阅读说明：本技术 一种带有减速装置的全向反斜面导弹 (Omnidirectional reverse inclined plane missile with speed reducer ) 是由 于剑桥 蒋军 于 2020-12-29 设计创作，主要内容包括：本发明提供了一种带有减速装置的全向反斜面导弹,包括制导组件、弹载控制模块、战斗部、斜置喷管增速发动机、电动舵机、减速装置、飞行发动机、尾翼组件和发射发动机；制导组件、弹载控制模块、战斗部、斜置喷管增速发动机、电动舵机、减速装置、飞行发动机、尾翼组件和发射发动机由头至尾顺次连接构成导弹；电动舵机根据控制指令执行动作使导弹沿规划弹道飞行直至击中目标。本发明可实现对建筑物进行全向打击,具备在城市战中对目标精确打击和压制的能力。(The invention provides an omnidirectional anti-slope missile with a speed reducer, which comprises a guidance assembly, a missile-borne control module, a warhead, an inclined spray pipe speed-increasing engine, an electric steering engine, a speed reducer, a flight engine, a tail wing assembly and a launching engine, wherein the missile-borne control module is arranged on the warhead; the missile comprises a guidance assembly, a missile loading control module, a warhead, an inclined spray pipe speed-increasing engine, an electric steering engine, a speed-reducing device, a flight engine, a tail wing assembly and a launching engine which are sequentially connected from head to tail to form a missile; and the electric steering engine executes actions according to the control instructions to enable the missile to fly along the planned trajectory until the missile hits the target. The invention can realize the omnidirectional striking to the building and has the capability of accurately striking and suppressing the target in urban war.)

1. An omnidirectional anti-slope missile with a speed reducer is characterized by comprising a guidance assembly, a missile loading control module, a warhead, an inclined spray pipe speed-increasing engine, an electric steering engine, the speed reducer, a flight engine, a tail wing assembly and a launching engine;

the guidance assembly, the missile loading control module, the warhead, the inclined spray pipe speed-increasing engine, the electric steering engine, the speed reducer, the flight engine, the empennage assembly and the launching engine are sequentially connected from head to tail to form a missile;

the launching engine provides initial power for launching the guided missile, the guided missile flies opposite to a target in a launching stage, and the flight engine provides power for the launching stage of the guided missile; after the missile flies to a preset position, the speed reducer works to enable the missile to enter a speed reduction stage; when the guidance assembly detects that the posture of the missile changes into a downward head, a mechanism from the speed reducer to the tail is thrown away; then the missile enters an attitude adjusting stage and an attacking stage, the inclined spray pipe speed-increasing engine provides power for accelerating the missile, and fuel gas acts on a rudder of an electric steering engine to adjust the head direction of the missile to be directed at a target; the missile control system comprises a guidance assembly, a missile-borne control module, an electric steering engine and a corresponding trajectory correction control instruction, wherein the guidance assembly resolves position and attitude information of a missile body in real time and transmits the position and attitude information to the missile-borne control module, the missile-borne control module is communicated with the electric steering engine, the corresponding trajectory correction control instruction is generated by combining with a missile flight time sequence and is transmitted to the electric steering engine, and the electric steering engine is used for executing actions according to the control instruction to enable the missile to fly along a planned trajectory until the missile hits a target.

2. The omnidirectional anti-slope missile with the reduction gear according to claim 1, wherein the reduction gear comprises a connecting cylinder, a pressure spring, a reduction parachute bay shell, a push plate, a reduction parachute, a connecting stud, a connecting cover and two sets of ignition devices;

the speed reducing umbrella cabin shell is a cylinder with one open end and one closed end, the closed end is fixedly connected with the connecting cylinder, the end face of the closed end and the inner wall of the connecting cylinder form a separated chemical chamber I, one set of ignition device is arranged on the connecting cylinder, and when certain pressure is reached in the separated chemical chamber I, the speed reducing umbrella cabin shell is separated from the connecting cylinder; one end of the pressure spring is fixed on the inner wall of the closed end, the other end of the pressure spring is fixed on the push plate, the speed reducing umbrella is fixed in the speed reducing umbrella cabin shell, the connecting cover is fixedly connected to the open end of the speed reducing umbrella cabin shell, the speed reducing umbrella is pressed between the push plate and the inner wall of the connecting cover, and the pressure spring is in a compressed state; the other set of ignition device is arranged on the connecting cover, a separation medicine chamber II is arranged in the connecting cover, and when certain pressure is reached in the separation medicine chamber II, the connecting cover is separated from the speed reducing umbrella cabin shell.

