CN211336463U - Parachute bay ejection cover for unmanned aerial vehicle - Google Patents
Parachute bay ejection cover for unmanned aerial vehicle Download PDFInfo
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- CN211336463U CN211336463U CN201922396265.9U CN201922396265U CN211336463U CN 211336463 U CN211336463 U CN 211336463U CN 201922396265 U CN201922396265 U CN 201922396265U CN 211336463 U CN211336463 U CN 211336463U
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- lock pin
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to parachute bay launches lid for unmanned aerial vehicle, including the lid, be equipped with scalable removal's lockpin on the lid, the lockpin is connected with lockpin thrust piece, and the portable setting of lockpin thrust piece is on the lid, and the moving direction of lockpin thrust piece is mutually perpendicular with the moving direction of lockpin, and the removal through lockpin thrust piece can realize the removal of lockpin, the lid is circular lid, has three lockpin along its circumferencial direction evenly distributed, and the lockpin setting is in the lockpin guide way, and lockpin thrust piece sets up and puts at lid central point, including three evenly distributed's thrust plate, thrust plate one end runs through the lid setting perpendicularly, and the other end is connected with the drive plate perpendicularly, is equipped with the. The utility model discloses simple structure, convenient to use can guarantee the jettison device during operation, launches the quick separation of lid and umbrella cabin, guarantees the effect of launching of parachute, has very big market value, is worth wideling popularize and apply.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to parachute bay launches lid for unmanned aerial vehicle.
Background
Unmanned aerial vehicle can be in sometimes at the flight in-process and fall, unusual flight state such as out of control, in order to guarantee unmanned aerial vehicle's safety, generally can be furnished with the parachute on unmanned aerial vehicle, when unmanned aerial vehicle is in above-mentioned unusual flight state, through corresponding jettison device, pop out the parachute, and then can ensure unmanned aerial vehicle's safety to lead to unmanned aerial vehicle to damage because of out of control falls.
The ejection cover adopted by the ejection device plays a crucial role in the ejection effect of the parachute, at present, the common ejection cover is mostly in the magic tape mode, and after the parachute is ejected, the wings of the unmanned aerial vehicle still keep working under the large condition, so that the balance of the unmanned aerial vehicle can be directly influenced due to the conditions of swinging, gravity center offset and the like caused by the fact that the ejection cover cannot be completely ejected.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the problems existing in the prior art, providing a simple structure, convenient to use can guarantee to launch the parachute cabin ejection cover for the unmanned aerial vehicle of effect.
In order to achieve the above object, the utility model adopts the following technical scheme: the utility model provides an umbrella cabin ejection lid for unmanned aerial vehicle, includes the lid, be equipped with the lockpin of scalable removal on the lid, the lockpin is connected with lockpin thrust piece, lockpin thrust piece movable setting is on the lid, and the moving direction of lockpin thrust piece is mutually perpendicular with the moving direction of lockpin, can realize the removal of lockpin through the removal of lockpin thrust piece.
Preferably, the cover body is a circular cover body, and three lock pins are uniformly distributed along the circumferential direction of the cover body.
Preferably, the lock pin is disposed in the lock pin guide groove.
Preferably, a first spring is arranged between the lock pin and the cover body.
Preferably, the lock pin thrust piece is arranged at the center of the cover body and comprises three thrust plates which are uniformly distributed, one end of each thrust plate vertically penetrates through the cover body, the other end of each thrust plate is vertically connected with a driving plate, and a second spring is arranged between the driving plate and the cover body.
Preferably, the upper part of the thrust plate abuts against the lock pin, and the lower part of the thrust plate is provided with a lock pin groove matched with the lock pin.
Preferably, the lock pin is provided with a limit block matched with the lock pin groove.
