阅读说明：本技术 一种40mm火箭筒用自主分离通用有控弹体 (40mm rocket launcher is with general accuse projectile body that has of autonomy separation ) 是由 于剑桥 蒋军 郝渊 于 2019-09-25 设计创作，主要内容包括：本发明提供了一种40mm火箭筒用自主分离通用有控弹体,增加控制舱、电动舵机、制导指引或接收组件、自主分离机构及可折叠裙尾机构；控制舱、电动舵机及自主分离机构顺次连接,均位于超口径舱段,超口径段通过自主分离机构与位于火箭筒内的弹体固定连接；制导指引或接收组件位于自主分离机构内,可折叠裙尾机构安装在自主分离机构前端,弹体发射前可折叠裙尾机构由自主分离机构限位处于折叠状态；弹体发射后,超口径舱段通过自主分离机构与位于火箭筒内的弹体分离,制导指引或接收组件外露,可折叠裙尾机构展开；控制舱完成解算并生成控制指令驱动电动舵机从而控制有控弹体飞行。本发明能够避免导弹后继飞行过程中后段弹体结构对制导信号的遮挡影响。(The invention provides an autonomous separation general controlled projectile body for a 40mm rocket launcher, which is additionally provided with a control cabin, an electric steering engine, a guidance guide or receiving assembly, an autonomous separation mechanism and a foldable skirt tail mechanism; the control cabin, the electric steering engine and the autonomous separating mechanism are sequentially connected and are all positioned in an ultra-caliber cabin section, and the ultra-caliber section is fixedly connected with a projectile body positioned in the rocket tube through the autonomous separating mechanism; the guidance guiding or receiving assembly is positioned in the autonomous separating mechanism, the foldable skirt tail mechanism is arranged at the front end of the autonomous separating mechanism, and the foldable skirt tail mechanism is limited by the autonomous separating mechanism to be in a folded state before the projectile body is launched; after the projectile body is launched, the ultra-caliber cabin section is separated from the projectile body in the rocket tube through the automatic separation mechanism, the guidance guide or receiving assembly is exposed, and the foldable skirt tail mechanism is unfolded; the control cabin completes resolving and generates a control instruction to drive the electric steering engine so as to control the controlled projectile body to fly. The invention can avoid the shielding influence of the rear-section missile body structure on the guidance signal in the subsequent flying process of the missile.)

1. A40 mm rocket launcher is with controlling the projectile body with the general use of autonomous separation, characterized by, increase control cabin, electronic steering engine, guidance and guide or receiving assembly, autonomous separation mechanism and collapsible skirt tail mechanism;

the rocket projectile body positioned outside the rocket barrel is an ultra-caliber cabin section, the control cabin, the electric steering engine and the autonomous separating mechanism are sequentially connected and are all positioned in the ultra-caliber cabin section, and the ultra-caliber section is fixedly connected with the rocket projectile body positioned in the rocket barrel through the autonomous separating mechanism; the guidance guiding or receiving assembly is positioned in the autonomous separating mechanism, the foldable skirt tail mechanism is arranged at the front end of the autonomous separating mechanism, and the foldable skirt tail mechanism is limited by the autonomous separating mechanism to be in a folded state before the projectile body is launched; after the projectile body is launched, the ultra-caliber cabin section is separated from the projectile body in the rocket tube through the automatic separation mechanism, the guidance guide or receiving assembly is exposed, and the foldable skirt tail mechanism is unfolded; the control cabin is used for resolving rocket projectile space position information given by the guidance guide or receiving assembly, and generating a control instruction to drive the electric steering engine so as to control the controlled projectile body to fly.

2. The self-separating universal projectile body as claimed in claim 1 wherein said guidance or receiving assembly is an infrared beacon or laser receiver.

3. The self-separating universal controlled projectile for a 40mm rocket tube as claimed in claim 1 wherein said self-separating mechanism comprises a conical body, shear screws, ignition means, charge pack, drug shield and protective shield;

the conical surface of the conical body is provided with an annular groove, the medicine bag is arranged in the annular groove and is sealed by a medicine baffle plate, and the end surface of the annular groove is provided with an axial hole for installing an igniter; the end face of the small-diameter section of the conical body is used for mounting a guide signal device; the safety cover is the toper, and big footpath end suit is at the toper body conical surface, simultaneously through shear screw and toper body fixed connection, the safety cover path end be equipped with rocket section of thick bamboo in projectile body fixed connection's screw thread.

