute device, reduce unmanned aerial vehicle's the falling with this, but now many places have the forbidden height of flying, most forbidden height is at 120 meters, under this height, if unmanned aerial vehicle breaks down and stops flying, then the unmanned aerial vehicle chance stands the horse to fall, open the parachute on the way of falling, open the parachute on the way of the promotion in the storehouse, it is still very fast at the speed that unmanned aerial vehicle falls to the ground, avoided directly falling the aircraft in the air, but probably can't avoid unmanned aerial vehicle when falling the ground part to be broken by the collision.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a parachute device for an unmanned aerial vehicle aircraft in an emergency, and aims to solve the problems in the background technology.

In order to achieve the purpose, the utility model provides the following technical scheme:

a parachute device used in an unmanned aerial vehicle aircraft emergency comprises a shell, wherein one side of the upper end face of the shell is connected with a shell cover through a hinge, the middle of the shell is fixedly provided with a baffle, the upper end of the baffle is provided with a parachute structure, two sides of the upper end face of the baffle are provided with through holes, the middle of the lower end face of the baffle is fixedly provided with an insertion rod, the lower end of the insertion rod is sleeved with a sleeve, the insertion rod can slide in the sleeve, a first compression spring is fixedly connected between the insertion rod and the sleeve, the bottom end of the sleeve is fixedly provided with a transverse plate, the bottom end of the transverse plate is provided with a square groove, two ends of the square groove are fixedly provided with a sliding rod, the sliding rod is provided with a sliding block in a sliding manner, a reset spring is fixedly arranged between the sliding block and the inner wall of the square groove, a movable plate is arranged at the lower end of the transverse plate, and the upper end face of the sliding plate is hinged with two movable plates, and the other end of the connecting rod is hinged on the sliding block.

As a further scheme of the utility model: clamping blocks are arranged at two ends of the transverse plate and are connected with the transverse plate through telescopic springs.

As a still further scheme of the utility model: the fixture block is kept away from the one end of expanding spring and is installed the pulley, the spout has been seted up to shell bottom both sides.

As a still further scheme of the utility model: the parachute structure includes parachute package, roof, telescopic link and second compression spring, baffle up end middle part fixed mounting has the telescopic link, telescopic link top fixedly connected with roof, the cover is equipped with second compression spring on the telescopic link, second compression spring fixed connection is between roof and baffle, the parachute package has been placed on the roof, the parachute package is connected at the shell inner wall through the parachute rope.

As a still further scheme of the utility model: the sleeve both sides fixedly connected with locating plate, fixed mounting has the copper wire on the locating plate and passes the through-hole and connect on the roof, the fusing board has been placed in the through-hole, and fusing board and copper wire contact, fusing board one end is connected with the power cord, and the power cord links to each other with the switch controller of shell upper end one side.

Compared with the prior art, the utility model has the beneficial effects that: experience the organism when weightlessness sensor is in weightlessness status, can communicate the power cord and make fusing board work, can the on-off controller can open the cap simultaneously, the cap can be opened under the effect of hinge, when the fusing copper wire, the roof can be ejecting with the umbrella package under second compression spring's effect, first compression spring can be ejecting with the sleeve simultaneously, make diaphragm roll-off shell, when unmanned aerial vehicle contact ground, movable plate touching ground, the connecting rod can drive slider extrusion reset spring, and drive the first compression spring of diaphragm and sleeve extrusion, decompose the impulsive force between unmanned aerial vehicle and the ground, the injury that impact force when effectual solution unmanned aerial vehicle and ground contact led to the fact the organism.

Drawings

Fig. 1 is a schematic structural diagram of a parachute device for an unmanned aerial vehicle aircraft in an emergency.

Fig. 2 is a cross-sectional view of a parachute assembly for use in an unmanned aerial vehicle aircraft emergency.

Fig. 3 is a partially enlarged view of fig. 2 of a parachute assembly for use in an emergency situation with an unmanned aerial vehicle.

Wherein: 1-shell, 2-shell cover, 3-baffle, 4-umbrella bag, 5-top plate, 6-copper wire, 7-telescopic rod, 8-second compression spring, 9-first compression spring, 10-inserted link, 11-sleeve, 12-positioning plate, 13-transverse plate, 14-moving plate, 15-sliding rod, 16-sliding block, 17-reset spring, 18-connecting rod, 19-telescopic spring, 20-clamping block, 21-pulley, 22-fusing plate and 23-switch controller.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

Example one

Referring to fig. 1-3, a parachute device for an unmanned aerial vehicle aircraft in emergency comprises a housing 1, wherein a housing cover 2 is connected to one side of the upper end face of the housing 1 through a hinge, a baffle 3 is fixedly mounted in the middle of the housing 1, a parachute structure is mounted at the upper end of the baffle 3, through holes are formed in two sides of the upper end face of the baffle 3, an insertion rod 10 is fixedly mounted in the middle of the lower end face of the baffle 3, a sleeve 11 is sleeved on the lower end of the insertion rod 10, the insertion rod 10 can slide in the sleeve 11, a first compression spring 9 is fixedly connected between the insertion rod 10 and the sleeve 11, a transverse plate 13 is fixedly mounted at the bottom end of the sleeve 11, a square groove is formed in the bottom end of the transverse plate 13, slide rods 15 are fixedly mounted at two ends in the square groove, a slide block 16 is slidably arranged on the slide rod 15, and a reset spring 17 is fixedly mounted between the slide block 16 and the inner wall of the square groove, moving plate 14 has been placed to diaphragm 13 lower extreme, moving plate 14 up end articulates there are two connecting rods 18, and the other end of connecting rod 18 articulates on slider 16, and when moving plate 14 touching ground, connecting rod 18 can drive slider 16 extrusion reset spring 17 to drive diaphragm 13 and sleeve 11 extrusion first compression spring 9, decompose the impulsive force between unmanned aerial vehicle and the ground.

