阅读说明：本技术 一种用于投放无人机的多级分离系统 (Multistage separation system for throwing unmanned aerial vehicle ) 是由 邹云翔 张毅 季宝锋 要锦伟 郭浩 于 2021-07-30 设计创作，主要内容包括：本发明提供一种用于投放无人机的多级分离系统,包括：主体舱体；固定于所述主体舱体内部的推动器；与所述主体舱体的尾部插接固定的尾部减速结构；所述主体舱体内壁上还设置有至少两条导轨；所述至少两条导轨之间沿所述主体舱体内壁上设置有伞绳管路。本发明的方案提供的分离系统,结构简单且稳定,并能将无人机快速的推出舱体。(The invention provides a multistage separation system for launching an unmanned aerial vehicle, which comprises: a main body cabin; the pusher is fixed inside the main body cabin; the tail part speed reducing structure is fixedly connected with the tail part of the main body cabin body in an inserting mode; at least two guide rails are further arranged on the inner wall of the main body cabin body; an umbrella rope pipeline is arranged between the at least two guide rails along the inner wall of the main body cabin body. The separation system provided by the scheme of the invention has a simple and stable structure, and can quickly push the unmanned aerial vehicle out of the cabin body.)

1. A multi-stage separation system for launching a drone, comprising:

a main body cabin (2);

a pusher (4) fixed inside the main body cabin (2);

the tail part speed reducing structure is fixedly inserted with the tail part of the main body cabin body (2);

at least two guide rails are further arranged on the inner wall of the main cabin body (2);

an umbrella rope pipeline is arranged between the at least two guide rails along the inner wall of the main body cabin body (2).

2. The multistage separation system for launching a drone of claim 1, wherein the guide rail comprises:

a first rail (21), a second rail (22), and a third rail (23);

any two of the first guide rail (21), the second guide rail (22) and the third guide rail (23) are symmetrical with respect to the axis of the main body cabin (2);

and the first guide rail (21), the second guide rail (22) and the third guide rail (23) are provided with sliding grooves which are in sliding connection with the pulley structure of the pusher (4).

3. The multistage separation system for launching a drone of claim 2, wherein the parachute line comprises:

a first umbrella rope pipeline (24) arranged between the first guide rail (21) and the third guide rail (23);

a second umbrella rope pipeline (25) arranged between the second guide rail (22) and the third guide rail (23);

and the first umbrella rope pipeline (24) and the second umbrella rope pipeline (25) are symmetrically arranged on the inner wall of the main body cabin body (2).

4. The multistage separation system for launching a drone according to claim 2, characterized in that said impeller (4) comprises:

a main body mounting plate (10);

a center joint (11) fixed on the main body mounting plate (10);

at least two support carbon tubes connected to the central joint (11);

the support carbon tube is fixed on the main body mounting plate (10) through a hoop;

the pulley structure passes through the adapter with support carbon pipe fixed connection.

5. The multistage separation system for launching a drone according to claim 2 or 4,

the pulley structure includes: the pulley, the pulley limit ring and the wheel fork;

the pulley is fixed inside the fork head of the wheel fork through the pulley limiting ring;

the other end of the wheel fork is fixedly connected with the adapter.

6. The multi-stage separation system for launching a drone of claim 4,

the central joint (11) is also provided with at least one umbrella rope through hole (12).

7. The multistage separation system for launching a drone of claim 1, wherein the tail deceleration structure comprises:

a separable multi-stage cabin;

and the separation wing device is fixed on the separable multi-stage cabin body.

8. The multi-stage separation system for launching a drone of claim 7,

the separable multi-stage cabin comprises: a first cabin body (13) and a second cabin body (14) spliced with the first cabin body (13);

the separation wing arrangement comprises a first wing platform (51);

a second platform (52) which is plugged with the first platform (51);

a third platform (53) which is plugged with the second platform (52);

a first airfoil (61) plugged into the first platform (51) and the second platform (52);

a second airfoil (62) plugged with the third platform (53);

the first airfoil surface (61) is plugged with the second airfoil surface (62).

9. The multi-stage separation system for launching a drone of claim 8,

the tail part of the second cabin body (14) is also inserted with a tail cover (7).