4. The self-separating universal controlled projectile for a 40mm rocket launcher according to claim 1, wherein said collapsible skirt tail mechanism comprises stabilizing skirt pieces, wing roots, rotating shafts, torsion springs and bayonet locks;

the wing root is integrally in a concave shape and is an integrated structure with vertical rods arranged at two ends of a horizontal rod, the vertical rods at two ends are provided with through holes in rotating fit with the rotating shaft, and meanwhile, the vertical rods at two ends are correspondingly provided with limiting holes in rotating fit with the bayonet pins;

the bayonet lock is L-shaped and is formed by vertically and fixedly connecting a bayonet lock column with a mounting plate, and the mounting plate is provided with a mounting hole for mounting the rotating shaft;

the stabilizing skirt piece is fixedly connected to the horizontal rod of the wing root, and the fixing direction is opposite to the extending direction of the vertical rod; the bayonet is positioned in the wing root opening, the mounting hole is coaxial with the vertical rod through hole, and the bayonet column is in running fit with the limiting hole; the rotating shaft is fixed in the conical body, meanwhile, the rotating shaft is respectively in rotating fit with the wing root through hole and the bayonet lock mounting hole, the torsion spring is sleeved on the rotating shaft, when the steadily increasing skirt piece is folded, the steadily increasing skirt piece is limited by the automatic separating mechanism, and the torsion spring is in a pre-tightening state; after the steadily increasing skirt piece is unfolded in place, the clamping pin column penetrates through the limiting hole to be embedded into the conical body, and the steadily increasing skirt piece is locked.

5. The self-separating universal controlled projectile for a 40mm rocket launcher according to claim 4, wherein said torsion springs comprise a left-handed torsion spring and a right-handed torsion spring, used in pairs.

Technical Field

The invention relates to the technical field of small-caliber guided munitions, in particular to an autonomous separation general controlled projectile body for a 40mm rocket launcher.

Background

A40 mm individual rocket launcher is conventional hard-attacking weapon equipment for infantry short-distance counter-personnel, tanks, armors and workers, is favored due to the characteristics of low cost, light weight, simple operation and convenient carrying, is still greatly equipped and used by various countries at present, and the total equipment amount reaches more than one million. However, all the existing ammunitions of the platform are uncontrolled rocket projectiles, and the maximum firing range is only 300m under the condition that the CEP (scattering accuracy) is 0.45 m. This greatly limits the effectiveness of the 40mm rocket mount long range combat.

The effective way for solving the problem is to develop a guided rocket projectile for a 40mm rocket launcher launching platform, and realize the accurate striking of the 40mm rocket launcher launching platform on a target far from 1500m through an accurate guiding technology, namely, components such as a control cabin are added on the original 40mm rocket projectile, and the requirement of the guided rocket projectile on the striking accuracy after the range is increased can be met. The control cabin of the missile is used for resolving the space position information of the missile given by the guidance guide or receiving component and generating a control instruction by combining the rolling attitude angle of the missile in the flying process to control the missile to fly to a target; and simultaneously supplies power to the missile electrical system. However, the special launching structure of the 40mm rocket launcher determines that the standard rocket launcher used on the rocket launcher can only adopt a flight engine and a tail wing assembly structure with the caliber less than 40mm, the space size is very limited, and in the launching process, the components of the rocket launcher positioned in the launching launcher need to bear the bore pressure exceeding 80MPa, so that the arrangement of a precise guiding and guiding or receiving assembly at the tail part is difficult to realize in the process of developing the guiding rocket launcher; meanwhile, the tail guidance guide or receiving assembly and the ultra-caliber section control cabin are in power supply and signal transmission.

One possible solution to solve the above problems is to place the guidance or receiving assembly at the ultra-caliber ring part at the rear end of the ultra-caliber section of the rocket projectile, and such a structural layout arrangement can well solve the influence of high chamber pressure on the guidance or receiving assembly. However, due to the limitation of the special structure of the rocket projectile, the guidance or receiving assembly is arranged in the middle of the projectile body, so that the guidance signal is shielded by the rear structure of the projectile body, and for a laser beam-driving guidance mode, the laser signal is not continuous due to shielding; for infrared angle measurement plus instruction guidance, blocking can cause discontinuity of ground receiving rocket projectile position information and uploading control information. Discontinuous guidance information can bring great problems to the design of a guided rocket projectile control system and the guarantee of control precision.