3. The omnidirectional anti-slope missile with the reduction gear according to claim 1, wherein the reduction gear comprises a connecting cylinder, a reduction plate cabin shell, a pressure spring, a rotating shaft, a reduction plate, a torsion spring, a push plate, a connecting cover and two sets of ignition devices;

the speed reduction plate cabin shell is a cylinder with one open end and one closed end, the closed end is fixedly connected with the connecting cylinder, the end face of the closed end and the inner wall of the connecting cylinder form a separated chemical chamber I, one set of ignition device is arranged on the connecting cylinder, and when certain pressure is reached in the separated chemical chamber I, the speed reduction plate cabin shell is separated from the connecting cylinder; one end of the pressure spring is fixed on the inner wall of the closed end, and the other end of the pressure spring is fixed on the push plate; the speed reducing plate is rotatably connected to the cylinder through the rotating shaft and attached to the outer circumferential surface of the cylinder, the torsion spring is sleeved on the rotating shaft, and meanwhile, the radial extension rod of the speed reducing plate extends into the speed reducing plate cabin shell to be clamped with the axial locking pin of the push plate so as to limit the rotation of the speed reducing plate; the connecting cover is fixedly connected to the open end of the speed reducing plate cabin shell, and the push plate is extruded to enable the pressure spring to be in a compressed state; the other set of ignition device is arranged on the connecting cover, a separation medicine chamber II is arranged in the connecting cover, and when certain pressure is reached in the separation medicine chamber II, the connecting cover is separated from the speed reduction plate cabin shell; under the action of the pressure spring, the radial extension rod of the speed reducing plate is separated from the axial locking pin of the push plate, and the speed reducing plate rotates outwards by 90 degrees along the rotating shaft under the action of the torsion spring.

4. An omnidirectional anti-slope missile according to claim 2 or claim 3, wherein the connecting cylinder is a cylinder with one open end and one closed end, the open end is provided with an annular boss, the inner surface of the annular boss is provided with threads, the inner end surface of the annular boss is provided with a sawtooth cutting angle, and the sawtooth cutting angle is broken under a certain pressure.

5. An omnidirectional anti-slope missile with a speed reducer according to claim 2 or 3, wherein the cavity of the separation chamber II is provided with a sawtooth cutting angle, and the sawtooth cutting angle is broken under certain pressure to separate the connecting cover from the connected parts.

6. The omnidirectional anti-slope missile of claim 3, wherein the thrust plate is a structural member formed by connecting two circular plates into a whole by a connecting rod, and an axial locking pin is provided on an outer surface of one of the circular plates.

Technical Field

The invention relates to the technical field of guided missiles, in particular to an omnidirectional anti-slope missile with a speed reducing device.

Background

Urban combat is one of the main forms of modern war. The street lane is moved about freely and quickly in the city, and the building is tall and big and intensive, and such operation condition makes the city war possess following characteristics: 1. easy conservation and difficult attack: urban buildings can be used as shelters and forts, and the protection force and the concealment are good; 2. the battle scale is small: the city street has limited width, is not beneficial to group battles, and is mainly involved in the battle scale of single soldier or team; 3. small arms are commonly used: the battle place is mainly semi-closed spaces such as rooms, and the building is arranged between the battle place and the battle place to block the battle place, so that the battle place is not beneficial to heavy weapons, and the battle weapon is mainly light weapons. Based on the characteristics of the three urban wars, in the traditional urban wars, because of the blockage of the building, the fighter usually needs to move to one side of the building opposite to the target to attack the target taking the building as a shelter, and the fighter is exposed in the threat of enemy firepower in such a fighting mode, so that casualties are caused. Most of the existing urban warfare weapons can only carry out positive attack and do not have the capability of attacking one side of the urban warfare weapons by bypassing buildings.

Disclosure of Invention

In view of the above, the invention provides an omnidirectional anti-slope missile with a speed reducer, which can realize omnidirectional striking on buildings and has the capability of accurately striking and suppressing a target in urban war.

