CN210268363U - Individual air defense missile launching support - Google Patents

Abstract

The utility model provides an individual soldier air defense missile launching cradle, it includes: base (2), seat (7), connecting pipe subassembly and missile launching canister fixture (6), wherein seat (7) set up in on base (2), and can carry out the stepless continuously adjustable's of height lift adjustment, missile launching canister fixture (6) can be used for erectting the missile launching canister, the connecting pipe subassembly is used for connecting base (2) with missile launching canister fixture (6). Through the utility model discloses can let the user carry on the launch canister as required with the regulation of user's body phase relative height and hold on the shoulder, improve the travelling comfort, be fit for the shooter of different heights, improve the commonality.

Description

Individual air defense missile launching support

Technical Field

The utility model belongs to the technical field of machinery, concretely relates to individual soldier's air defense missile launching cradle.

Background

The shoulder-carried missile is an effective low-altitude air defense weapon, and is mainly used for dealing with low-altitude flying targets, such as low-altitude flying helicopters, diving attacking machines and the like; it is an important air defense weapon for field troops. With the continuous change of the situation of local wars and anti-terrorism wars all over the world, the low-altitude air defense task is increasingly difficult, and the means of enemy potential destruction are more and more diversified, including the destruction of aircrafts such as armed helicopters, unmanned planes, fighters, dynamic delta wings, dynamic umbrellas and the like flying through low-altitude and ultra-low-altitude targets, and the use of low-altitude air defense shoulder-launched missiles is increasingly frequent.

The combat performance and the launching stability of the shoulder-mounted missile are inseparable from the body comfort level of the shooter; the existing shoulder-mounted missile launching support plays a role in enhancing launching stability, absorbs a certain recoil force, and still has many problems, such as large volume (large mechanism occupation space), heavy weight (non-portable), fixed and non-liftable seat or discontinuous step regulation of lifting (suitable for narrow height range of a shooter), poor compatibility (single type of a missile launching tube), complex erection and retraction (long time consumption and low efficiency) and the like.

In the existing individual air defense missile launching support, the height of a seat is positioned by inserting different hole positions through a bolt, and the adjustment mode is graded and discontinuous, so that the discomfort of soldiers with certain heights is easily caused. The existing missile launcher clamp can only clamp one type of missile launcher, and the operation cannot be finished if another type of missile launcher needs to be replaced during the operation.

Because the height of the seat of the individual air defense missile launching support in the prior art is positioned by inserting different hole sites through the bolts, the adjustment mode is graded and discontinuous, the adjustment is inconvenient, and the discomfort of soldiers with certain heights can be easily caused; present missile launching tube fixture can only adorn a missile launching tube of card, if when doing the war surely need change another kind of missile launching tube, will unable completion operation, technical problem such as the commonality is relatively poor, consequently the utility model discloses research and design has produced an individual soldier's air defense missile launching support.

SUMMERY OF THE UTILITY MODEL

Therefore, the to-be-solved technical problem of the utility model lies in overcoming the mode of adjustment of individual soldier's air defense missile launching cradle's seat height among the prior art and be the discrete defect of having a grade, lead to the comfort relatively poor to an individual soldier air defense missile launching cradle is provided.

The utility model provides an individual soldier air defense missile launching cradle, it includes:

the height-adjustable missile launcher comprises a base, a seat, a connecting pipe assembly and a missile launcher fixture, wherein the seat is arranged on the base and can be used for height stepless continuously adjustable lifting adjustment, the missile launcher fixture can be used for erecting a missile launcher, and the connecting pipe assembly is used for connecting the base with the missile launcher fixture.

Preferably, the first and second electrodes are formed of a metal,

the seat comprises a lifting screw rod, a guide rail pipe and a seat surface, wherein the lifting screw rod is fixedly connected with the seat surface, the guide rail pipe is fixedly arranged on the base, and the lifting screw rod can be sleeved in the guide rail pipe and can move up and down along the vertical direction.

