CN217436059U

CN217436059U - Booster separating mechanism

Info

Publication number: CN217436059U
Application number: CN202221275207.6U
Authority: CN
Inventors: 董晓龙; 张朝阳
Original assignee: Sanjing Xinghang Beijing Technology Co ltd
Current assignee: Sanjing Xinghang Beijing Technology Co ltd
Priority date: 2022-05-24
Filing date: 2022-05-24
Publication date: 2022-09-16
Anticipated expiration: 2032-05-24

Abstract

The utility model discloses a booster separating mechanism, which comprises an unmanned aerial vehicle, a passive separating mechanism and a booster, wherein one end of the booster is fixedly connected with a front ejector rod, both sides of the unmanned aerial vehicle are fixedly connected with an installation block and a rear hanging shaft of a machine body, and a front ball socket of the machine body is arranged on the bottom side wall of each installation block; the passive separating mechanism comprises two adapter side plates, wherein an adapter front baffle is fixedly connected between the bottoms of the adapter side plates, and each of the two ends of the upper side of each adapter side plate is fixedly connected with a first fixing block and a second fixing block. The utility model discloses can be when fuselage belly space is not enough, can transversely install the boost motor, and simple installation, can autosegregation after the boost motor stop work, separation orbit is controllable and does not take place to interfere with unmanned aerial vehicle, shortens the separation time, reduces the influence to the unmanned aerial vehicle gesture, ensures that the boost engine can in time, controllably separate, and the separation back unmanned aerial vehicle surface remains intact.

Description

Booster separating mechanism

Technical Field

The utility model relates to a boost technical field especially relates to a boost separating mechanism.

Background

The installation of the booster can be divided into longitudinal installation and transverse installation from the installation position, and the corresponding separation of the booster is also divided into longitudinal separation and transverse separation. The longitudinal installation is mainly used for the aircraft insensitive to the longitudinal length, and the transverse installation is mainly used for the aircraft with strict requirements on the length. An important takeoff mode of the unmanned aerial vehicle at the present stage is zero-length takeoff, and the launching frame is simple and low in cost under the condition that the mode occupies a small area. In order to realize zero-length takeoff of the unmanned aerial vehicle, a booster is mostly arranged below the unmanned aerial vehicle, so that the unmanned aerial vehicle flies forwards and upwards.

In order to solve the problem that the booster is separated from the unmanned aerial vehicle, the following methods exist: firstly, the booster is installed on the unmanned aerial vehicle by using the explosive bolts, the unmanned aerial vehicle sends out a detonation instruction during separation, the explosive bolts are disconnected, and the booster is separated from the unmanned aerial vehicle; the booster is installed in a non-fixed mode, the head of the booster is directly abutted against an unmanned aerial vehicle through shaft-hole matching, the booster is installed on the unmanned aerial vehicle under the matching of a launcher and other equipment before working, the booster slides out along the shaft-hole matching position after working is finished, the method has higher requirement on the precision of shaft-hole matching and needs other equipment for matching, in addition, the disengagement process of the booster is uncontrollable under the influence of wind and other factors after the booster stops working, clamping stagnation and other conditions are easy to occur, and parts matched with the booster do not disengage with the booster, so that the pneumatic characteristic of the unmanned aerial vehicle is influenced; thirdly, the booster is installed on the unmanned aerial vehicle through a tiny guide rail and a shear pin on the unmanned aerial vehicle, the shear pin is cut off by the thrust of the booster when the booster is ignited, and the booster slides away from the unmanned aerial vehicle along the guide rail under the action of pneumatic resistance after the booster stops working. The above methods are sensitive to the belly space of the fuselage, and are not suitable for the situation that the belly space of the fuselage is insufficient, so that a booster separating mechanism is needed.

SUMMERY OF THE UTILITY MODEL

The utility model provides a booster separating mechanism to solve the problem of proposing among the above-mentioned background art.

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

a booster separating mechanism comprises an unmanned aerial vehicle, a passive separating mechanism and a booster, wherein one end of the booster is fixedly connected with a front ejector rod, two sides of the unmanned aerial vehicle are fixedly connected with mounting blocks and a rear hanging shaft of a machine body, and the bottom side wall of each mounting block is provided with a front ball socket of the machine body;

passive separating mechanism includes two adapter curb plates, two baffle before the fixedly connected with adapter between the adapter curb plate bottom, every the first fixed block of the equal fixedly connected with in upside both ends of adapter curb plate and second fixed block, every bulb before the upside fixedly connected with of first fixed block and the preceding ball socket looks adaptation of fuselage, every set up on the lateral wall of second fixed block with the fuselage after hang the groove behind the adapter of axle looks adaptation, baffle is connected with the adapter backplate before the adapter through thrust line adjusting device, preceding ejector pin passes through fixing device and connects in the adapter backplate.