The technical scheme adopted by the invention is as follows:

an omnidirectional anti-slope missile with a speed reducer comprises a guidance assembly, a missile loading control module, a warhead, an inclined spray pipe speed-increasing engine, an electric steering engine, the speed reducer, a flight engine, a tail wing assembly and a launching engine;

the guidance assembly, the missile loading control module, the warhead, the inclined spray pipe speed-increasing engine, the electric steering engine, the speed reducer, the flight engine, the empennage assembly and the launching engine are sequentially connected from head to tail to form a missile;

the launching engine provides initial power for launching the guided missile, the guided missile flies opposite to a target in a launching stage, and the flight engine provides power for the launching stage of the guided missile; after the missile flies to a preset position, the speed reducer works to enable the missile to enter a speed reduction stage; when the guidance assembly detects that the posture of the missile changes into a downward head, a mechanism from the speed reducer to the tail is thrown away; then the missile enters an attitude adjusting stage and an attacking stage, the inclined spray pipe speed-increasing engine provides power for accelerating the missile, and fuel gas acts on a rudder of an electric steering engine to adjust the head direction of the missile to be directed at a target; the missile control system comprises a guidance assembly, a missile-borne control module, an electric steering engine and a corresponding trajectory correction control instruction, wherein the guidance assembly resolves position and attitude information of a missile body in real time and transmits the position and attitude information to the missile-borne control module, the missile-borne control module is communicated with the electric steering engine, the corresponding trajectory correction control instruction is generated by combining with a missile flight time sequence and is transmitted to the electric steering engine, and the electric steering engine is used for executing actions according to the control instruction to enable the missile to fly along a planned trajectory until the missile hits a target.

Furthermore, the speed reducer comprises a connecting cylinder, a pressure spring, a speed reducing umbrella cabin shell, a push plate, a speed reducing umbrella, a connecting stud, a connecting cover and two sets of ignition devices;

the speed reducing umbrella cabin shell is a cylinder with one open end and one closed end, the closed end is fixedly connected with the connecting cylinder, the end face of the closed end and the inner wall of the connecting cylinder form a separated chemical chamber I, one set of ignition device is arranged on the connecting cylinder, and when certain pressure is reached in the separated chemical chamber I, the speed reducing umbrella cabin shell is separated from the connecting cylinder; one end of the pressure spring is fixed on the inner wall of the closed end, the other end of the pressure spring is fixed on the push plate, the speed reducing umbrella is fixed in the speed reducing umbrella cabin shell, the connecting cover is fixedly connected to the open end of the speed reducing umbrella cabin shell, the speed reducing umbrella is pressed between the push plate and the inner wall of the connecting cover, and the pressure spring is in a compressed state; the other set of ignition device is arranged on the connecting cover, a separation medicine chamber II is arranged in the connecting cover, and when certain pressure is reached in the separation medicine chamber II, the connecting cover is separated from the speed reducing umbrella cabin shell.

Furthermore, the speed reduction device comprises a connecting cylinder, a speed reduction plate cabin shell, a pressure spring, a rotating shaft, a speed reduction plate, a torsion spring, a push plate, a connecting cover and two sets of ignition devices;

the speed reduction plate cabin shell is a cylinder with one open end and one closed end, the closed end is fixedly connected with the connecting cylinder, the end face of the closed end and the inner wall of the connecting cylinder form a separated chemical chamber I, one set of ignition device is arranged on the connecting cylinder, and when certain pressure is reached in the separated chemical chamber I, the speed reduction plate cabin shell is separated from the connecting cylinder; one end of the pressure spring is fixed on the inner wall of the closed end, and the other end of the pressure spring is fixed on the push plate; the speed reducing plate is rotatably connected to the cylinder through the rotating shaft and attached to the outer circumferential surface of the cylinder, the torsion spring is sleeved on the rotating shaft, and meanwhile, the radial extension rod of the speed reducing plate extends into the speed reducing plate cabin shell to be clamped with the axial locking pin of the push plate so as to limit the rotation of the speed reducing plate; the connecting cover is fixedly connected to the open end of the speed reducing plate cabin shell, and the push plate is extruded to enable the pressure spring to be in a compressed state; the other set of ignition device is arranged on the connecting cover, a separation medicine chamber II is arranged in the connecting cover, and when certain pressure is reached in the separation medicine chamber II, the connecting cover is separated from the speed reduction plate cabin shell; under the action of the pressure spring, the radial extension rod of the speed reducing plate is separated from the axial locking pin of the push plate, and the speed reducing plate rotates outwards by 90 degrees along the rotating shaft under the action of the torsion spring.