Disclosure of Invention

In view of the above, the invention provides an autonomous separation general controlled projectile body for a 40mm rocket launcher, which can avoid the shielding influence of the structure of the rear projectile body on a guidance signal in the subsequent flying process of a missile.

The technical scheme adopted by the invention is as follows:

a40 mm rocket launcher is with controlling the projectile body with the general use of autonomous separation, increase the control cabin, electronic steering engine, guidance guide or receiving assembly, autonomous separation mechanism and collapsible skirt tail mechanism;

the rocket projectile body positioned outside the rocket barrel is an ultra-caliber cabin section, the control cabin, the electric steering engine and the autonomous separating mechanism are sequentially connected and are all positioned in the ultra-caliber cabin section, and the ultra-caliber section is fixedly connected with the rocket projectile body positioned in the rocket barrel through the autonomous separating mechanism; the guidance guiding or receiving assembly is positioned in the autonomous separating mechanism, the foldable skirt tail mechanism is arranged at the front end of the autonomous separating mechanism, and the foldable skirt tail mechanism is limited by the autonomous separating mechanism to be in a folded state before the projectile body is launched; after the projectile body is launched, the ultra-caliber cabin section is separated from the projectile body in the rocket tube through the automatic separation mechanism, the guidance guide or receiving assembly is exposed, and the foldable skirt tail mechanism is unfolded; the control cabin is used for resolving rocket projectile space position information given by the guidance guide or receiving assembly, and generating a control instruction to drive the electric steering engine so as to control the controlled projectile body to fly.

Further, the guidance or receiving component is an infrared beacon or a laser receiver.

Furthermore, the automatic separation mechanism comprises a conical body, a shearing screw, an igniter, a medicine bag, a medicine baffle plate and a protective cover;

the conical surface of the conical body is provided with an annular groove, the medicine bag is arranged in the annular groove and is sealed by a medicine baffle plate, and the end surface of the annular groove is provided with an axial hole for installing an igniter; the end face of the small-diameter section of the conical body is used for mounting a guide signal device; the safety cover is the toper, and big footpath end suit is at the toper body conical surface, simultaneously through shear screw and toper body fixed connection, the safety cover path end be equipped with rocket section of thick bamboo in projectile body fixed connection's screw thread.

Furthermore, the foldable skirt tail mechanism comprises stably-increased skirt pieces, wing roots, a rotating shaft, a torsion spring and a bayonet lock;

the wing root is integrally in a concave shape and is an integrated structure with vertical rods arranged at two ends of a horizontal rod, the vertical rods at two ends are provided with through holes in rotating fit with the rotating shaft, and meanwhile, the vertical rods at two ends are correspondingly provided with limiting holes in rotating fit with the bayonet pins;

the bayonet lock is L-shaped and is formed by vertically and fixedly connecting a bayonet lock column with a mounting plate, and the mounting plate is provided with a mounting hole for mounting the rotating shaft;

the stabilizing skirt piece is fixedly connected to the horizontal rod of the wing root, and the fixing direction is opposite to the extending direction of the vertical rod; the bayonet is positioned in the wing root opening, the mounting hole is coaxial with the vertical rod through hole, and the bayonet column is in running fit with the limiting hole; the rotating shaft is fixed in the conical body, meanwhile, the rotating shaft is respectively in rotating fit with the wing root through hole and the bayonet lock mounting hole, the torsion spring is sleeved on the rotating shaft, when the steadily increasing skirt piece is folded, the steadily increasing skirt piece is limited by the automatic separating mechanism, and the torsion spring is in a pre-tightening state; after the steadily increasing skirt piece is unfolded in place, the clamping pin column penetrates through the limiting hole to be embedded into the conical body, and the steadily increasing skirt piece is locked.

Further, the torsion springs comprise a left-handed torsion spring and a right-handed torsion spring which are used in pairs.