As a further improvement scheme of the technical scheme: the thrust line adjusting device comprises a fixed ball, the fixed ball is fixedly connected to a front baffle of the adapter, a hemispherical groove matched with the fixed ball is formed in the side wall of a rear baffle of the adapter, the fixed ball is supported in the hemispherical groove, three thrust line adjusting screws are in threaded connection with the side wall of the front baffle of the adapter, each thrust line adjusting screw is fixedly connected with a rotating ball at one end, three spherical grooves matched with the rotating ball are formed in the side wall of the rear baffle of the adapter, and the rotating balls are located in the corresponding spherical grooves respectively.

As a further improvement scheme of the technical scheme: the mounting arrangement positions of the three thrust line adjusting screws are arranged in an equilateral triangle.

As a further improvement scheme of the technical scheme: the fixing device comprises jacks, the jacks are formed in the side walls of the adapter rear baffle, the front ejector rod slides in the jacks, through holes are formed in the two side walls of the jacks, the axial leads of the through holes are the same, positioning holes are formed in the side walls of the front ejector rod, and pins penetrate through the through holes.

As a further improvement scheme of the technical scheme: the pin is made of stainless steel.

As a further improvement scheme of the technical scheme: the adapter curb plate is the frame form setting of seting up the dead slot on the lateral wall.

As a further improvement scheme of the technical scheme: the front baffle of the adapter is arranged in a triangular shape.

As a further improvement scheme of the technical scheme: passive separating mechanism is located unmanned aerial vehicle's afterbody below.

Compared with the prior art, the beneficial effects of the utility model are that:

the device can be when fuselage belly space is not enough, can transversely install the boost motor, and simple installation, can autosegregation after the boost motor stop work, and separation orbit is controllable and does not take place to interfere with unmanned aerial vehicle, shortens the separation time, reduces the influence to the unmanned aerial vehicle gesture, ensures that the boosting engine can in time, controllably separate, and separation back unmanned aerial vehicle surface keeps intact.

The above description is only an outline of the technical solution of the present invention, and in order to make the technical means of the present invention more clearly understood and to be implemented in accordance with the content of the specification, the following detailed description will be given of preferred embodiments of the present invention in conjunction with the accompanying drawings. The detailed description of the present invention is given by the following examples and the accompanying drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:

fig. 1 is a schematic front structural view of a separating mechanism of a booster according to the present invention;

fig. 2 is a schematic left-side view structural diagram of a roll booster separating mechanism provided by the present invention;

fig. 3 is a schematic view of a connection structure between the unmanned aerial vehicle and the first fixed block and between the unmanned aerial vehicle and the second fixed block respectively;

fig. 4 is a schematic cross-sectional structural view between the middle booster and the front baffle of the adapter of the present invention;

fig. 5 is a schematic three-dimensional structure diagram of a second fixing block of the present invention;

fig. 6 is a schematic perspective view of a first fixing block of the present invention;

FIG. 7 is a schematic view of a portion of the enlarged structure of A in FIG. 1;

FIG. 8 is a schematic view of a portion B of FIG. 4;

fig. 9 is a partially enlarged structural diagram of C in fig. 4.

In the drawings, the components represented by the respective reference numerals are listed below:

1. an unmanned aerial vehicle; 2. an adapter side plate; 3. a front baffle of the adapter; 4. an adapter tailgate; 5. a booster; 6. a thrust line adjusting screw; 7. a front ball socket of the body; 8. a rear hanging shaft of the machine body; 9. a front ball head of the adapter; 10. a rear hanging groove of the adapter; 11. a front ejector rod; 12. a first fixed block; 13. a second fixed block; 14. mounting blocks; 15. fixing the ball; 16. a hemispherical groove; 17. a spherical groove; 18. rotating the ball; 19. a pin; 20. a through hole; 21. positioning holes; 22. and (4) inserting the jack.