Furthermore, the connecting cylinder is a cylinder with one open end and one closed end, a circular boss is arranged at the port of the open end, threads are arranged on the inner surface of the circular boss, a sawtooth cutting angle is arranged on the end face of the inner side of the circular boss, and the sawtooth cutting angle is broken under certain pressure.

Furthermore, a sawtooth cutting angle is arranged on the cavity of the separation medicine chamber II, and under certain pressure, the sawtooth cutting angle is broken to realize separation of the connecting cover and the connected parts.

Furthermore, the push plate is a structural member formed by connecting two circular plates into a whole through a connecting rod, and an axial locking pin is arranged on the outer surface of one circular plate.

Has the advantages that:

1. the missile flight process is divided into four stages, namely a launching stage, a deceleration stage, an attitude adjustment stage and an attack stage, the attitude and the flight track of the missile are adjusted under the coordination of mechanisms, so that the missile can bypass a building to strike a target, and the front side, the rear side, the left side, the right side and the top of the building can be struck from a launching point, so that the problem of striking the target covered by the building in urban warfare is well solved, and the missile flight process has the capability of realizing omnidirectional accurate striking on the building within 50-1000 meters;

secondly, the invention contains two sets of power systems of a flight engine and a speed-increasing engine, and the speed requirements of a launching and throwing section and an attack stage of the missile in the flight process are ensured through a multi-stage thrust scheme;

moreover, the speed reduction device is adopted for reducing the speed, so that the flying speed of the missile is rapidly reduced when the missile flies to the opposite side of the target position of the building, the missile is rapidly changed from the launching direction to the vertical direction, the overload requirement is reduced for the subsequent steering flight, and the hitting to the targets in all directions of the building is met; in addition, the invention realizes that the missile throws away the redundant weight at the rear part of the missile body in the process of deceleration, thereby reducing the difficulty for the subsequent steering flight of the missile;

finally, the invention adopts an actuating mechanism combining the speed-increasing engine and the electric steering engine, and the scheme can ensure that the electric steering engine generates control force by using aerodynamic force when the speed-increasing engine does not work, and generates control force by using gas generated by the operation of the speed-increasing engine when the flying speed of the missile is lower after the speed reduction, thereby ensuring the maneuverability of the missile under the low-speed condition.

2. The speed reducer comprises two times of separation, and the missile separated for the first time simultaneously throws off the redundant weight at the rear part of the missile body in the speed reducing process, so that the difficulty of subsequent steering flight of the missile is reduced.

Drawings

FIG. 1 is a schematic ballistic diagram of the present invention;

FIG. 2 is a flow chart of the operation of the present invention;

FIG. 3 is a schematic view of the overall structure of the present invention;

FIG. 4 is a schematic diagram of the projectile after it has been thrown off the deceleration device of the present invention;

FIG. 5 is a schematic diagram of the deceleration stage of the present invention using a parachute solution;

FIG. 6 is a schematic diagram of the structure of the deceleration stage of the present invention using the deceleration plate scheme;

FIG. 7 is a schematic view of a step-up engine;

FIG. 8 is a schematic view of the reduction gear of the parachute solution;

FIG. 9 is a schematic structural view of a reduction umbrella cabin shell section;

FIG. 10(a) is a schematic view showing a structure of a connection cap, and FIG. 10(b) is a sectional view of FIG. 10 (a);

FIG. 11 is a schematic view of the reduction gear of the reduction plate arrangement;

fig. 12(a) is a schematic view of a speed brake cabin shell section structure, and fig. 12(b) is a left side view of fig. 12 (a);

wherein, 1-a guidance assembly, 2-a missile-borne control module, 3-a warhead, 4-an inclined nozzle booster engine, 5-an electric steering engine, 6-a speed reducer, 7-a flight engine, 8-a tail wing assembly, 9-a launching engine, 10-a combustion chamber bottom, 11-an igniter I, 12-an engine shell, 13-a propellant, 14-a connecting cylinder, 15-an igniter II, 16-a sealing cover I, 17-a separation powder I, 18-a pressure spring I, 19-a speed reducing umbrella cabin shell, 20-a push plate I, 21-a screw, 22-a speed reducing umbrella, 23-a connecting stud, 24-a connecting cover, 25-a separation powder II, 26-a sealing cover II, 27-an igniter III and 28-a speed reducing plate cabin shell, 29-a pressure spring II, 30-a speed reducing plate and 31-a push plate II.

