CN221163417U

CN221163417U - Unmanned aerial vehicle launching cradle

Info

Publication number: CN221163417U
Application number: CN202322654289.6U
Authority: CN
Inventors: 李威; 刘铁军; 岳向泉; 牛圣杰
Original assignee: Tianjin Hangyu Intelligent Equipment Co ltd
Current assignee: Tianjin Hangyu Intelligent Equipment Co ltd
Priority date: 2023-09-28
Filing date: 2023-09-28
Publication date: 2024-06-18
Anticipated expiration: 2033-09-28

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle launching frame, which comprises a supporting seat which is obliquely arranged, wherein a fixing frame is fixed on the upper side of the supporting seat and positioned in the middle of the supporting seat, a movable frame is rotatably arranged on the supporting seat and positioned on one side of the fixing frame, and the movable frame can rotate towards one side close to or far from the fixing frame; the supporting seat is provided with a limiting frame, and the limiting frame and the movable frame are fixed through a disposable shearing pin; the unmanned aerial vehicle is abutted to the upper sides of the fixed frame and the movable frame; the supporting seat is provided with a booster which is positioned on one side of the fixed frame far away from the movable frame, and an output shaft of the booster is abutted against the unmanned aerial vehicle; the limiting frame is located at one higher end of the supporting seat, and the booster is located at one lower end of the supporting seat. The structure can assist the unmanned aerial vehicle with relatively large volume and relatively large weight to take off.

Description

Unmanned aerial vehicle launching cradle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle launching cradle.

Background

The unmanned plane is called as unmanned plane for short, and is a unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other devices. Personnel on the ground, ships or on a mother machine remote control station track, position, remote control, telemetere and digital transmission through radar and other equipment. Can take off like a common plane under radio remote control or launch and lift off by using a boosting rocket, and can also be brought into the air by a master machine to put in flight. When recovered, the aircraft can automatically land in the same way as the landing process of a common aircraft, and can also be recovered by a parachute or a barrier net for remote control. Can be repeatedly used for a plurality of times. The method is widely used for air reconnaissance, monitoring, communication, anti-diving, electronic interference and the like.

Unmanned aerial vehicles among the prior art include unmanned aerial vehicle and the unmanned aerial vehicle of hand throwing type that automatically droop. The hand throwing type unmanned aerial vehicle generally needs to manually control the unmanned aerial vehicle to throw out for taking off. The hand throwing mode is generally suitable for unmanned aerial vehicles with smaller weight, and when the unmanned aerial vehicle has relatively large volume and weight, the mode of controlling the unmanned aerial vehicle to take off through hand throwing is not suitable. Therefore, there is an urgent need for an unmanned aerial vehicle launching cradle capable of controlling an unmanned aerial vehicle to take off.

Disclosure of utility model

(One) solving the technical problems

Aiming at the defects of the prior art, the utility model provides the unmanned aerial vehicle launching frame, which can assist the unmanned aerial vehicle with relatively large volume and relatively large weight to take off.

(II) technical scheme

In order to achieve the above purpose, the embodiment of the application provides an unmanned aerial vehicle launching frame, which comprises a supporting seat which is obliquely arranged, wherein a fixing frame is fixed on the upper side of the supporting seat and positioned in the middle of the supporting seat, a movable frame is rotatably arranged on the supporting seat and positioned on one side of the fixing frame, and the movable frame can rotate towards one side close to or far from the fixing frame; the supporting seat is provided with a limiting frame, and the limiting frame and the movable frame are fixed through a disposable shearing pin; the unmanned aerial vehicle is abutted to the upper sides of the fixed frame and the movable frame; the supporting seat is provided with a booster which is positioned on one side of the fixed frame far away from the movable frame, and an output shaft of the booster is abutted against the unmanned aerial vehicle; the limiting frame is located at one higher end of the supporting seat, and the booster is located at one lower end of the supporting seat.

Preferably, the mount is in the both sides of supporting seat width direction are provided with one respectively, including the support arm of vertical setting, two one side that the support arm is close to each other and be close to movable frame, booster's both sides are fixed with the support floor respectively, the one end that the supporting seat was kept away from to the support arm is provided with spacing support, spacing support is being close to one side of movable frame has seted up the spacing groove, spacing groove and the stopper joint on the unmanned aerial vehicle body, the stopper can break away from by being close to movable frame one side the spacing groove.