Detailed Description

The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention. The invention is described in more detail in the following paragraphs by way of example with reference to the accompanying drawings. The advantages and features of the present invention will become more fully apparent from the following description and appended claims. It should be noted that the drawings are in simplified form and are not to precise scale, and are provided for convenience and clarity in order to facilitate the description of the embodiments of the present invention.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1 to 9, in the embodiment of the present invention, a booster separating mechanism includes an unmanned aerial vehicle 1, a passive separating mechanism and a booster 5, one end of the booster 5 is fixedly connected with a front ejector rod 11, both sides of the unmanned aerial vehicle 1 are fixedly connected with mounting blocks 14 and a rear fuselage hanging shaft 8, a front fuselage ball socket 7 is disposed on a bottom side wall of each mounting block 14, and the passive separating mechanism is located below a tail portion of the unmanned aerial vehicle 1;

passive separating mechanism includes two adapter curb plates 2, baffle 3 before the fixedly connected with adapter between 2 bottoms of two adapter curb plates, baffle 3 is triangle-shaped setting before the adapter, equal first fixed block 12 of fixedly connected with in upside both ends of every adapter curb plate 2 and second fixed block 13, bulb 9 before the adapter of ball socket 7 looks adaptation before the upside fixedly connected with of every first fixed block 12 and the fuselage, set up on the lateral wall of every second fixed block 13 with the fuselage behind the adapter of hanging a groove 10 of 8 looks adaptations of peg, baffle 3 is connected with adapter backplate 4 through thrust line adjusting device before the adapter, preceding ejector pin 11 passes through fixing device and connects in adapter backplate 4.

Specifically, the thrust line adjusting device comprises a fixed ball 15, the fixed ball 15 is fixedly connected to the adapter front baffle plate 3, a hemispherical groove 16 matched with the fixed ball 15 is formed in the side wall of the adapter rear baffle plate 4, the fixed ball 15 abuts against the hemispherical groove 16, three thrust line adjusting screws 6 are in threaded connection with the side wall of the adapter front baffle plate 3, one end of each thrust line adjusting screw 6 is fixedly connected with a rotating ball 18, three spherical grooves 17 matched with the rotating balls 18 are formed in the side wall of the adapter rear baffle plate 4, the three rotating balls 18 are respectively located in the corresponding spherical grooves 17, the three thrust line adjusting screws 6 are arranged in an equilateral triangle shape, the three thrust line adjusting screws 6 are screwed on the adapter front baffle plate 3, and the thrust line adjusting screws 6 can drive the adapter rear baffle plate 4 through the rotating balls 18 to use the fixed ball 15 as a fulcrum, the adapter rear baffle 4 is rotated by an angle, the booster 5 can be driven to rotate by rotating the adapter rear baffle 4, and the direction of the thrust line of the booster can be adjusted by adjusting the three thrust line adjusting screws 6.

Specifically, fixing device includes jack 22, jack 22 is seted up on the lateral wall of adapter backplate 4, preceding ejector pin 11 slides in jack 22, through-hole 20 has been seted up on the both sides wall of jack 22, the axial lead of two through-holes 20 is the same, locating hole 21 has been seted up on the lateral wall of preceding ejector pin 11, it has pin 19 to run through between two through-holes 20, pin 19 adopts the stainless steel material, insert in jack 22 of adapter backplate 4 through preceding ejector pin 11 of boost motor 5, when locating hole 21 on preceding ejector pin 11 and two through-holes 20 communicate, use pin 19 to insert locating hole 21 and two through-holes 20, fix preceding ejector pin 11 on adapter backplate 4, boost motor 5 and the passive separating centrifuge of boost motor constitute a whole this moment.

Specifically, adapter curb plate 2 is the frame form setting of seting up the dead slot on the lateral wall, the whole weight of greatly reduced adapter curb plate 2.