10. The multistage separation system for launching a drone according to any one of claims 1 to 9, characterized by further comprising a head cap (1); the head cover (1) is fixedly connected with the head of the main body cabin body (2).

Technical Field

The invention relates to the technical field of separation of aerospace and aviation aircrafts, in particular to a multistage separation system for launching an unmanned aerial vehicle.

Background

At present, the aircraft industry is rapidly developing. In the traditional multi-stage separation structure of the unmanned aerial vehicle for aerospace, the internal structure of most of cabins for storing the unmanned aerial vehicle is complex, and the cabin is inconvenient to produce and process; the adopted separation scheme can generate certain impact force influence on the whole structure, and meanwhile, when the aircraft is boosted, no matter the adopted solid booster or the liquid booster is complex in structure and application principle, and the safety and the economical efficiency of the traditional booster are also important problems of the traditional booster.

Disclosure of Invention

The invention aims to provide a multistage separation system for launching an unmanned aerial vehicle. The system is simple and stable in structure, and can realize the quick and stable push-out cabin body of the unmanned aerial vehicle.

In order to solve the technical problems, the technical scheme of the invention is as follows:

a multi-stage separation system for launching a drone, comprising:

a main body cabin;

the pusher is fixed inside the main body cabin;

the tail part speed reducing structure is fixedly connected with the tail part of the main body cabin body in an inserting mode;

at least two guide rails are further arranged on the inner wall of the main body cabin body;

an umbrella rope pipeline is arranged between the at least two guide rails along the inner wall of the main body cabin body.

Optionally, the guide rail includes:

a first guide rail, a second guide rail and a third guide rail;

any two of the first guide rail, the second guide rail and the third guide rail are symmetrical with respect to the axis of the main body cabin;

and the first guide rail, the second guide rail and the third guide rail are provided with sliding grooves, and the sliding grooves are in sliding connection with the pulley structures of the pushers.

Optionally, the umbrella rope pipeline includes:

the first umbrella rope pipeline is arranged between the first guide rail and the third guide rail;

the second umbrella rope pipeline is arranged between the second guide rail and the third guide rail;

and the first umbrella rope pipeline and the second umbrella rope pipeline are symmetrically arranged on the inner wall of the main body cabin body.

Optionally, the pusher comprises:

a main body mounting plate;

a center connector fixed on the main body mounting plate;

at least two support carbon tubes connected to the central joint;

the support carbon tube is fixed on the main body mounting plate through a hoop;

the pulley structure passes through the adapter with support carbon pipe fixed connection.

Optionally, the pulley structure includes: the pulley, the pulley limit ring and the wheel fork;

the pulley is fixed inside the fork head of the wheel fork through the pulley limiting ring;

the other end of the wheel fork is fixedly connected with the adapter.

Optionally, the central joint is further provided with at least one umbrella rope through hole.

Optionally, the tail decelerating structure includes:

a separable multi-stage cabin;

and the separation wing device is fixed on the separable multi-stage cabin body.

Optionally, the detachable multi-stage cabin comprises: the first cabin body and the second cabin body are spliced with the first cabin body;

the separation wing arrangement comprises a first wing platform;

the second wing platform is spliced with the first wing platform;

a third wing platform spliced with the second wing platform;

a first airfoil inserted into the first and second airfoils;

a second airfoil surface spliced with the third airfoil;

the first airfoil surface is inserted with the second airfoil surface.

Optionally, a tail cover is further inserted into the tail of the second cabin.

Optionally, the multistage separation system for launching the unmanned aerial vehicle further comprises a hood;

the head cover is fixedly connected with the head of the main body cabin body.

The scheme of the invention at least comprises the following beneficial effects:

according to the scheme, the main body cabin body, the pusher and the tail speed reducing structure are designed in a mutually matched mode, and a multi-stage separation system is formed. The whole separation system is simple in structure, and the unmanned aerial vehicle can be stably and quickly pushed out.