Detailed Description

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

The embodiment provides an omnidirectional anti-slope missile with a speed reducer, which takes a 40 mm rocket tube as a launching platform, and as shown in fig. 3, the omnidirectional anti-slope missile comprises a guidance assembly 1, a missile-borne control module 2, a warhead 3, an inclined nozzle speed-increasing engine 4, an electric steering engine 5, a speed reducer 6, a flight engine 7, a tail wing assembly 8 and a launching engine 9.

In the embodiment, the guidance component 1 adopts an inertial guidance system, consists of an inertial navigation device and a fuse and is arranged at the head of the missile. The inertial guidance device comprises an acceleration measuring device, an attitude measuring device and a position resolving device, wherein the acceleration measuring device can sense the acceleration of the missile projectile body; the attitude measuring device can sense the attitude and attitude change rate of the missile body; the position calculating device can calculate the position information of the missile body according to the acceleration and the attitude integral of the missile body. The guidance assembly 1 sends the motion information of the missile to the missile-borne control module 2.

The missile-borne control module 2 consists of a wireless loading and receiving module, a missile-borne computer and a missile-borne power supply. The wireless setting receiving module is used for receiving geomagnetic reference, target position information, altitude information, meteorological condition information and ephemeris data wirelessly transmitted by the ground simple fire control setter module before shooting, and information such as rocket tube shooting angle and shooting direction calculated by ground simple fire control. And the on-missile computer manages the platform working process, calculates according to the missile position information and the attitude information transmitted by the guidance component 1, plans the flight trajectory, generates a control instruction and sends the generated control instruction to the electric steering engine 5. The pop-up power source employs a thermal battery activated by launch overload for powering the pop-up electrical system.

Besides the embodiment of the method, an inertial guidance system is adopted, and satellite guidance, laser semi-active guidance, television guidance and infrared guidance can also be adopted. When other guidance systems are adopted, an attitude measurement element is required to be added into the missile-borne control module 2.

The warhead 3 is composed of a security mechanism, a detonating tube and a warhead body.

As shown in fig. 7, the oblique nozzle booster engine 4 includes a combustion chamber bottom 10, an igniter i 11, an engine case 12, and a propellant 13. The combustion chamber bottom 10 is connected with the engine shell 12 through threads, the open end of the engine shell 12 is closed, and a closed combustion chamber is formed by the combustion chamber bottom and the inner cavity of the engine shell 12. The propellant 13 is positioned in a combustion chamber formed by the combustion chamber bottom 10 and the inner cavity of the engine shell 12, and after the igniter I11 ignites the propellant, gas generated during combustion is sprayed out through four spray pipes on the engine shell, so that the speed of the posture adjusting stage and the attack stage of the missile is increased. The engine shell 12 is a cylindrical shell, and a propellant 13 is placed in the cavity; four inclined spray pipes are arranged on the outer circumference of the engine shell 12, the phases of the four inclined spray pipes are consistent with those of four rudder pieces of the electric steering engine 5, and nozzles of the inclined spray pipes face the four rudder pieces of the electric steering engine 5. When the inclined nozzle speed-increasing engine 4 works, the igniter I11 ignites the propellant 13, the propellant 13 burns in the combustion chamber and generates gas, the gas is sprayed out from the four inclined nozzles of the engine shell 12 and acts on the rudder of the electric steering engine 5, when the rudder of the electric steering engine 5 acts, a control force is generated to adjust the posture of a missile body, and meanwhile, the sprayed gas generates thrust to increase the speed of the missile.

As shown in figure 8, the speed reducing device 6 adopts a speed reducing umbrella scheme and comprises a connecting cylinder 14, an igniter II 15, a sealing cover I16, a separation powder I17, a pressure spring I18, a speed reducing umbrella cabin shell 19, a push plate I20, a screw 21, a speed reducing umbrella 22, a connecting stud 23, a connecting cover 24, a separation powder II 25, a sealing cover II 26 and an igniter III 27.

The connecting cylinder 14 is a cylinder with one open end and one closed end, the closed end is provided with a step surface, the outer circumference of the step end is a thread surface and is used for being connected with the electric steering engine 5, the closed end is provided with a separated medicine chamber I, and the separated medicine chamber I is communicated with the interior of the cylinder; the port of the open end is provided with a circular ring boss, the inner surface of the circular ring boss is provided with threads for connecting with the speed reducing umbrella cabin shell 19, the end surface of the inner side of the circular ring boss is provided with a sawtooth cutting angle, and the sawtooth cutting angle is broken under certain pressure and is called as a shearing key. The separation explosive I17 and the ignition tool II 15 are positioned in a separation explosive chamber on the end face of the connecting cylinder 14, and the sealing cover I16 is in threaded connection with the closed end of the connecting cylinder 14 to seal the separation explosive chamber I outwards.