Preferably, the movable frame comprises three mounting seats fixed at the end parts of the supporting seats, a supporting shaft is rotatably arranged between the three mounting seats, two ends of the supporting shaft are fixedly provided with swinging arms, first torsion springs are respectively sleeved on the supporting shaft and positioned between two adjacent mounting seats, one ends of the first torsion springs are connected with the mounting seats, the other ends of the first torsion springs are connected with the swinging arms, and the swinging arms are controlled to swing towards one side far away from the fixed frame; the two swing arms are provided with clamping grooves at one ends far away from the mounting seat, the clamping grooves are embedded with clamping shafts at two sides of the unmanned aerial vehicle body, and the clamping shafts can be separated from the clamping grooves when the booster pushes the unmanned aerial vehicle.

Preferably, the limiting frame is L-shaped, one end of the limiting frame is fixedly mounted on the supporting seat, a first limiting hole is formed in the other end of the limiting frame, a second limiting hole is formed in the swing arm, the disposable shearing pin penetrates through the first limiting hole and the second limiting hole, and the length direction of the disposable shearing pin is parallel to the rotation axis direction of the swing arm.

Preferably, a bracket for supporting the booster is arranged on the supporting seat, the bracket comprises a first mounting plate and a second mounting plate which are fixed on the supporting seat at intervals, a connecting shaft is arranged between the first mounting plate and the second mounting plate in a rotating way, and a positioning block is fixed on the connecting shaft; the connecting shaft is provided with second torsion springs positioned on two sides of the positioning block respectively, one end of each second torsion spring is connected with the first mounting plate or the second mounting plate, and the other end of each second torsion spring is connected with the positioning block; an adjusting plate is fixed on one side, close to the supporting seat, of the positioning block, an adjusting assembly is arranged on the supporting seat, the adjusting assembly is located on one side, close to the fixing frame, of the adjusting plate, the adjusting assembly abuts against the adjusting plate, and the position of the adjusting plate is adjusted; the adjusting plate is kept in elastic contact with the adjusting component under the action of a second torsion spring; the locating piece is kept away from the one end of regulating plate is fixed with the spliced pole, the spliced pole upper end is fixed with the U-shaped frame, the inboard rotation of U-shaped frame is provided with the C shaped plate, the C shaped plate butt the booster.

Preferably, the adjusting component comprises a first adjusting block and a second adjusting block which are fixed on the supporting seat and are arranged at intervals along the length direction, an adjusting screw is connected to the first adjusting block and the second adjusting block in a threaded mode, one end of the adjusting screw is abutted to the adjusting plate, and an operation control part is arranged at the other end of the adjusting screw.

Preferably, an abutment block is arranged on the output shaft of the booster, and the abutment block is in limiting abutment with an abutment groove on the unmanned aerial vehicle.

Preferably, the booster comprises a combustion cylinder, a combustion chamber is formed in the combustion cylinder, a medicine blocking plate is arranged on one side, close to the output shaft, of the combustion chamber, and one end, far away from the combustion chamber, of the medicine blocking plate is connected with the output shaft; the one end that the output shaft was kept away from to the combustion bowl is provided with the spray tube, the spray tube diameter is less than the diameter of combustion bowl, C shaped plate joint in the spray tube outside.

(III) beneficial effects

The utility model provides an unmanned aerial vehicle launching frame, before launching, a movable frame is limited by a disposable shear pin, a fixed frame and the movable frame support an unmanned aerial vehicle, when the unmanned aerial vehicle takes off, an initial power is provided for the unmanned aerial vehicle through a booster, the unmanned aerial vehicle moves obliquely upwards, the unmanned aerial vehicle is separated from the fixed frame in the moving process, the movable frame rotates relative to the limiting frame, the disposable shear pin is broken, and then the unmanned aerial vehicle continuously flies forwards. The structure can assist the unmanned aerial vehicle with relatively large volume and large weight to take off, simplify the operation steps of taking off the unmanned aerial vehicle, and improve the reliability of transmission.