Has the advantages that:

1. according to the invention, the control cabin, the electric steering engine, the guidance or receiving assembly, the automatic separation mechanism and the foldable skirt tail mechanism are added, and the controlled projectile body adopts the automatic separation mechanism to separate the flying engine and the tail wing assembly at the rear section of the rocket projectile from the super-caliber part at the front section of the rocket projectile after the operation of the rocket projectile flying engine is finished, so that the shielding influence of the rear section projectile body structure on guidance signals in the subsequent flying process of the missile is avoided; meanwhile, in order to ensure the flight stability and the control capability of the ultra-caliber part at the front end of the rocket projectile, the controllable projectile body also adopts an electric steering engine and a foldable skirt tail mechanism which is matched with the automatic separating mechanism to act and can be unfolded, so that the flight stability and the control capability of the ultra-caliber part are ensured.

2. The invention adopts a pair of torsion springs with opposite rotation directions, so that the unfolding and folding actions of the stably-increased skirt piece of the foldable skirt tail mechanism are more reliable and stable.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the controlled projectile of the present invention;

FIG. 2 is a schematic structural view of an autonomous separating mechanism;

FIGS. 3(a) and (b) are schematic structural views of the rocket projectile ultra-caliber cabin section in unfolded and folded states of the steadily increasing skirt piece respectively;

FIGS. 4(a), (b), (c) are right side, front and partial cross-sectional views, respectively, of the collapsible skirt tail mechanism;

FIG. 5 is a schematic view of the structure of a wing root;

FIG. 6 is a schematic view of the latch;

the airplane comprises a guidance system 1, a control cabin 2, an electric steering engine 3, an autonomous separation mechanism 4, a flight engine 5, a tail wing assembly 6, a foldable skirt tail mechanism 7, a laser receiver 8, a conical body 9, an igniter 10, a medicine baffle 11, a medicine bag 12, a protective cover 13, a wing root 14, a bayonet 15, a stable skirt piece 16, a left-handed torsion spring 17, a right-handed torsion spring 18, a rotating shaft 19, a locking groove 20, a radial shaft hole 21, a mounting groove II 22, a mounting groove I23, a limiting hole 24, a through hole 25, a rivet hole 26, a bayonet column 27, a mounting hole 28 and a rudder piece 29.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

The embodiment provides an autonomous separation general controlled projectile body for a 40mm rocket launcher, which comprises a missile launching system 1, a control cabin 2 (a missile-borne computer, a roll angle measuring device and a missile-borne power supply), an electric steering engine 3, an autonomous separation mechanism 4/a foldable skirt tail mechanism 7, a flight engine 5 and a tail wing assembly 6 in sequence from the head as shown in fig. 1. In addition, the weapon system also comprises a ground guidance instrument.

The rocket projectile body positioned outside the rocket tube is an ultra-caliber cabin section, the control cabin 2, the electric steering engine 3 and the autonomous separating mechanism 4 are sequentially connected and are all positioned in the ultra-caliber cabin section, and the ultra-caliber section is fixedly connected with the rocket projectile body positioned in the rocket tube through the autonomous separating mechanism 4; the guidance guiding or receiving assembly is positioned in the autonomous separating mechanism 4, the foldable skirt tail mechanism 7 is installed at the front end of the autonomous separating mechanism 4, and the foldable skirt tail mechanism 7 is limited by the autonomous separating mechanism 4 to be in a folded state before the projectile body is launched; after the projectile body is launched, the ultra-caliber cabin section is separated from the projectile body in the rocket tube through the automatic separation mechanism 4, the guidance guide or receiving assembly is exposed, and the foldable skirt tail mechanism 7 is unfolded; the control cabin 2 is used for resolving the space position information of the rocket projectile given by the guidance guide or receiving component, and generating a control command by combining the rolling attitude angle of the missile in the flying process to drive the electric steering engine 3 so as to control the controlled projectile to fly.

The specific forms and functions of the above components are as follows:

(1) the detonator system 1 is composed of a detonator, a security mechanism, a detonator and a warhead.

(2) The electric steering engine 3 is composed of a rudder sheet 29, a transmission mechanism, a motor, a driver and the like, and receives a control instruction given by the control cabin 2 to generate a control force and a control moment, so that the rocket is bounced to fly towards a target.

(3) The control pod 2 contains a roll angle measurement device, an onboard computer and an onboard power source. The roll angle measuring device consists of a Hall geomagnetic sensitive sensor and a signal resolving circuit and is used for outputting a roll attitude angle of the rocket projectile in the flight process; the missile-borne computer is used for resolving space information given by the guidance guide or receiving assembly and generating a control instruction by combining a projectile roll angle given by the roll angle measuring device; the pop-up power source employs a thermal battery, activated by a launch overload, for powering the pop-up electrical system.