As shown in fig. 9, the deceleration umbrella chamber housing 19 is a cylinder with one open end and one closed end, and the outer circumference of the closed end is provided with a cylindrical table with a thread surface on the outer wall for connecting with the connecting cylinder 14; four light holes are radially arranged on the outer circumference of the open end and are used for connecting with the connecting cover 24; the middle part is provided with four screw holes along the radial direction for fixing the umbrella rope of the deceleration umbrella 22. One end of a pressure spring I18 is fixed with the inner wall of the closed end of the speed reducing umbrella cabin shell 19, and the other end of the pressure spring I is fixed with a push plate I20. The deceleration umbrella 22 is folded and placed on the push plate I20, the umbrella rope is fixed on the deceleration umbrella cabin shell 19 through screws 21, and the screws 21 are matched with four screw holes of the deceleration umbrella cabin shell 19.

As shown in fig. 10(a), the connecting cover 24 is a stepped cylinder having a large diameter section and a small diameter section; the small-diameter section is provided with four cylindrical unthreaded holes along the radial direction, and when the connecting cover 24 is matched with the deceleration umbrella cabin shell 19, the four unthreaded holes are coaxial with the four unthreaded holes on the deceleration umbrella cabin shell 19; a cylindrical stepped hole is formed in the bottom of each hole of the small-diameter section, the inner wall of each stepped hole is a thread surface and is used for being fixed with the connecting stud 23, four cylindrical unthreaded holes are converged and communicated in the connecting cover 24, and the radial cross-sectional view at the cylindrical unthreaded holes is shown in fig. 10 (b); the connecting cover 24 is provided with a cylindrical separation explosive chamber II along the axial direction, the separation explosive chamber II is communicated with four cylindrical unthreaded holes, a separation explosive II 25 and a branch ignition tool III 27 are arranged in the separation explosive chamber II, and the rear part of the separation explosive chamber II is sealed by a sealing cover II 26; and a sawtooth cutting angle, called a shearing key, is arranged on the cavity of the separation medicine chamber II, and the sawtooth cutting angle is broken under certain pressure to realize the separation of the connecting cover and the connected parts.

The end face of the large-diameter section of the connecting cover 24 is provided with a threaded hole for connecting the flight engine 7.

The connecting stud 23 is a cylinder with three sections of different diameters, the diameter of the upper cylinder is the largest, and the connecting stud is tightly pressed on the speed reducing umbrella cabin shell 19 during matching; the middle part is a smooth surface cylinder and is used for restraining the axial movement of the speed reducing umbrella cabin shell 19 and the connecting cover 24; the lower part is a screw thread surface cylinder, the diameter of the screw thread surface cylinder is slightly smaller than that of the smooth surface cylinder in the middle part, and the screw thread surface cylinder is used for being matched with the inner wall of the step hole of the connecting cover 24, so that the speed reducing umbrella cabin shell 19 and the connecting cover 24 are fixed.