The utility model discloses a theory of operation is:

when the installation is carried out, the front ejector rod 11 of the booster 5 is firstly inserted into the jack 22 of the adapter backplate 4 until the positioning hole 21 on the front ejector rod 11 is communicated with the two through holes 20, the pin 19 is used for being inserted into the positioning hole 21 and the two through holes 20, the front ejector rod 11 is fixed on the adapter backplate 4, and at the moment, the booster 5 and the booster passive separator form a whole; then, the rear adapter hanging groove 10 on the second fixing block 13 is hung on the rear hanging shaft 8 of the machine body, the side plate 2 of the adapter is rotated to enable the front adapter ball head 9 on the first fixing block 12 to be in contact with the front ball socket 7 of the machine body, at the moment, under the action of the gravity of the passive separation mechanism and the booster 5, the front adapter ball head 9 is attached to the front ball socket 7 of the machine body, and the direction of a thrust line of the booster can be adjusted by adjusting the three thrust line adjusting screws 6;

after the booster 5 is ignited, the thrust of the booster 5 is transferred by means of a front ball head 9 of the adapter, a front ball socket 7 of the machine body, a rear hanging groove 10 of the adapter and a rear hanging shaft 8 of the machine body;

after the thrust of the booster 5 is terminated, under the action of self gravity and air power, the booster 5 and the passive separation mechanism of the booster rotate downwards around the rear hanging shaft 8 of the unmanned aerial vehicle body together, and are separated from the unmanned aerial vehicle 1 after rotating for about 30 degrees, and the separation track in the process is controllable and does not interfere with the unmanned aerial vehicle 1.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way; the present invention can be smoothly implemented by those skilled in the art according to the drawings and the above description; however, those skilled in the art should understand that the equivalent embodiments of the present invention are equivalent embodiments of the present invention, and that the changes, modifications and evolutions made by the above-disclosed technical contents are not departed from the technical scope of the present invention; meanwhile, any changes, modifications, evolutions, etc. of the above embodiments, which are equivalent to the actual techniques of the present invention, still belong to the protection scope of the technical solution of the present invention.

Claims

1. A booster separating mechanism comprises an unmanned aerial vehicle (1), a passive separating mechanism and a booster (5), and is characterized in that one end of the booster (5) is fixedly connected with a front ejector rod (11), both sides of the unmanned aerial vehicle (1) are fixedly connected with mounting blocks (14) and a rear fuselage hanging shaft (8), and the bottom side wall of each mounting block (14) is provided with a front fuselage ball socket (7);

passive separating mechanism includes two adapter curb plates (2), two baffle (3) before the fixedly connected with adapter between adapter curb plate (2) bottom, every ball head (9) before the upside fixedly connected with of first fixed block (2) and the equal fixedly connected with in upside both ends of adapter curb plate (2) and second fixed block (13), every before the upside fixedly connected with of first fixed block (12) and the adapter of the preceding ball socket (7) looks adaptation of fuselage, every set up on the lateral wall of second fixed block (13) with the fuselage behind hang groove (10) of hanging axle (8) looks adaptation, baffle (3) are connected with adapter backplate (4) through thrust line adjusting device before the adapter, preceding ejector pin (11) are connected in adapter backplate (4) through fixing device.

2. The booster separating mechanism according to claim 1, wherein the thrust line adjusting device comprises a fixed ball (15), the fixed ball (15) is fixedly connected to the front baffle (3) of the adapter, a hemispherical groove (16) matched with the fixed ball (15) is formed in the side wall of the rear baffle (4) of the adapter, the fixed ball (15) abuts against the hemispherical groove (16), three thrust line adjusting screws (6) are connected to the side wall of the front baffle (3) of the adapter in a threaded manner, a rotating ball (18) is fixedly connected to one end of each thrust line adjusting screw (6), three spherical grooves (17) matched with the rotating balls (18) are formed in the side wall of the rear baffle (4) of the adapter, and the three rotating balls (18) are respectively located in the corresponding spherical grooves (17).

3. The booster release mechanism of claim 2, wherein the three thrust line adjusting screws (6) are arranged in an equilateral triangle.

4. The booster separating mechanism according to claim 1, wherein the fixing device comprises a jack (22), the jack (22) is arranged on a side wall of the adapter rear baffle (4), the front ejector rod (11) slides in the jack (22), through holes (20) are formed in two side walls of the jack (22), axial leads of the two through holes (20) are identical, a positioning hole (21) is formed in a side wall of the front ejector rod (11), and a pin (19) penetrates through the two through holes (20).

5. A booster release mechanism according to claim 4, characterised in that the pin (19) is of stainless steel.

6. The booster release mechanism according to claim 1, wherein the adapter side plate (2) is formed in a frame shape with a hollow groove formed in a side wall thereof.

7. A booster release mechanism according to claim 1, characterised in that the adapter front baffle (3) is triangularly shaped.

8. A booster release mechanism according to claim 1, characterised in that the passive release mechanism is located below the tail of the drone (1).