Preferably, the first and second electrodes are formed of a metal,

the guide rail pipe is provided with a clamping groove, the adjusting nut can be arranged in the clamping groove and can accommodate the lifting screw rod to penetrate through the adjusting nut, and the lifting screw rod is adjusted by the adjusting nut and is in threaded connection with the adjusting nut so that the lifting screw rod moves up and down.

Preferably, the first and second electrodes are formed of a metal,

the inner wall of the guide rail pipe is further provided with a tenon in an extending manner along the axis direction of the guide rail pipe, the outer wall surface of the lifting screw is further provided with a groove in an extending manner along the axis direction of the guide rail pipe, and the tenon can be inserted into the groove along the axis direction to stop rotation of the lifting screw; and/or at least three handles distributed along the circumferential direction are arranged on the outer wall of the adjusting nut; and/or the seat further comprises a seat back, and the seat back is fixedly arranged on the seat surface.

Preferably, the first and second electrodes are formed of a metal,

the missile launcher clamping device comprises a first clamping device, a second clamping device, a supporting rib and an adjustable buckle, one end of the second clamping device is connected with the supporting rib, the other end of the second clamping device is connected with one end of the first clamping device, and the other end of the first clamping device can be clamped on the supporting rib through the adjustable buckle.

Preferably, the first and second electrodes are formed of a metal,

the adjustable buckle is arranged on the first fixture, a clamping position is arranged on the supporting rib, and the adjustable buckle comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle and the clamping position through threaded connection of the screw rod and the screw hole;

or the adjustable buckle is arranged on the supporting rib and provided with a clamping position on the first clamping apparatus, and the adjustable buckle comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle and the clamping position through the threaded connection of the screw rod and the screw hole.

Preferably, the first and second electrodes are formed of a metal,

the first fixture is hinged with the second fixture; and/or the first fixture is an upper fixture, and the second fixture is a lower fixture; and/or a first slot capable of being clamped with one type of missile launcher is arranged on the inner wall of the first fixture, and a second slot capable of being clamped with another type of missile launcher is arranged on the inner wall of the second fixture.

Preferably, the first and second electrodes are formed of a metal,

the missile launching canister is characterized by further comprising a horizontal rotating seat, the horizontal rotating seat is arranged on the base and can rotate horizontally, the connecting pipe assembly comprises a pitching pipe and a vertical pipe, the pitching pipe is connected with the missile launching canister clamp, one end of the vertical pipe is connected with the horizontal rotating seat, the other end of the vertical pipe is connected with the pitching pipe, and the horizontal rotating seat can drive the vertical pipe to rotate.

Preferably, the first and second electrodes are formed of a metal,

the base is arranged on the ground, and the base is arranged on the ground.

Preferably, the first and second electrodes are formed of a metal,

the number of the supporting legs is 3, the supporting legs are distributed along the circumferential direction of the base in a dispersed mode, and the 3 supporting legs extend in an inclined mode along the direction forming an inclination angle with the horizontal direction; and/or the supporting legs are connected with the base through plug pins.

The utility model provides a pair of individual soldier's air defense missile launching cradle has following beneficial effect:

1. the utility model can adjust the height of the launching tube relative to the body of the user according to the requirement and carry on shoulder through setting the seat to be adjustable continuously, especially through the matching mode of the elevating screw and the guide rail tube, thereby improving the comfort, being suitable for shooters with different heights and improving the universality;

2. the utility model discloses still include first and second fixture through missile launcher fixture, and still through adjustable buckle, can locate the launcher card between first and the second fixture, and locate the fixture card on the supporting rib through adjustable buckle, and the length through adjustable buckle adjusting screw and screw spiro union is with the locking dynamics of adjusting the joint, adjust first fixture promptly and support the distance between the rib, thereby the size of the cavity of the surrounding of realization first and second fixture changes as required, can satisfy the card to different launchers and establish as required, suitability and commonality can be stronger.

Drawings

FIG. 1 is a schematic view of the overall structure of the individual air defense missile launching cradle of the utility model;

fig. 2 is a partially enlarged structural view of a portion a in fig. 1;

fig. 3 is a partially enlarged structural view of a portion B in fig. 1;

fig. 4 is the utility model discloses a use state diagram of individual soldier's air defense missile launching cradle.