The operating principle of the speed reducing device 6 is as follows: when the missile is in a service state and does not enter a deceleration stage after being launched, the connecting cylinder 14 is connected with the end surface of the deceleration umbrella cabin shell 19; the connecting cover 24 is connected with the speed reducing umbrella cabin shell 19, the speed reducing umbrella 22 is pressed between the push plate I20 and the inner wall of the connecting cover 24, and the pressure spring I18 is in a compressed state. When the missile flies to a designated height and distance, the branch igniter III 27 ignites the separation gunpowder II 25, the pressure in a closed cavity formed by the lower end surface of the connecting stud 23, the sealing cover II 26 and the separation gunpowder chamber II of the connecting cover 24 is rapidly increased by the generated gas, the shearing key is sheared after the pressure exceeds the stress threshold of the shearing key, at the moment, the connecting stud 23 loses the fixation with the connecting cover 24, and the connecting stud is pushed away from the connecting cover 24 and the speed reducing parachute cabin shell 19 under the action of the gas pressure; as the connecting stud 23 is pushed out, the deceleration parachute bay housing 19 and the connecting cover 24 are not fixed; under the condition, a pressure spring I18 in a speed reducing umbrella cabin shell 19 pushes a push plate I20 and a speed reducing umbrella 22, and then a connecting cover 24 is pushed away from the speed reducing device 6, so that the front part and the rear part of the missile are separated; meanwhile, the brake parachute 22 is pushed out of the parachute bay casing 19, and the brake parachute 22 is opened under the action of air to decelerate the missile. After the projectile body decelerates, when the projectile body posture sensitive by an inertia device in the guidance assembly 1 meets the condition that the head of the projectile body faces downwards (if a guidance system other than inertia guidance is adopted, the projectile body posture is measured by a posture measuring element in the projectile loading control module 2), an ignition tool II 15 in the connecting cylinder 14 ignites the separation powder I17, the generated gas is gathered in a separation powder chamber I consisting of a sealing cover I16, the connecting cylinder 14 and the end face of a deceleration parachute cabin shell 19, meanwhile, the pressure in the cavity of the separation powder chamber I is rapidly increased, the shear key is sheared after the pressure exceeds the stress threshold value of the shear key of the connecting cylinder 14, and the deceleration parachute cabin shell 19 is connected with the shear key of the connecting cylinder 14 through threads, so that the deceleration parachute cabin shell 19 is separated from the connecting cylinder 14 after the shear key is sheared, and the projectile body can be thrown away from the deceleration part of the deceleration device 6.

The flight engine 8 is used for providing first-level acceleration for the missile after the missile body platform launches, and when precision launching is not required, the range can reach 1500 m.

The tail wing assembly 9 is arranged between a flight engine 8 and a launching engine 10 of the missile, consists of a tail rod and a tail wing, and is used for stabilizing the flight attitude of the missile body and providing the rotating speed of the missile body leaving a barrel.

The launching engine 10 is arranged at the tail of the missile and is used for launching the missile into a 40 mm rocket tube at a certain initial speed and direction. A 40 mm system projectile launching system may also be used as the launching system of the present invention, in place of the launch engine 10.

The overall working process of the embodiment is as follows:

when the simple fire control setter module is used for setting geomagnetic geographical reference information, target position information, meteorological condition information, ephemeris data, altitude information and firing angles and direction calculated by simple fire control to the missile during working, a shooter enters a position according to the instruction of a superior command system. After the operation is finished, the shooter loads the full-reserve missile into the rocket tube, places the rocket tube on the shoulder, adjusts the launching angle to a set range through the rocket tube sighting device, activates the guidance assembly 1 and finishes the initial alignment of the inertial navigation device. Then, a shooter pulls a trigger to ignite the launching engine 9, the launching engine 9 pushes the missile body to accelerate to a preset speed after being ignited, and the missile flies opposite to a target in a throwing stage, as shown in the figures 1 and 2; after the thermal battery is discharged from the blast hole for about 0.5s, the thermal battery works normally and stably; in the flight process, the flight engine 8 provides power for the launching stage of the missile, and the guidance component 1 resolves the motion states of the missile body such as real-time position, attitude and the like in real time; after the missile flies to a preset position, an igniter III 27 of the speed reducer 6 ignites a separation powder II 25, so that the missile is separated from a flight engine 7, a tail wing assembly 8 and a launching engine 9 which are arranged at the rear part of the missile body of the speed reducer 6, meanwhile, a deceleration parachute 22 is pushed out and opened, the missile is rapidly decelerated, and the missile enters a deceleration stage, as shown in figure 5; when the missile body is decelerated and the missile body is changed into a state that the head of the missile body is downward, the igniter II 15 in the connecting cylinder 14 in the speed reducing device 6 ignites the separation powder I17, the deceleration parachute cabin shell 19 is separated from the connecting cylinder 14 under the action of gas, the deceleration part of the speed reducing device 6 is thrown away, and the missile enters a posture adjustment stage in a state shown in figure 4. After entering the attitude adjustment stage, an igniter I11 of the inclined nozzle speed-increasing engine 4 ignites the propellant 13; after the propellant 13 is ignited, the generated gas acts on a rudder blade of the electric steering engine 5 to generate a control force so that the projectile body adjusts the posture to face a target direction; the gas also has the function of accelerating the missile. After the projectile body enters an attack stage, the guidance assembly 1 continues to work and continuously calculates the motion information of the projectile body; the missile computer generates a control instruction after receiving the spatial position information of the missile body and the attitude information output by the attitude measuring device; and the control command is transmitted to the electric steering engine 5 to control the projectile body to fly along the planned trajectory until the projectile body hits the target.