Drawings

Fig. 1 is a schematic structural view of an unmanned aerial vehicle launching cradle according to the present utility model;

FIG. 2 is an enlarged view of the A structure of FIG. 1;

FIG. 3 is a schematic view of another angle of a unmanned aerial vehicle launcher according to the present utility model;

FIG. 4 is an enlarged view of the B structure of FIG. 3;

Fig. 5 is a schematic view showing a structure of a protruding mobile frame in an unmanned aerial vehicle launching frame according to the present utility model.

The reference numerals in the drawings:

100. A support base; 200. a fixing frame; 210. a support arm; 220. supporting rib plates; 230. a limit support; 231. a limit groove; 300. a movable frame; 310. a mounting base; 320. a support shaft; 330. a swing arm; 331. a clamping groove; 340. a first torsion spring; 400. a limiting frame; 410. a disposable shear pin; 500. a booster; 510. an output shaft; 511. an abutment block; 520. a combustion cylinder; 530. a spray pipe; 600. a bracket; 610. a first mounting plate; 620. a second mounting plate; 630. a connecting shaft; 640. a positioning block; 650. a second torsion spring; 660. an adjusting plate; 670. an adjustment assembly; 671. a first adjustment block; 672. a second adjustment block; 673. adjusting a screw; 680. a connecting column; 690. a U-shaped frame; 691. a C-shaped plate.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Example 1

The utility model provides an unmanned aerial vehicle launching frame, referring to fig. 1-5, comprising a supporting seat 100 which is obliquely arranged, wherein a fixed frame 200 is fixed on the upper side of the supporting seat 100 and positioned in the middle, a movable frame 300 is rotatably arranged on the supporting seat 100 and positioned on one side of the fixed frame 200, and the movable frame 300 can rotate towards one side close to or far from the fixed frame 200; the supporting seat 100 is provided with a limiting frame 400, and the limiting frame 400 and the movable frame 300 are fixed through a disposable shearing pin 410; the unmanned aerial vehicle is abutted to the upper sides of the fixed frame 200 and the movable frame 300; a booster 500 is arranged on the supporting seat 100 and positioned on one side of the fixed frame 200 far away from the movable frame 300, and an output shaft 510 of the booster 500 is abutted against the unmanned aerial vehicle; the limiting frame 400 is located at a higher end of the supporting seat 100, and the booster 500 is located at a lower end of the supporting seat 100. When it is required to control the take-off of the unmanned aerial vehicle, the unmanned aerial vehicle is placed on the fixed frame 200 and the movable frame 300, and since the movable frame 300 is fixed by the disposable shear pins 410, the movable frame 300 is maintained in a fixed state at this time. When booster 500 works, power is provided to the unmanned aerial vehicle for unmanned aerial vehicle moves forward, and at this time, movable frame 300 rotates forward, so that disposable shear pin 410 breaks off, movable frame 300 continues to rotate and breaks away from the unmanned aerial vehicle, and the unmanned aerial vehicle takes off.

It should be noted that, the shear pin is a pin commonly used in the prior art, in the present application, the shear pin may limit the movable frame 300 before the booster 500 is started, so that the movable frame 300 is fixed, and when the booster 500 pushes the unmanned aerial vehicle, the movable frame 300 swings, and the relative rotation between the movable frame 300 and the limit frame 400 causes the shear pin to break.

Specifically, the fixing frame 200 is respectively provided with one support arm 210 at two sides of the support base 100 in the width direction, and the support rib plates 220 are respectively fixed at one side of the two support arms 210, which are close to each other, and at two sides of the movable frame 300 and the booster 500.

The end of the support arm 210, which is far away from the support seat 100, is provided with a limit bracket 230, a limit groove 231 is formed in one side of the limit bracket 230, which is close to the movable frame 300, the limit groove 231 is clamped with a limit block on the unmanned aerial vehicle, and the limit block can be separated from the limit groove 231 from one side, which is close to the movable frame 300. When booster 500 provides power to the unmanned aerial vehicle for unmanned aerial vehicle moves forward, at this point, the stopper breaks away from spacing support 230. The support arm 210 supports the unmanned aerial vehicle before the booster 500 is started, and when the booster 500 is started, the output shaft 510 of the booster 500 provides power to the unmanned aerial vehicle, so that the unmanned aerial vehicle obtains the initial power for forward flight.