The reference numbers in the figures denote:

1. supporting legs; 2. a base; 3. a horizontal rotating base; 4. a vertical tube; 5. a pitch tube; 6. a missile launching canister clamp; 61. a first clamp; 611. a first slot position; 62. a second fixture; 621. a second slot position; 63. A support rib; 64. an adjustable buckle; 7. a seat; 71. lifting a screw rod; 72. adjusting the nut; 73. a guide rail pipe; 74. a chair surface; 75. a chair back; 76. a card slot; 77. a handle.

Detailed Description

As shown in fig. 1-3, the utility model provides an individual soldier air defense missile launching cradle, it includes:

the missile launcher comprises a base 2, a seat 7, a connecting pipe assembly and a missile launcher fixture 6, wherein the seat 7 is arranged on the base 2 and can be subjected to stepless continuously adjustable lifting adjustment, the missile launcher fixture 6 can be used for erecting a missile launcher, and the connecting pipe assembly is used for connecting the base 2 and the missile launcher fixture 6.

The utility model discloses a set the seat to and can carry out the high stepless continuously adjustable lift adjustment, especially the cooperation mode through elevating screw and guide rail pipe, can let the user carry out the regulation of height as required with the launching tube and hold on the shoulder, improved the travelling comfort, be fit for the shooter of different heights, improved the commonality.

The utility model mainly aims at providing a soldier shoulder-resistance missile launching bracket, the seat can be lifted, the height can be continuously adjusted in a stepless way, and the shoulders of a soldier can be comfortably carried on a launching tube, thereby being suitable for shooters with different heights; the missile launcher clamp is compatible with two series of single-soldier low-altitude missile launchers in China, and the clamp is firmly installed and clamped, so that the launching stability is improved, the recoil of launching is absorbed, the safety of a shooter is protected, and the fatigue of the shooter is reduced; the erection and the withdrawal are simple, convenient and quick.

The utility model relates to a single soldier shoulder combats formula guided missile launching cradle. The launching bracket can realize continuous and reciprocating rotation of 0-360 degrees in azimuth by moving with feet in a smaller volume space; the missile launcher clamp rotates 0-40 degrees in a pitching way, the clamp can adaptively adjust the locking degree, and the missile launcher clamp is compatible with two series of individual missile launchers in China; the height of the chair can be continuously adjusted in a stepless way. The self-adaptive locking and clamping device has the advantages of firm clamping and installing, stable structure, stable operation, simple and convenient erection and withdrawal, low manufacturing cost and easy maintenance.

Preferably, the first and second electrodes are formed of a metal,

the seat 7 comprises a lifting screw 71, a guide rail pipe 73 and a seat surface 74, the lifting screw 71 is fixedly connected with the seat surface 74, the guide rail pipe 73 is fixedly arranged on the base 2, and the lifting screw 71 can be sleeved in the guide rail pipe 73 and can move up and down along the vertical direction. Through the elevating screw, the seat can be arranged in the guide rail pipe in a penetrating mode, so that the seat can move in the vertical direction along the guide rail pipe, the seat surface of the seat is driven to move vertically together, stepless regulation is achieved, and comfort and universality are improved. The chair adopts a screw rod lifting mechanism, the height is continuously adjusted manually in a stepless way, the adjustable range is 110mm, the shoulders of the fighter can comfortably carry on the launching tube, and the adjustable height adjustable chair is suitable for the fighter with a larger height range.