Drawings

FIG. 1 is a cross-sectional view of a multi-stage separation system of the present invention;

FIG. 2 is a perspective view of the main enclosure of the multi-stage separation system of the present invention;

FIG. 3 is a rear view of the impeller of the multi-stage separation system of the present invention;

FIG. 4 is a schematic view of the pusher of the present invention attached to a main body enclosure;

FIG. 5 is a front view in cross-section of the tail reduction structure of the multi-stage separation system of the present invention;

FIG. 6 is a schematic diagram of the operation of the multi-stage separation system of the present invention.

The reference numbers illustrate: 1. a head cover; 2. a main body cabin; 3. an unmanned aerial vehicle; 4. a pusher; 5. a tail secondary speed reducing structure; 6. the tail part is provided with a first-stage speed reducing structure; 7. a tail cover; 21. a first guide rail; 22. a second guide rail; 23. a third guide rail; 24. a first umbrella rope pipeline; 25. a second umbrella rope pipeline; 26. a thickened region; 71. a first adapter; 72. a second adapter; 73. a third adapter; 81. a first clamp; 82. a second clamp; 83. a third clamp; 91. a first support carbon tube; 92. a second support carbon tube; 93. a third support carbon tube; 41. a first pulley structure; 411. a first pulley; 412. a first pulley retaining ring; 413. a first wheel fork; 42. a second pulley structure; 421. a second pulley; 422. a second pulley retainer ring; 423. a second wheel fork; 43. a third pulley structure; 431. a third pulley; 432. a third pulley limit ring; 433. a third wheel fork; 10. a main body mounting plate; 11. a center joint; 12. the umbrella rope passes through the hole; 13. a first cabin; 14. a second cabin; 15. opening the gap; 51. a first wing platform; 52. a second wing platform; 53. a third wing platform; 61. a first airfoil; 62. a second airfoil.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

As shown in fig. 1 and fig. 2, an embodiment of the present invention provides a multistage separation system for launching a drone, including: a main body cabin 2; a pusher 4 fixed inside the main body cabin 2; the tail speed reducing structure is fixedly inserted with the tail part of the main body cabin body 2; at least two guide rails are further arranged on the inner wall of the main body cabin body 2; an umbrella rope pipeline is arranged between the at least two guide rails along the inner wall of the main body cabin body 2.

In this embodiment, the main body hull 2, the pusher 4 and the tail deceleration structure constitute a multi-stage separation system. In practical application, the pusher 4 can push the unmanned aerial vehicle along the guide rail; the umbrella rope pipeline can be used for fixing and driving the pusher; the tail speed reducing structure enables the propeller 4 to stably push the unmanned aerial vehicle and provides power for the propeller 4. The multistage system overall structure that this embodiment provided is simple, can realize that unmanned aerial vehicle is steady fast and release fast.

In an alternative embodiment of the present invention, the guide rail includes: a first rail 21, a second rail 22, and a third rail 23; any two of the first guide rail 21, the second guide rail 22 and the third guide rail 23 are symmetrical with respect to the axis of the main body cabin 2; and the first guide rail 21, the second guide rail 22 and the third guide rail 23 are all provided with sliding grooves, and the sliding grooves are in sliding connection with the pulley structures of the pushers 4.

In the above embodiment, the lengths of the guide rails are all adapted to the length of the main body cabin 2, and the shapes and sizes of the guide rails are completely the same, and the descriptions of "first", "second", and "third" are only used for conveniently distinguishing the guide rails, and do not limit the sizes and positions of the guide rails.

As shown in fig. 2, the first guide rail 21 and the second guide rail 22 are distributed on the middle upper inner wall of the main body cabin 2, and the third guide rail 23 is distributed on the lower inner wall of the main body cabin 2; and the first guide rail 21 and the second guide rail 22 are symmetrical with respect to the main body nacelle 2 axis, the first guide rail 21 and the third guide rail 23 are symmetrical with respect to the main body nacelle 2 axis, and the second guide rail 22 and the third guide rail 23 are symmetrical with respect to the main body nacelle 2 axis; first guide rail 21 second guide rail 22 with the both sides of third guide rail 23 all have two threading pipes, and the cabin body of being convenient for is inside lays wire, walks the line, prevents that unmanned aerial vehicle from twining at the in-process horn of storage, transportation, input and other parts and electric wires.