(4) The autonomous separating mechanism 4: and executing a separation instruction output by the missile-borne computer in the control cabin 2, and separating the rocket projectile flight engine 5 and a rear cabin body from the ultra-caliber cabin section after the rocket projectile flight engine 5 finishes working. As shown in fig. 2, the autonomous separating mechanism 4 comprises a conical body 9, a shear screw, an igniter 10, a medicine package 12, a medicine baffle plate 11 and a protective cover 13; the conical body 9 is used for connecting the electric steering engine 3, an annular groove is formed in the conical surface, the medicine bag 12 is installed in the annular groove and is sealed through the medicine baffle plate 11, and an axial hole for installing the igniter 10 is formed in the end face of the annular groove; the end surface of the small diameter section of the conical body 9 is used for installing a guidance guide or receiving assembly; the protection cover 13 is conical, the large-diameter end is sleeved on the conical surface of the conical body 9, meanwhile, the small-diameter end of the protection cover 13 is fixedly connected with the conical body 9 through a shear screw, and threads fixedly connected with the projectile body in the rocket tube are arranged at the small-diameter end of the protection cover 13.

The working principle is as follows: after the flying engine 5 finishes working, the missile-borne computer controls the igniter 10 to work, the explosive package 12 is ignited, the shearing screw for fixing the protective cover 13 is sheared under the action of high-pressure gas, and meanwhile, the high-pressure gas further pushes the protective cover 13 away from the conical body 9, so that the separation of a rear cabin section and an ultra-caliber cabin section of the flying engine 5 is realized.

(5) Foldable skirt tail mechanism 7: before the rocket projectile flying engine 5 finishes working, the rear cabin section and the front end ultra-caliber cabin section of the rocket projectile flying engine 5 are not separated yet, and the steadily increasing skirt piece 16 is folded on the conical surface of the conical body 9 of the autonomous separating mechanism 4 at the rear part of the projectile ultra-caliber section; after the flying engine 5 finishes working, the steadily increasing skirt piece 16 is matched with the self-separating mechanism 4 to act, and is unfolded in place after the protective cover 13 of the self-separating mechanism 4 is separated. After the rear part of the rocket projectile is separated from the ultra-caliber cabin section, the stably-increased skirt piece 16 is unfolded outwards to form a skirt tail structure. The schematic structural diagrams of the rocket projectile super-caliber cabin section in the unfolded and folded state of the stabilizing skirt piece 16 are shown in fig. 3(a) and 3 (b).

As shown in fig. 4(a), 4(b) and 4(c), the foldable skirt tail mechanism 7 is installed at the large end of the tapered body 9, and comprises four steady skirt pieces 16 (six, eight or more pieces can be adopted), a wing root 14, a torsion spring, a rotating shaft 19 and two clamping pins 15. As shown in fig. 5, the wing root 14 is in a shape of a Chinese character 'ao', and is an integrated structure with vertical rods at two ends of a horizontal rod, the vertical rods at two ends are provided with through holes 25 rotatably matched with the rotating shaft 19, the vertical rods at two ends are correspondingly provided with limiting holes 24 rotatably matched with bayonet columns 27, and the limiting holes 24 are positioned at the inner sides of the through holes 25; the horizontal rod is provided with a rivet hole 26 and a mounting groove I23 which are fixedly connected with the steadily increasing skirt piece 16. As shown in fig. 6, the bayonet 15 is L-shaped and is formed by a bayonet column 27 vertically and fixedly connected to a mounting plate, and the mounting plate is provided with a mounting hole 28 for mounting the rotating shaft 19.