Preferably, the first and second electrodes are formed of a metal,

the lifting screw rod device further comprises an adjusting nut 72, the guide rail pipe 73 is provided with a clamping groove 76, the adjusting nut 72 can be arranged in the clamping groove 76 and can accommodate the lifting screw rod 71 to penetrate through the adjusting nut 72, and the lifting screw rod is adjusted by the adjusting nut 72 to be in threaded connection with the adjusting nut so as to enable the lifting screw rod to move up and down. The lifting screw rod is driven to move up and down by the threaded connection of the adjusting nut and the external thread of the lifting screw rod, the adjusting nut is clamped through the clamping groove in the guide rail pipe so as to fix the adjusting nut, the up-and-down position of the nut is fixed, and therefore the lifting screw rod is driven to move up and down by the matching of the threads when the nut is rotated. The assembly sequence is to place the nut into the clamping groove when the screw rod is inserted into one half of the guide rail pipe, and then drop the screw rod to penetrate into the nut to form assembly connection.

Preferably, the first and second electrodes are formed of a metal,

a tenon is arranged on the inner wall of the guide rail pipe 73 in a manner of extending along the axial direction of the guide rail pipe 73, a groove is further formed on the outer wall surface of the lifting screw rod 71 in a manner of extending along the axial direction of the guide rail pipe, and the tenon can be inserted into the groove along the axial direction to stop rotation of the lifting screw rod; and/or, the outer wall of the adjusting nut 72 is provided with at least three handles 77 distributed along the circumferential direction, preferably three handles uniformly distributed at 120 degrees in the circumferential direction; and/or, the seat 7 further comprises a seat back 75, and the seat back 75 is fixedly arranged on the seat surface 74.

This is the utility model discloses a further preferred structural style, through the tenon that sets up on the guide rail pipe inner wall and the recess that sets up along the axis direction on the lead screw outer wall, can make the tenon insert in the recess along the axis direction, thereby form the effect of splining to the lead screw effectively, prevent that the lead screw from rotating, only make the lead screw can the up-and-down motion, thereby make the seat of seat only move in the vertical direction and do not take place to rotate, make the user use more comfortable, make the orientation only adjust in the vertical direction simultaneously, and can not take place the deflection of horizontal direction, improve the stability of soldier's sitting and standing operation, thereby improve the precision of location hit; the rotation torque of the nut can be increased through the arrangement of the handle, so that the rotation adjustment of the nut is convenient, labor-saving and convenient; the chair back is convenient for users to use and is more comfortable.

Preferably, the first and second electrodes are formed of a metal,

the missile launcher clamping apparatus 6 comprises a first clamping apparatus 61, a second clamping apparatus 62, a supporting rib 63 and an adjustable buckle 64, wherein one end of the second clamping apparatus 62 is connected with the supporting rib 63, the other end of the second clamping apparatus 62 is connected with one end of the first clamping apparatus 61, and the other end of the first clamping apparatus 61 can be clamped on the supporting rib 63 through the adjustable buckle 64. Include first and second fixture through missile launcher fixture, and still through adjustable buckle, can locate the launch canister card between first and second fixture, and locate the fixture card on supporting the rib through adjustable buckle, and can adjust first fixture and support the distance between the rib through adjustable buckle, guarantee that first and second fixture surround the space size that holds the missile launcher and change, thereby can satisfy the card to different launch canisters as required and establish, suitability and commonality are stronger.

Preferably, the first and second electrodes are formed of a metal,

the adjustable buckle 64 is arranged on the first fixture 61, the supporting rib 63 is provided with a clamping position, and the adjustable buckle 64 comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle 64 and the clamping position through the threaded connection of the screw rod and the screw hole;

or, the adjustable buckle 64 is arranged on the supporting rib 63, a clamping position is arranged on the first fixture 61, and the adjustable buckle 64 comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle 64 and the clamping position through the threaded connection of the screw rod and the screw hole.

The adjustable buckle comprises a screw rod and a screw hole structure, the length of the screw rod in threaded connection with the screw hole is adjusted to adjust the clamping locking force, namely, the distance between the first fixture and the supporting rib is adjusted, so that the size of a cavity surrounded by the first fixture and the second fixture is changed as required, the compatibility is good, the adjustable buckle is adaptive to two series of individual soldier air defense missile launching tubes in China, the adaptive locking is realized, and the clamping is firm; the missile launcher clamps adopt compatible design, are designed and processed according to the barrel diameter appearance of two series of individual soldier air defense missile launchers in China, and are suitable for installing two series of missile launchers; the locking degree of the clamp structure is adjustable, the missile launching tube is locked in a self-adaptive manner through the adjustable buckle arranged on the clamp structure, and the adjustable buckle is convenient and firm to clamp and disassemble the missile launching tube;