The movable frame 300 comprises three mounting seats 310 fixed at the end part of the supporting seat 100, a supporting shaft 320 is rotatably arranged between the three mounting seats 310, swinging arms 330 are fixed at two ends of the supporting shaft 320, first torsion springs 340 are respectively sleeved on the supporting shaft 320 and positioned between two adjacent mounting seats 310, one end of each first torsion spring 340 is connected with one mounting seat 310, the other end of each first torsion spring is connected with the swinging arm 330, and the swinging arm 330 is controlled to swing towards one side far away from the fixed frame 200.

The two swing arms 330 are provided with clamping grooves 331 at one end far away from the mounting seat 310, the clamping grooves 331 are embedded with clamping shafts at two sides on the unmanned aerial vehicle body, and the clamping shafts can be separated from the clamping grooves 331 when the booster 500 pushes the unmanned aerial vehicle. The position of draw-in groove 331 is located the top of swing arm 330, and when booster 500 promoted unmanned aerial vehicle, the clamping axle of unmanned aerial vehicle both sides rotated with draw-in groove 331 and is connected for swing arm 330 receives external force because the spacing effect of draw-in groove 331, and swing arm 330 is the forward swing of spacing 400 relatively, and at this moment, the shear pin fracture, swing arm 330 continue forward swing until with unmanned aerial vehicle separation.

The limiting frame 400 is L-shaped, one end of the limiting frame is fixedly mounted on the supporting seat 100, the other end of the limiting frame is provided with a first limiting hole, the swing arm 330 is provided with a second limiting hole, the disposable shearing pin 410 penetrates through the first limiting hole and the second limiting hole, and the length direction of the disposable shearing pin 410 is parallel to the rotation axis direction of the swing arm 330.

The support 100 is provided with a bracket 600 for supporting the booster 500, the bracket 600 includes a first mounting plate 610 and a second mounting plate 620 fixed on the support 100 at intervals, a connection shaft 630 is rotatably provided between the first mounting plate 610 and the second mounting plate 620, and a positioning block 640 is fixed on the connection shaft 630.

The connecting shaft 630 is provided with second torsion springs 650 respectively positioned on two sides of the positioning block 640, one end of each second torsion spring 650 is connected with the first mounting plate 610 or the second mounting plate 620, and the other end is connected with the positioning block 640.

An adjusting plate 660 is fixed on one side of the positioning block 640, which is close to the supporting seat 100, an adjusting assembly 670 is arranged on the supporting seat 100, the adjusting assembly 670 is positioned on one side of the adjusting plate 660, which is close to the fixing frame 200, and the adjusting assembly 670 abuts against the adjusting plate 660 and adjusts the position of the adjusting plate 660; the adjustment plate 660 is held in resilient contact with the adjustment assembly 670 by the second torsion spring 650.

A connecting column 680 is fixed at one end of the positioning block 640, which is far away from the adjusting plate 660, a U-shaped frame 690 is fixed at the upper end of the connecting column 680, a C-shaped plate 691 is rotatably arranged at the inner side of the U-shaped frame 690, and the C-shaped plate 691 abuts against the booster 500.

The adjusting assembly 670 includes a first adjusting block 671 and a second adjusting block 672 fixed on the supporting seat 100 and disposed at intervals along a long direction, an adjusting screw 673 is screwed on the first adjusting block 671 and the second adjusting block 672, one end of the adjusting screw 673 abuts against the adjusting plate 660, and the other end is provided with a control part.

An abutment block 511 is provided on the output shaft 510 of the booster 500, and the abutment block 511 is in limited abutment with an abutment groove on the unmanned aerial vehicle. The abutment block 511 can provide power to the unmanned aerial vehicle through the abutment slot, and when the unmanned aerial vehicle takes off, the abutment block 511 can be separated from the abutment slot.

Booster 500 includes a combustion can 520, with a combustion chamber formed within combustion can 520, and with corresponding combustion chamber materials filled therein. The combustion chamber is provided with the drug baffle near one side of output shaft 510, and the one end that keeps away from the combustion chamber of drug baffle is connected output shaft 510. The combustion cylinder 520 is provided with a spray pipe 530 at one end far away from the output shaft 510, the diameter of the spray pipe 530 is smaller than that of the combustion cylinder 520, and the C-shaped plate 691 is clamped on the outer side of the spray pipe 530.