As can be seen from fig. 2, the first guide rail 21, the second guide rail 22 and the third guide rail 23 are triangular prism-shaped on the internal space structure of the main body cabin 2, and this structure ensures the stability of the guide rails when the guide rails are slidably connected with the pusher 4. And simultaneously, first guide rail 21 the second guide rail 22 the pulley of the unmanned aerial vehicle impeller of spout structure adaptation that designs on the third guide rail 23, with impeller 4 carries out sliding connection, has guaranteed that the unmanned aerial vehicle impeller can be with the quick and accessible release of unmanned aerial vehicle the main part cabin body 2.

In an optional embodiment of the present invention, the parachute line comprises: a first umbrella rope pipeline 24 arranged between the first guide rail 21 and the third guide rail 23; a second parachute line 25 disposed between the second guide rail 22 and the third guide rail 23; and the first parachute line pipeline 24 and the second parachute line pipeline 25 are symmetrically arranged on the inner wall of the main body cabin body 2.

In this embodiment, the length of the parachute line is adapted to the length of the main body hull 2; similarly, the shape and size of the umbrella rope pipeline are completely the same, and the descriptions of "first" and "second" are only used for distinguishing the umbrella rope pipeline, and do not limit the size and position of the umbrella rope pipeline. The parachute line pipeline set up in between the guide rail, just first parachute line pipeline 24 with second parachute line pipeline 25 position symmetry, simultaneously first parachute line pipeline 24 with second parachute line pipeline 25 also is about 2 axis symmetry in the main part cabin body.

In an alternative embodiment of the invention, the pusher is described in an expanded view. The pusher 4 includes: a main body mounting plate 10; a center joint 11 fixed to the main body mounting plate 10; at least two support carbon tubes connected to the central joint 11; the support carbon tube is fixed on the main body mounting plate 10 through a hoop; the pulley structure passes through the adapter with support carbon pipe fixed connection.

In this embodiment, as shown in fig. 4, the main body mounting plate 10 is a cabin body adapted to be connected to a drum-shaped structure, and the main body mounting plate 10 is designed to have an irregular hexagonal structure, so as to facilitate the mounting of the main body mounting plate 10 and the main body cabin body 2. With the main part mounting panel 10 will as the backup pad, will support the carbon pipe and connect 11 fixed connection with the center of fixing on main part mounting panel 10, support on the carbon pipe is fixed in main part mounting panel 10 through the clamp, support the one end of carbon pipe pass through the adapter with pulley structure fixed connection. This arrangement ensures stability of the main structure of the pusher 4.

The support carbon tube includes: first support carbon pipe 91, second support carbon pipe 92, third support carbon pipe 93, the pulley structure includes: a first pulley structure 41, a second pulley structure 42, a third pulley structure 43; the clamp includes: a first clip 81, a second clip 82, a third clip 83; the adapter includes: a first adapter 71, a second adapter 72, and a third adapter 73.

As shown in fig. 3, specifically: the first pulley structure 41 is fixedly connected with a first supporting carbon tube 91 through a first adapter 71, and the first supporting carbon tube 91 is fixedly connected with a first side of the center adapter 11; the second pulley structure 42 is fixedly connected to a second supporting carbon tube 92 through a second adapter 72, and the second supporting carbon tube 92 is fixedly connected to a second edge of the center connector 11; the third pulley structure 43 is fixedly connected to a third supporting carbon tube 93 through a third adapter 73, and the third supporting carbon tube 93 is fixedly connected to a third side of the center joint 11.

Wherein, the first support carbon tube 91 is fixed on the main body mounting plate 10 by a first clamp 81; the second support carbon tube 92 is fixed on the main body mounting plate 10 through a second clamp 82; the third support carbon tube 93 is fixed to the main body mounting plate 10 by a third clamp 83. Optionally, the first clamp 81, the second clamp 82 and the third clamp 83 are metal clamps.

In this embodiment, the shape of the central joint 11 is designed as a hexagon; correspondingly, the support carbon tube is fixedly connected with one side of the central joint 11; the first supporting carbon tube 91, the second supporting carbon tube 92, the third supporting carbon tube 93 and the center connector 11 are fixedly connected to form a Y-shaped structure. The fixed mode of connection between each part has guaranteed the stability of whole impeller structure when the impeller promotes unmanned aerial vehicle above.