preferably, the first and second electrodes are formed of a metal,

the first fixture 61 is hinged with the second fixture 62; and/or the first fixture 61 is an upper fixture, and the second fixture 62 is a lower fixture; and/or a first slot 611 capable of being clamped with one missile launching tube is arranged on the inner wall of the first fixture 61, and a second slot 621 capable of being clamped with another missile launching tube is arranged on the inner wall of the second fixture 62. Further preferably, the first jig 61 has a semi-annular structure, and the second jig 62 has a semi-annular structure.

This is the utility model discloses a further preferred structural style, can block through first trench promptly and establish a kind of guided missile launch canister, second trench can block and establish another kind of guided missile launch canister, the adaptability is stronger.

Preferably, the first and second electrodes are formed of a metal,

still include horizontal rotation seat 3 set up in just can carry out the horizontal rotation on the base 2, the connecting tube subassembly includes every single move pipe 5 and vertical pipe 4, every single move pipe 5 with missile launch canister fixture 6 is connected, vertical pipe one end with horizontal rotation seat 3 is connected, the other end with every single move pipe 5 is connected, horizontal rotation seat 3 can drive vertical pipe 4 is rotatory.

Through the horizontal rotating seat, the missile launcher fixture can be finally adjusted when rotating (rotating in the horizontal direction) through the vertical pipe and the pitching pipe, so that the positioning can be more accurate and precise, and the striking precision is improved.

Preferably, the first and second electrodes are formed of a metal,

the device also comprises support legs which are arranged at the lower part of the base 2 and used for supporting the base 2 on the ground. The supporting function of the base and even the whole individual air defense missile launching support can be realized through the supporting legs.

Preferably, the first and second electrodes are formed of a metal,

the number of the supporting legs 1 is 3, the supporting legs are distributed and distributed along the circumferential direction of the base 2, and the 3 supporting legs extend obliquely along the direction forming an inclination angle with the horizontal direction (the inclination angle is not 0 and is between the horizontal direction and the vertical direction); and/or the supporting leg 1 is connected with the base 2 through a plug pin. Can form firm support, 3 supporting legs to the support along the incline direction can realize quick plug, the stronger effect of detachability through the plug pin, and structural strength guarantees. The weight of the support is 30Kg, the tripod and the base are connected by adopting the quick plug pins, and the support is simple, convenient and quick to erect and withdraw.

The launching bracket provides a stepless continuous height-adjustable mechanism for a seat and a compatible and self-adaptive missile locking clamp structure, and has the advantages of portability, strong bearing capacity, convenience in erection and retraction, wide range of suitable shooters, improvement on shoulder comfort level, convenience and rapidness in erection and retraction and the like.

The missile launching bracket takes hard aluminum alloy 2A12 and Q235 pipes as an outer frame structure, a rotating part adopts wear-resistant parts and high-strength parts such as 45# steel, 40Cr and the like, and two ends of a rotating shaft are supported by bearings. The structure is stable, the layout is reasonable, the installation is simple, the fixed part is mainly connected by screw threads, and the rotating part is mainly connected by flat keys; the horizontal 0-360 degree continuous and reciprocating rotation can be realized, and the pitching angle is 0-40 degree; the maximum pitching angle of 40 degrees is not very large, and the reason is that if the elevation angle is too large, the contact bounce of the ejected objects at the rear part of the launching tube can cause physical damage to a fighter, so that the great elevation angle is not suitable for being realized.

Low manufacturing cost, convenient installation and easy maintenance: the mechanism is easy to process and assemble from the process angle, has clear structural hierarchy, complete functions and compact space, and can be easily assembled by 2 persons; the manufacturing cost is low; the disassembly is simple and convenient, and the maintenance is convenient.