The combustion chamber in the combustion cylinder 520 is an important component of the booster 500, and is required to withstand the high-temperature and high-pressure gas flushing action, and to exist as a negative mass after the end of the operation, so that the mass is required to be as small as possible.

The high-strength aluminum alloy has higher strength, and the aluminum alloy material is selected appropriately from the viewpoint of reducing the weight of the combustion chamber alone, but has large heat conductivity and poor ablation and flushing resistance. The high-quality carbon steel has wide material source, low cost, high elongation and low specific strength. The alloy steel has high specific strength and good ablation and scouring resistance, and in summary, 30CrMnSiA is selected as the combustion chamber housing material in order to ensure reliable operation of the booster 500.

For the free-loading booster 500, the combustor heat protection design is extremely important. After the combustion chamber is heated, the wall temperature of the metal shell of the combustion chamber rises, the allowable stress of the material of the metal shell is reduced, and if the metal shell is not protected by the heat insulation layer, the heated metal shell of the combustion chamber is difficult to bear the high pressure in the chamber to tear or even explode. Taking into account the lightweight design of the booster rocket and the external ventilation parameters of the internal trajectory, a military GT401 thermal barrier coating is employed as a thermal barrier coating for the combustor casing.

The nozzle 530 is a key part of the booster 500, and when the booster 500 is operated, high-temperature and high-pressure gas in the combustion chamber flows through the nozzle 530 and is converted into high-speed flowing kinetic energy by heat energy and pressure potential energy, so that thrust is generated. The design of the structure and parameters of the jet pipe 530 directly affects the efficiency, the magnitude of the thrust eccentricity and the safety of the operation of the booster 500. Considering the propellant gas temperature and the operation time of the booster 500, the throat lining material of the spray pipe 530 is high-purity graphite with good ablation resistance.

In the description of the present utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," "front," "rear," and the like indicate an azimuth or a positional relationship based on that shown in the drawings, and are merely for convenience of description and to simplify the description, but do not indicate or imply that the apparatus or elements to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present utility model, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediary, or communicating between the two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art. Embodiments of the utility model and features of the embodiments may be combined with each other without conflict.

The foregoing examples merely illustrate embodiments of the utility model and are described in more detail and are not to be construed as limiting the scope of the utility model. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the utility model, which are all within the scope of the utility model. Accordingly, the scope of protection of the present utility model is to be determined by the appended claims.

Claims

1. An unmanned aerial vehicle launching cradle, its characterized in that: comprises a supporting seat (100) which is obliquely arranged, a fixing frame (200) is fixed at the upper side of the supporting seat (100) and at the middle position,

A movable frame (300) is rotatably arranged on the supporting seat (100) and positioned on one side of the fixed frame (200), and the movable frame (300) can rotate towards one side close to or far from the fixed frame (200); a limiting frame (400) is arranged on the supporting seat (100), and the limiting frame (400) and the movable frame (300) are fixed through a disposable shearing pin (410); the unmanned aerial vehicle is abutted to the upper sides of the fixed frame (200) and the movable frame (300);

A booster (500) is arranged on the supporting seat (100) and positioned on one side of the fixed frame (200) far away from the movable frame (300), and an output shaft (510) of the booster (500) is abutted against the unmanned plane; the limiting frame (400) is located at the higher end of the supporting seat (100), and the booster (500) is located at the lower end of the supporting seat (100).

2. The unmanned aerial vehicle launcher according to claim 1, wherein: the fixed frame (200) is respectively provided with one on both sides of the width direction of the supporting seat (100) and comprises supporting arms (210) which are vertically arranged, one side of the two supporting arms (210) which are close to each other, and two sides of the movable frame (300) which are close to the movable frame and the booster (500) are respectively fixed with supporting rib plates (220),

One end of the supporting arm (210) far away from the supporting seat (100) is provided with a limiting support (230), a limiting groove (231) is formed in one side, close to the movable frame (300), of the limiting support (230), the limiting groove (231) is clamped with a limiting block on the unmanned aerial vehicle, and the limiting block can be separated from the limiting groove (231) from one side, close to the movable frame (300).