In an alternative embodiment of the present invention, a pulley structure is described. The first pulley structure 41, the second pulley structure 42, and the third pulley structure 43 each include: the pulley, the pulley limit ring and the wheel fork; the pulley is fixed inside the fork head of the wheel fork through the pulley limiting ring; the other end of the wheel fork is fixedly connected with the adapter;

as shown in fig. 3, specifically: the first pulley 411 is disposed on the first pulley retaining ring 412 in a penetrating manner, and both ends of the first pulley retaining ring 412 are fixedly connected to both ends of the U-shaped head of the first fork 413, so that the first pulley 411 is fixed inside the plug of the first fork 413, i.e. the first pulley structure 41 is formed; similarly, the second pulley 421 penetrates and is placed on the second pulley limiting ring 422, and two ends of the second pulley limiting ring 422 are fixedly connected with two ends of the U-shaped head of the second fork 423, so that the second pulley 421 is fixed inside the plug of the second fork 423, i.e., the second pulley structure 42 is formed; the third pulley 431 penetrates and is arranged on the third pulley limiting ring 432, and two ends of the third pulley limiting ring 432 are fixedly connected with two ends of the U-shaped head of the third fork 433, so that the third pulley 431 is fixed inside the plug of the third fork 433, and the third pulley structure 43 is formed. The first pulley structure 41 is fixedly connected with the first supporting carbon tube 91 through a first adapter 71; the second pulley structure 42 is fixedly connected to the second support carbon tube 92 through a second adapter 72; the third pulley structure 43 is fixedly connected to the third supporting carbon tube 93 through a third adapter 73.

In an optional embodiment of the present invention, two parachute line through holes 12 are further disposed on the central joint 11, as shown in fig. 3, in combination with the above embodiments, the pusher 4 is mainly slidably connected to the slide rail of the main body cabin 2 through a pulley structure, and when the pusher 4 works, such a connection mode can ensure that the pusher 4 can rapidly push out the unmanned aerial vehicle; two parachute ropes are arranged on the central joint 11 and pass through the holes 12 at the same time, and are symmetrically arranged relative to the central joint 11, when the pusher 4 is connected with the cabin body in a sliding mode through a pulley structure, the parachute ropes pass through the parachute ropes on the central joint 11 and pass through the holes 12 and are fixedly connected with the parachute, and when the pusher 4 pushes the unmanned aerial vehicle or does not work, the pusher 4 can be guaranteed to be stable in the cabin body; simultaneously when impeller 4 during operation also directly cooperates the parachute to promote unmanned aerial vehicle.

In an optional embodiment of the present invention, the tail decelerating structure includes: a separable multi-stage cabin; and the separation wing device is fixed on the separable multi-stage cabin body.

In this embodiment, the multi-stage cabins are fixedly inserted; the separation wing device is fixedly connected with the multi-stage cabin body in an inserting manner; when the multi-stage cabin body is separated, the separation wing device is also separated at the same time. The multi-stage cabin body and the separation wing device are connected in an inserting mode, so that the multi-stage cabin body and the separation wing device can be separated quickly.

As shown in fig. 5, the detachable multi-stage hull includes: a first cabin 13 and a second cabin 14 spliced with the first cabin 13; the separation wing arrangement comprises a first platform 51; a second platform 52 which is plugged into the first platform 51; a third wing 53 to which the second wing 52 is inserted; a first airfoil 61 inserted into the first and second platforms 51 and 52; a second wing surface 62 inserted into the third wing platform 53; the first airfoil 61 is plugged into the second airfoil 62.