The utility model discloses a guided missile launch support installation step:

1. the supporting legs are connected to the base through the quick plug pins to form a stable bottom support of the whole support;

2. a horizontal rotating shaft is arranged in the base, and two ends of the rotating shaft are respectively provided with a deep groove ball bearing support;

3. the horizontal rotating seat is connected with a horizontal rotating shaft of the base through a flat key and is locked by double nuts, so that the horizontal rotating seat 3 is connected with the horizontal rotating shaft into a whole;

4. the 90-degree short bent part at the lower part of the vertical pipe is welded on the opening on the cylindrical surface of the horizontal rotating seat 3; the vertical pipe 4 and the horizontal rotary seat 3 are connected into a whole, and the vertical pipe 4 and the horizontal rotary seat 3 synchronously rotate;

5. the lower vertical pipe of the pitching pipe is fixedly connected with the vertical pipe 4 through step limiting and threaded connection; a pitching shaft is arranged in the transverse part of the pitching pipe 5, and two ends of the pitching shaft are respectively provided with a deep groove ball bearing support; the pitching rotating cover and the pitching shaft are fixedly connected into a whole through threads, and the pitching rotating cover and the pitching rotating shaft rotate synchronously;

6. the supporting ribs 63 of the missile fixture are connected with the pitching rotating cover through pins; the missile launching canister clamp 6 and the pitching rotating cover synchronously rotate; the pitching rotation is 0-40 degrees, and the pitching angle range is limited by the end face of the fan-shaped boss of the pitching rotation cover; the maximum pitching angle of 40 degrees is not very large, and the reason is that if the elevation angle is too large, the contact bounce of the ejected objects at the rear part of the launching tube can cause physical damage to a fighter, so that the great elevation angle is not suitable for being realized.

The lower fixture is hinged with the upper fixture, the lower fixture is welded and fixed on the supporting ribs 63, the upper fixture can rotate by more than 180 degrees, when the missile launcher is installed, the upper fixture is rotated to be opened, then the missile launcher is installed in the lower fixture, the upper fixture is rotated to be closed, and the wire slot on the launcher is placed in the corresponding slot position of the fixture; the missile launcher clamp 6 can be suitable for installing two series of missile launchers in China; in fig. 3, slot positions suitable for accommodating two series of missile launching cylinders are marked;

the hook size of the adjustable buckle 64 can be adjusted, and the missile launcher clamp can be adaptively locked to an appropriate force according to the actual clamping tightness;

7. the seat part is fixedly connected to the side surface of the horizontal rotating seat 3 through two pins. When in operation, a soldier can sit on the seat surface 74 and lean against the back 75 to relieve fatigue;

the height of the seat 7 can be continuously adjusted in a stepless way, the handle 77 of the adjusting nut 72 is rotated by a soldier by left-handed rotation or right-handed rotation, the lifting screw rod 71 can do up-and-down lifting movement under the limited rotation of the guide rail pipe 73, the translation range is 110mm, the shoulders of the soldier can be comfortably carried on the launching tube, and the height adjusting device is suitable for the soldiers in a large-range height section;

when a shooter sits on the seat 7 and steps are pedaled, the horizontal rotating seat 3 and the missile launcher clamping device 6 which is fixedly connected with the horizontal rotating seat can be rotated to clamp the launcher, so that the target can be aimed in time, and timely launching operation can be performed. The supporting leg 1 adopts "worker" style of calligraphy cross section, and structural strength, rigidity are high to supporting leg 1 has the ground dish that falls of disc, and bearing load ability is strong, can bear and absorb the transmission recoil, forms the protection to the fighter's health.

The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention. The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.

Claims (10)

1. The utility model provides an individual soldier air defense missile launching cradle which characterized in that: the method comprises the following steps:

base (2), seat (7), connecting pipe subassembly and missile launching canister fixture (6), wherein seat (7) set up in on base (2), and can carry out the stepless continuously adjustable's of height lift adjustment, missile launching canister fixture (6) can be used for erectting the missile launching canister, the connecting pipe subassembly is used for connecting base (2) with missile launching canister fixture (6).