After the technical scheme is adopted, the utility model discloses following beneficial effect has:
the utility model provides a parachute bay ejection cover for unmanned aerial vehicle, under the initial condition, through the design of the lock pin thrust piece to the butt of lock pin, can guarantee that the lock pin is propped tightly in the lock pin hole of the parachute bay, namely can guarantee the close connection of cover body and unmanned aerial vehicle parachute bay; through the design of the lock pin groove, when the lock pin thrust piece moves upwards under the internal pressure of the umbrella cabin, the lock pin can enter the lock pin groove under the action of the first spring, so that the lock pin can contract inwards to leave the lock pin hole of the umbrella cabin, namely the cover body is separated from the umbrella cabin; through the design of the lock pin guide groove, the stability of the telescopic action of the lock pin can be ensured; therefore, the utility model discloses simple structure, convenient to use can guarantee the jettison device during operation, launches the quick separation of lid and umbrella cabin, guarantees the effect of launching of parachute, has very big market value, is worth wideling popularize and apply.
Drawings
Fig. 1 is a schematic view of the internal structure of an umbrella cabin ejection cover for an unmanned aerial vehicle according to the present invention;
fig. 2 is a top view of the parachute bay ejection cover for the unmanned aerial vehicle of the present invention;
fig. 3 is a bottom view of the parachute bay ejection cover for the unmanned aerial vehicle of the present invention;
fig. 4 is a schematic view of a part of the structure of the parachute bay ejection cover for the unmanned aerial vehicle.
Wherein: lid 1, lockpin 2, lockpin thrust piece 3, lockpin guide way 4, first spring 5, thrust plate 6, drive plate 7, second spring 8, lockpin groove 9, stopper 10.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
As shown in fig. 1-4, for the utility model discloses a parachute bay launches lid for unmanned aerial vehicle, including lid 1, lid 1 is circular lid, be equipped with scalable removal's lockpin 2 on lid 1, it is specific, lockpin 2 is equipped with threely, along the circumferencial direction evenly distributed of lid 1, lockpin 2 sets up in lockpin guide way 4, and is equipped with first spring 5 between lockpin 2 and the lid 1.
One end of the lock pin 2 penetrates out of the cover body 1, the other end of the lock pin 2 is connected with a lock pin thrust piece 3, the lock pin thrust piece 3 can be movably arranged on the cover body 1, the moving direction of the lock pin thrust piece 3 is perpendicular to the moving direction of the lock pin 2, the lock pin 2 can move through the movement of the lock pin thrust piece 3, specifically, the lock pin thrust piece 3 is arranged in the center of the cover body 1 and comprises three thrust plates 6 which are uniformly distributed and respectively correspond to the three lock pins 2 one by one, one end of each thrust plate 6 perpendicularly penetrates through the cover body 1, the other end of each thrust plate is perpendicularly connected with a driving plate 7, and a second spring 8 is arranged between each driving plate 7 and the cover body 1, so that the lock pin 2 can horizontally move by overcoming the acting force of the first spring 5, and the lock pin thrust piece 3.
Furthermore, the upper part of the thrust plate 6 is abutted to the lock pin 2, and the lower part of the thrust plate 6 is provided with a lock pin groove 9 matched with the lock pin 2, so that when the thrust plate 6 moves upwards, the lock pin 2 can move inwards to enter the lock pin groove 9, and the lock pin 2 is provided with a limit block 10 matched with the lock pin groove 9, so that the moving distance of the lock pin 2 in the lock pin groove 9 can be ensured.
The utility model provides a pair of when unmanned aerial vehicle used parachute bay ejection cover to use, under the initial condition, lid 1 and parachute bay zonulae occludens, lockpin 2 is under the butt effect on thrust plate 6 upper portion promptly, overcome the effort of first spring 5 and stretch out outside 1 lid, the joint is downthehole at the lockpin of parachute bay, thereby realize the zonulae occludens of lid 1 and parachute bay, when unmanned aerial vehicle satisfied the parachute ejection condition, the propellant can be lighted to ignition in the parachute bay, the gaseous pressure that the propellant produced forces drive plate 7 to overcome the effort of second spring 8 and drives 6 rebound of thrust plate, when 6 lower part lockpin grooves 9 of thrust plate remove to lockpin 2's position, lockpin 2 inwards removes under the effect of first spring 5 and enters lockpin groove 9, lockpin 2 and the lockpin hole of parachute bay are disconnected from being connected, realize lid 1 promptly and launch and leave the parachute bay.