In this embodiment, the first cabin 13 is inserted into the second cabin 14 in a horizontal and horizontal direction; the first wing platform 51, the second wing platform 52 and the third wing platform 53 are sequentially inserted and also horizontally inserted, and optionally, weight-reducing holes are designed on the wing platforms, so that the weight of the whole separation wing device is reduced. Simultaneously, first wing platform 51 pegs graft with the main part cabin body 2, second wing platform 52 with first cabin body 13 pegs graft, third wing platform 53 with the second cabin body 14 pegs graft, wherein, the wing platform with peg graft for the vertical ascending grafting of level between the cabin body. The first airfoil surface 61 and the second airfoil surface 62 are inserted in a horizontal transverse direction; the first airfoil 61 is plugged with the first platform 51 and the second platform 52 at the same time. Of course, the first wing platform 51 and the second wing platform 52 may also be inserted with one wing surface; the second wing surface 62 is inserted into the third wing platform 53; the insertion between the wing platform and the wing surface is horizontal and longitudinal insertion. The edge of the first airfoil 61, i.e. the edge inserted into the first platform 51, is designed as a streamline structure to reduce the resistance in the actual nacelle separation deceleration application.

In an optional embodiment of the invention, the number of the separation wing devices is 4, the separation wing devices are uniformly inserted and distributed around the separable multi-stage cabin body, and when the multi-stage cabin body is separated, the separation wing devices can be used for stabilizing the flight state of the aircraft, ensuring the flight posture to be unchanged and preventing the aircraft from rotating.

A tail cover 7 is further inserted into one end of the second cabin 14, and notch structures 15 are arranged at positions of the second wing surface 62 and the third wing platform 53 corresponding to the tail cover 7; in a specific application, the gap structure 15 facilitates the separation of the tail cap 7 from the second cabin 14.

The thickened area 26 arranged at the middle section of the outer part of the main body cabin 2 can generate certain impact force and reverse acting force when the outer part of the main body cabin 2 is hung on the machine and separated from the main body cabin 2, and the thickened area 26 can protect the main body cabin 2.

The multistage separation system for launching the unmanned aerial vehicle in the embodiment optionally further comprises a head cover 1, the upper head cover and the lower head cover of the head cover 1 are fixedly connected with the head of the main cabin body 2 through hinges, and in the multistage separation system, the upper head cover and the lower head cover of the head cover 1 are completely separated around respective hinge rotating shafts along with sequential deceleration separation among the multistage cabin bodies; optionally, the parachute automatic separation device is fixedly connected with the unmanned aerial vehicle 3 in the main cabin body 2, and the spring pin shrinkage movement is realized through the rotation movement of the steering engine in the separation device, so that the separation of the umbrella hanging component and the unmanned aerial vehicle 3 is realized

The invention discloses a multistage separation system for launching an unmanned aerial vehicle, which comprises the following specific implementation applications: first deceleration separation is carried out, and a first-stage deceleration parachute is released; the second deceleration separation is carried out, and the second-stage deceleration parachute is released; and carrying out deceleration separation for the third time, and releasing the three-stage deceleration parachute. After the brake parachute is released, the brake parachute is connected with the parachute rope to the 2 tail directions of the main body cabin body move, and meanwhile, the pusher 4 moves under the reverse acting force of the movement of the parachute rope and pushes the unmanned aerial vehicle to the 2 heads of the main body cabin body.

As shown in fig. 6: when the tail cover 7 is unlocked and separated from the second cabin 14, the first deceleration is carried out at the moment, and the first-stage deceleration parachute is released;

when the second cabin 14 is separated from the first cabin 13, the second speed reduction is carried out, and a second-stage speed reducing parachute is released; at the same time: the second airfoil surface 62 is separate from the first airfoil surface 61; the third airfoil 53 is separated from the second airfoil surface 62; the third airfoil 53 is separate from the second hull 14;

when the first cabin body 13 is separated from the main cabin body 2, the third deceleration is carried out, and a third-stage deceleration parachute is released; at the same time: the first airfoil 61 is separate from the first and second platforms 51, 52; the first platform 51 is separate from the second platform 52; the first platform 51 is separated from the main body hull 2; the second wing 52 is separate from the first nacelle 13.

In the separation wing device formed by mutually inserting the wing platforms and the wing surfaces, namely, the tail part of the position where the second wing surface 62 is inserted into the third wing platform 53 is designed with a notch 15 structure, so that the second cabin body 14 is separated from the tail cover 7; the airfoil, the wing platform and the separable multi-stage cabin body are fixed in an inserting mode, so that the airfoil, the wing platform and the separable multi-stage cabin body can be quickly separated.

While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.