Further, the method comprises the following steps of; the two ends of the transverse plate 13 are provided with the fixture blocks 20, and the fixture blocks 20 are connected with the transverse plate 13 through the telescopic springs 19.

Further, the method comprises the following steps of; the pulley 21 is installed to the one end that the fixture block 20 kept away from expanding spring 19, the spout has been seted up to shell 1 bottom both sides, makes things convenient for diaphragm 13 to follow the interior roll-off of shell 1.

Further, the method comprises the following steps of; parachute structure includes parachute package 4, roof 5, telescopic link 7 and

second compression spring

8, 3 up end middle part fixed mounting of baffle has

telescopic link

7, 7 top fixedly connected with roofs of telescopic link 5, the cover is equipped with second compression spring 8 on the

telescopic link

7, 8 fixed connection of second compression spring are between roof 5 and baffle 3, parachute package 4 has been placed on roof 5, parachute package 4 is connected at 1 inner wall of shell through the parachute harness, through the second spring can be quick pop out shell 1 with parachute package 4.

Example two

On the basis of embodiment 1, because the interval of parachute package 4 and diaphragm 13 roll-off shell 1 time can cause the organism to fall to the ground and can not in time do the protection, so the following design has been done, 11 both sides fixedly connected with locating plate 12 of sleeve, fixed mounting has copper wire 6 and passes the through-hole and connect on roof 5 on locating plate 12, fuse plate 22 has been placed in the through-hole, and fuse plate 22 and copper wire 6 contact, fuse plate 22 one end is connected with the power cord, and the power cord links to each other with switch controller 23 of shell 1 upper end one side, can directly open the cap through the signal that the inductor spreads, and the fusing of copper wire 6 can pop out parachute package 4 and diaphragm 13 out shell 1 simultaneously.

The working principle of the utility model is as follows: when the unmanned aerial vehicle takes place emergency, unmanned aerial vehicle can become the whereabouts of free fall from the sky, when weightlessness inductor experienced the organism and was in weightlessness status, can communicate the power cord and make fusing plate 22 work, meeting on-off controller 23 can open cap 2 simultaneously, cap 2 can be opened under the effect of hinge, when fusing copper wire 6, roof 5 can be ejecting 4 with the parachute bag under the effect of second compression spring 8, first compression spring 9 can be ejecting with sleeve 11 simultaneously, make diaphragm 13 roll-off shell 1, when unmanned aerial vehicle contacts ground, movable plate 14 touching ground, connecting rod 18 can drive slider 16 extrusion reset spring 17, and drive diaphragm 13 and sleeve 11 extrusion first compression spring 9, decompose the impulsive force between unmanned aerial vehicle and the ground.

Although the preferred embodiments of the present patent have been described in detail, the present patent is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present patent within the knowledge of those skilled in the art.

Claims

1. The utility model provides a parachute device that unmanned aerial vehicle aircraft emergency used, includes shell (1), its characterized in that: the parachute comprises a shell cover (2) and is characterized in that one side of the upper end face of the shell (1) is connected with the shell cover (2) through a hinge, a baffle (3) is fixedly mounted in the middle of the shell (1), a parachute structure is mounted at the upper end of the baffle (3), through holes are formed in two sides of the upper end face of the baffle (3), an inserting rod (10) is fixedly mounted in the middle of the lower end face of the baffle (3), a sleeve (11) is sleeved on the lower end of the inserting rod (10), the inserting rod (10) can slide in the sleeve (11), a first compression spring (9) is fixedly connected between the inserting rod (10) and the sleeve (11), a transverse plate (13) is fixedly mounted at the bottom end of the sleeve (11), a square groove is formed in the bottom end of the transverse plate (13), sliding rods (15) are fixedly mounted at two ends of the square groove, a sliding block (16) is arranged on the sliding rod (15), and a reset spring (17) is fixedly mounted between the sliding block (16) and the inner wall of the square groove, a moving plate (14) is placed at the lower end of the transverse plate (13), two connecting rods (18) are hinged to the upper end face of the moving plate (14), and the other ends of the connecting rods (18) are hinged to the sliding blocks (16).

2. The parachute device for the unmanned aerial vehicle aircraft in the emergency situation as claimed in claim 1, wherein clamping blocks (20) are disposed at two ends of the transverse plate (13), and the clamping blocks (20) are connected with the transverse plate (13) through telescopic springs (19).

3. The parachute device that an unmanned aerial vehicle aircraft emergency used of claim 2, characterized in that, pulley (21) is installed to the one end that telescopic spring (19) was kept away from in fixture block (20), the spout has been seted up to shell (1) bottom both sides.

4. The parachute device that an unmanned aerial vehicle aircraft emergency used of claim 1, characterized in that, the parachute structure includes parachute package (4), roof (5), telescopic link (7) and second compression spring (8), baffle (3) up end middle part fixed mounting has telescopic link (7), telescopic link (7) top fixedly connected with roof (5), the cover is equipped with second compression spring (8) on telescopic link (7), second compression spring (8) fixed connection is between roof (5) and baffle (3), parachute package (4) have been placed on roof (5), parachute package (4) are connected at shell (1) inner wall through the parachute line.

5. The parachute device of claim 1-4, wherein the sleeves (11) are fixedly connected with positioning plates (12) on two sides, copper wires (6) are fixedly mounted on the positioning plates (12) and penetrate through holes to be connected to the top plate (5), fuse plates (22) are placed in the through holes, the fuse plates (22) are in contact with the copper wires (6), one ends of the fuse plates (22) are connected with power lines, and the power lines are connected with a switch controller (23) on one side of the upper end of the housing (1).