2. The individual antiaircraft missile launcher of claim 1, characterized in that:

seat (7) include elevating screw (71), guide rail pipe (73) and seat (74), elevating screw (71) with seat (74) fixed connection, guide rail pipe (73) fixed set up in on base (2), elevating screw (71) can be located by the cover in guide rail pipe (73), and along vertical direction up-and-down motion.

3. The individual antiaircraft missile launcher of claim 2, characterized in that:

the lifting guide rail device is characterized by further comprising an adjusting nut (72), the guide rail pipe (73) is provided with a clamping groove (76), the adjusting nut (72) can be arranged in the clamping groove (76) and can accommodate the lifting screw rod (71) to penetrate through the adjusting nut (72), and the lifting screw rod is adjusted by the adjusting nut (72) to be in threaded connection with the adjusting nut so as to enable the lifting screw rod to move up and down.

4. The individual antiaircraft missile launcher of claim 3, characterized in that:

a tenon is arranged on the inner wall of the guide rail pipe (73) in a manner of extending along the axial direction of the guide rail pipe (73), a groove is further formed in the outer wall surface of the lifting screw rod (71) in a manner of extending along the axial direction of the guide rail pipe, and the tenon can be inserted into the groove along the axial direction to form rotation stop for the lifting screw rod; and/or the outer wall of the adjusting nut (72) is provided with at least three handles (77) distributed along the circumferential direction; and/or the seat (7) further comprises a seat back (75), and the seat back (75) is fixedly arranged on the seat surface (74).

5. The individual soldier air defense missile launching cradle of any one of claims 1 to 4, wherein:

the missile launcher clamping device (6) comprises a first clamping device (61), a second clamping device (62), a supporting rib (63) and an adjustable buckle (64), one end of the second clamping device (62) is connected with the supporting rib (63), the other end of the second clamping device is connected with one end of the first clamping device (61), and the other end of the first clamping device (61) can be clamped on the supporting rib (63) through the adjustable buckle (64).

6. The individual antiaircraft missile launcher of claim 5, characterized in that:

the adjustable buckle (64) is arranged on the first fixture (61), the supporting rib (63) is provided with a clamping position, and the adjustable buckle (64) comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle (64) and the clamping position through the threaded connection of the screw rod and the screw hole;

or the adjustable buckle (64) is arranged on the supporting rib (63), the first fixture (61) is provided with a clamping position, and the adjustable buckle (64) comprises a screw rod and a screw hole so as to control the distance between the adjustable buckle (64) and the clamping position through the threaded connection of the screw rod and the screw hole.

7. The individual antiaircraft missile launcher of claim 5, characterized in that:

the first fixture (61) is hinged with the second fixture (62); and/or the first fixture (61) is an upper fixture, and the second fixture (62) is a lower fixture; and/or a first slot position (611) capable of being clamped with one missile launching tube is arranged on the inner wall of the first clamping apparatus (61), and a second slot position (621) capable of being clamped with another missile launching tube is arranged on the inner wall of the second clamping apparatus (62).

8. The individual air defense missile launching cradle of any one of claims 1-4 and 6-7, wherein:

still include horizontal swivel base (3) set up in on base (2) and can carry out the horizontal rotation, connecting tube subassembly includes every single move pipe (5) and vertical pipe (4), every single move pipe (5) with missile launch barrel fixture (6) are connected, vertical pipe one end with horizontal swivel base (3) are connected, the other end with every single move pipe (5) are connected, horizontal swivel base (3) can drive vertical pipe (4) are rotatory.

9. The individual air defense missile launching cradle of any one of claims 1-4 and 6-7, wherein:

the device also comprises support legs which are arranged at the lower part of the base (2) and used for supporting the base (2) on the ground.

10. The individual antiaircraft missile launcher of claim 9, characterized in that:

the number of the supporting legs (1) is 3, the supporting legs are distributed along the circumferential direction of the base (2), and the 3 supporting legs extend obliquely along the direction forming an inclination angle with the horizontal direction; and/or the supporting leg (1) is connected with the base (2) through a plug pin.

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