3. The unmanned aerial vehicle launcher according to claim 1, wherein: the movable frame (300) comprises three mounting seats (310) fixed at the end parts of the supporting seats (100), a supporting shaft (320) is rotatably arranged between the three mounting seats (310), two ends of the supporting shaft (320) are fixedly provided with swinging arms (330), first torsion springs (340) are respectively sleeved on the supporting shaft (320) and positioned between two adjacent mounting seats (310), one ends of the first torsion springs (340) are connected with the mounting seats (310), the other ends of the first torsion springs are connected with the swinging arms (330), and the swinging arms (330) are controlled to swing towards one side far away from the fixed frame (200);

The two swing arms (330) are provided with clamping grooves (331) at one ends far away from the mounting seat (310), the clamping grooves (331) are embedded with clamping shafts at two sides of the unmanned aerial vehicle body, and when the booster (500) pushes the unmanned aerial vehicle, the clamping shafts can be separated from the clamping grooves (331).

4. The unmanned aerial vehicle launcher according to claim 1, wherein: the limiting frame (400) is L-shaped, one end of the limiting frame is fixedly mounted on the supporting seat (100), a first limiting hole is formed in the other end of the limiting frame, a second limiting hole is formed in the swinging arm (330), the disposable shearing pin (410) penetrates through the first limiting hole and the second limiting hole, and the length direction of the disposable shearing pin (410) is parallel to the rotation axis direction of the swinging arm (330).

5. The unmanned aerial vehicle launcher according to claim 1, wherein: the support seat (100) is provided with a bracket (600) for supporting the booster (500), the bracket (600) comprises a first mounting plate (610) and a second mounting plate (620) which are fixed on the support seat (100) at intervals, a connecting shaft (630) is rotatably arranged between the first mounting plate (610) and the second mounting plate (620), and a positioning block (640) is fixed on the connecting shaft (630);

Second torsion springs (650) are respectively arranged on the connecting shaft (630) and positioned on two sides of the positioning block (640), one end of each second torsion spring (650) is connected with the first mounting plate (610) or the second mounting plate (620), and the other end of each second torsion spring is connected with the positioning block (640);

An adjusting plate (660) is fixed on one side, close to the supporting seat (100), of the positioning block (640), an adjusting assembly (670) is arranged on the supporting seat (100), the adjusting assembly (670) is located on one side, close to the fixing frame (200), of the adjusting plate (660), the adjusting assembly (670) abuts against the adjusting plate (660), and the position of the adjusting plate (660) is adjusted; the adjusting plate (660) is kept in elastic contact with the adjusting assembly (670) under the action of a second torsion spring (650);

One end of the positioning block (640) far away from the adjusting plate (660) is fixedly provided with a connecting column (680), the upper end of the connecting column (680) is fixedly provided with a U-shaped frame (690), the inner side of the U-shaped frame (690) is rotatably provided with a C-shaped plate (691), and the C-shaped plate (691) is abutted to the booster (500).

6. The unmanned aerial vehicle launcher according to claim 1, wherein: the adjusting assembly (670) comprises a first adjusting block (671) and a second adjusting block (672) which are fixed on the supporting seat (100) and are arranged at intervals along the length direction, an adjusting screw (673) is connected to the first adjusting block (671) and the second adjusting block (672) in a threaded mode, one end of the adjusting screw (673) abuts against the adjusting plate (660), and an operation control part is arranged at the other end of the adjusting screw.

7. The unmanned aerial vehicle launcher according to claim 1, wherein: an abutting block (511) is arranged on an output shaft (510) of the booster (500), and the abutting block (511) is in limiting abutting connection with an abutting groove on the unmanned aerial vehicle body.

8. The unmanned aerial vehicle launcher according to claim 1, wherein: the booster (500) comprises a combustion cylinder (520), a combustion chamber is formed in the combustion cylinder (520), a drug baffle plate is arranged on one side, close to the output shaft (510), of the combustion chamber, and one end, far away from the combustion chamber, of the drug baffle plate is connected with the output shaft (510);

The one end that output shaft (510) was kept away from to combustion tube (520) is provided with spray tube (530), spray tube (530) diameter is less than the diameter of combustion tube (520), C shaped plate (691) joint in spray tube (530) outside.