The stabilizing skirt 16 is mounted in the mounting slot i 23 of the horizontal bar of the root 14 and is secured by rivets passing through rivet holes 26 in a direction opposite to the direction in which the vertical bars extend. The big end of the conical body 9 is provided with a mounting groove II 22 for mounting a vertical rod of the wing root 14, a torsion spring and a clamping pin 15, a radial shaft hole 21 for mounting a rotating shaft 19 is arranged in the mounting groove II 22, and a locking groove 20 in clearance fit with the clamping pin column 27 is also arranged. The torsional spring is two: the left-handed torsion spring 17 and the right-handed torsion spring 18 have opposite rotation directions. The bayonet 15 is positioned in the opening of the wing root 14, the mounting hole 28 is coaxial with the through hole 25 of the vertical rod, and the part of the bayonet column 27 is in running fit with the limiting hole 24; two ends of the rotating shaft 19 are fixed in the radial shaft hole 21 of the mounting groove II 22 and simultaneously pass through a through hole 25 on one side of the wing root 14, a mounting hole 28 of the first bayonet pin 15, the left-handed torsion spring 17, the right-handed torsion spring 18, a mounting hole 28 of the second bayonet pin 15 and a through hole 25 on the other side of the wing root 14.

When the stably-increased skirt piece 16 is unfolded in place, the bayonet columns 27 are positioned in the locking grooves 20, and the bayonet columns 27 are in clearance fit with the locking grooves 20; when steadily increasing skirt piece 16 and withdrawing, use special frock to make bayonet lock post 27 of bayonet lock 15 withdraw from in the locking groove 20 of body, compress two torsional springs simultaneously, it is folding to steadily increase skirt piece 16, wing root 14 revolves axle 19 and rotates, bayonet lock post 27 of bayonet lock 15 still is located wing root 14's spacing hole 24 this moment, bayonet lock post 27 terminal surface top is at body mounting groove II 22 internal face, steadily increase skirt piece 16 is in fold condition, hoop steadily increase skirt piece 16 by the safety cover 13 of autonomic separating mechanism 4. After the projectile body flies out of the rocket launcher, the protective cover 13 of the autonomous separating mechanism 4 is thrown away, the steadily increasing skirt piece 16 is opened under the action of the torsion spring, the steadily increasing skirt piece 16 is opened in place, the bayonet pin columns 27 of the two bayonet pins 15 respectively enter the locking grooves 20 of the conical body 9, and under the action of the torsion spring and the bayonet pin columns 27, the steadily increasing skirt piece 16 cannot rotate around the rotating shaft 19 to complete locking.

(6) The flight engine 5: used for accelerating the rocket projectile after the rocket projectile is launched.

(7) The tail assembly 6: consists of a tail rod and a tail wing and is used for stabilizing the flying state of the rocket projectile.

(8) The ground fire control guidance instrument: the ground fire control guidance instrument is composed of a white light/red appearance aiming module and a laser beam steering guidance module, wherein the white light/red appearance aiming module is used for aiming and tracking a target, and the laser beam steering guidance module is used for emitting coded laser beams to a space and providing guidance information for a missile.

The working principle of the autonomous separation general controlled projectile body is as follows:

the guidance or receiving component may be a laser receiver 8 or an infrared beacon, and the present implementation employs a laser receiver 8. After the shooter enters a place of battle, the missile is loaded into the rocket tube, the rocket tube is placed on the shoulder, the target is searched and aimed through the white light/infrared aiming channel of the fire control guidance instrument, and after the target is stably aimed, the shooter pulls the trigger to ignite the propellant powder of the rocket. High-pressure gas generated after the propellant powder is ignited acts on the projectile body to push the guided rocket projectile out of the rocket tube. And meanwhile, a thermal battery in the missile-borne control module is activated under the action of launching overload. After the rocket projectile flying engine 5 works, the autonomous separation mechanism 4 receives an instruction of a projectile loading computer in the control cabin 2, the rear part of the rocket projectile is separated from the ultra-caliber cabin section, a laser receiver 8 arranged at the tail part of the projectile body in the ultra-caliber cabin section is exposed, the laser receiver 8 starts to receive laser information and outputs projectile body space information to the projectile loading computer, the projectile loading computer generates a control instruction by combining with the projectile body roll angle given by a roll angle measuring device to drive the electric steering engine 3 to move, the electric steering engine 3 drives the rudder piece 29 to rotate to form control force and control torque, and the missile is controlled to fly along a sight line; and meanwhile, the four stably-increased skirt pieces 16 are unfolded to form a skirt tail structure, so that the flight stability and the control capability of the ultra-caliber cabin section are ensured until the target is hit. The working principles of signal transmission between the laser receiver 8 and the missile-borne computer in the control cabin 2, the roll angle measuring device in the control cabin 2, the missile-borne computer and the thermal battery are the prior art and are not improved.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.