The utility model provides a parachute bay ejection cover for unmanned aerial vehicle, through the design of the upper part of the thrust plate 6 to the butt of the lock pin 2, the lock pin 2 can be guaranteed to butt in the lock pin hole of the parachute bay, namely the close connection of the cover body 1 and the parachute bay of the unmanned aerial vehicle can be guaranteed; through the design of the locking pin groove 9 at the lower part of the thrust plate 6, when the driving plate 7 moves upwards under the internal pressure of the umbrella cabin, the locking pin 2 enters the locking pin groove 9 under the action of the first spring 5, so that the locking pin hole is retracted inwards and separated from the umbrella cabin, and the cover body 1 is separated from the umbrella cabin; through the design of lockpin guide way 4, can guarantee the stability of lockpin 2 flexible action. Therefore, the utility model discloses simple structure, convenient to use can guarantee the jettison device during operation, launches the quick separation of lid and umbrella cabin, guarantees the effect of launching of parachute, has very big market value, is worth wideling popularize and apply.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. The utility model provides an umbrella cabin ejection cover for unmanned aerial vehicle, includes lid (1), its characterized in that: the cover body (1) is provided with a lock pin (2) capable of moving in a telescopic mode, the lock pin (2) is connected with a lock pin thrust piece (3), the lock pin thrust piece (3) can be movably arranged on the cover body (1), the moving direction of the lock pin thrust piece (3) is perpendicular to the moving direction of the lock pin (2), and the lock pin (2) can move through the movement of the lock pin thrust piece (3).
2. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 1, wherein: the cover body (1) is a circular cover body, and three lock pins (2) are uniformly distributed along the circumferential direction of the cover body.
3. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 1, wherein: the lock pin (2) is arranged in the lock pin guide groove (4).
4. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 1, wherein: a first spring (5) is arranged between the lock pin (2) and the cover body (1).
5. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 1, wherein: the lock pin thrust piece (3) is arranged at the center of the cover body (1) and comprises three thrust plates (6) which are uniformly distributed, one end of each thrust plate (6) vertically penetrates through the cover body (1), the other end of each thrust plate (6) is vertically connected with a driving plate (7), and a second spring (8) is arranged between each driving plate (7) and the cover body (1).
6. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 5, wherein: the upper part of the thrust plate (6) is abutted to the lock pin (2), and the lower part of the thrust plate (6) is provided with a lock pin groove (9) matched with the lock pin (2).
7. The canopy ejection cap for an unmanned aerial vehicle as claimed in claim 6, wherein: and the lock pin (2) is provided with a limiting block (10) matched with the lock pin groove (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922396265.9U CN211336463U (en) | 2019-12-27 | 2019-12-27 | Parachute bay ejection cover for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922396265.9U CN211336463U (en) | 2019-12-27 | 2019-12-27 | Parachute bay ejection cover for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211336463U true CN211336463U (en) | 2020-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922396265.9U Active CN211336463U (en) | 2019-12-27 | 2019-12-27 | Parachute bay ejection cover for unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN211336463U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650788A (en) * | 2021-09-01 | 2021-11-16 | 常州市小域智能科技有限公司 | Automatic parachute disengaging device |
| CN114291265A (en) * | 2021-12-10 | 2022-04-08 | 武汉航空仪表有限责任公司 | Mechanical multi-stage separation method and system |
-
2019
- 2019-12-27 CN CN201922396265.9U patent/CN211336463U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113650788A (en) * | 2021-09-01 | 2021-11-16 | 常州市小域智能科技有限公司 | Automatic parachute disengaging device |
| CN114291265A (en) * | 2021-12-10 | 2022-04-08 | 武汉航空仪表有限责任公司 | Mechanical multi-stage separation method and system |
| CN114291265B (en) * | 2021-12-10 | 2023-07-21 | 武汉航空仪表有限责任公司 | Mechanical multistage separation method and system |
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