Another example of a deceleration scheme using the deceleration plate 30 is as follows:

since the speed reducer adopted by the speed reducer plate scheme and the speed reducer adopted by the speed reducer parachute scheme are consistent with the interfaces of the front part and the rear part of the projectile body, other parts of the projectile body of the speed reducer plate scheme are the same as the corresponding parts of the projectile body of the speed reducer parachute scheme, the difference is only in the structure of the speed reducer 6, and only the structure of the speed reducer 6 of the speed reducer plate scheme is described herein.

As shown in fig. 11, the reduction gear 6 includes a connecting cylinder 14, an igniter ii 15, a seal cover i 16, a separation powder i 17, a reduction gear compartment housing 28, a compression spring ii 29, a rotary shaft, a reduction gear 30, a thrust plate ii 31, a connecting stud 23, a connecting cover 24, a seal cover ii 26, an igniter iii 27, and a separation powder ii 25.

As shown in fig. 12(a), the speed-reduction board compartment casing 28 is a cylinder with one open end and one closed end, the closed end is fixedly connected with the connecting cylinder 14, and the outer circumference of the open end is provided with four light holes along the radial direction for connecting with the connecting cover 24; one end of a pressure spring II 29 is fixed with the inner wall of the closed end of the speed reducing plate cabin shell 28, and the other end of the pressure spring II is fixed with a push plate II 31. The push plate II 31 is a structural member formed by connecting two circular plates into a whole through a connecting rod, wherein four axial locking pins are uniformly distributed on the outer surface of one circular plate at intervals and are used for being inserted into through holes of radially extending rods on the speed reducing plate 30.

The number of the speed reducing plates 30 is four, each speed reducing plate is a quarter-cylinder thin-wall shell, and the inner wall of each speed reducing plate is attached to the outer wall of the middle part of the speed reducing plate cabin shell 28 in shape; the root of the speed reducing plate 30 is provided with a connecting arm, a through hole is arranged on the connecting arm, and the connecting arm is arranged on the speed reducing plate cabin shell 28 through a rotating shaft; the speed reducing plate 30 is provided with a radial extending rod which is perpendicular to the speed reducing plate 30, a through hole is formed in the radial extending rod, and when the speed reducing plate 30 is in a folded state, the axial locking pin on the push plate II 31 can be inserted into the through hole of the radial extending rod.

28 middle part diameters of speed reduction board cabin casing are less than both ends, four speed reduction boards 30 rotate through the pivot and connect at the middle part outer circumference, the laminating is at the periphery outward, fold condition, speed reduction board 30 surface and 14 surface parallel and level of connecting cylinder, all there is the torsional spring in the coupling department, the torsional spring suit is in the pivot, middle part coupling department is just to opening along the axial has the speed reduction board groove, this groove can guarantee that the speed reduction board linking arm passes and provides the rotation space when folding, the radial extension bar of speed reduction board 30 stretches into speed reduction board cabin casing 28 in with the axial stop pin block of push pedal II 31 simultaneously, restriction speed reduction board 30's rotation.

The structure of the connecting cylinder 14, the igniter II 15, the sealing cover I16, the separating powder I17, the connecting cover 24 and the connecting stud 23 is the same as that of the corresponding parts of the speed reducing umbrella scheme.

The operating principle of the speed reducing device 6 is as follows: when the missile is in a service state and does not enter a deceleration section after being launched, the connecting cylinder 14 is connected with the end face of the shell 28 of the speed reduction plate cabin; the connecting cover 24 is connected to the speed reduction panel compartment case 28; the compression spring II 29 is compressed through the push plate II 31; the speed reduction plate 30 is folded over the speed reduction plate compartment housing 28 and the axial locking pins of the push plate ii 31 are inserted into the radially projecting rods of the speed reduction plate 30. When the projectile flies to a designated height and distance, the branch ignition tool III 27 ignites the separation powder II 25, the generated gas enables the pressure in a closed cavity formed by the lower end face of the connecting stud 23, the sealing cover II 26 and the separation powder chamber II of the connecting cover 24 to sharply rise, the shearing key is sheared after the pressure exceeds the stress threshold value of the shearing key, at the moment, the connecting stud 23 loses the fixation with the connecting cover 24, and the connecting stud is pushed away from the speed reduction board cabin shell 28 and the connecting cover 24 under the action of the gas pressure; as the connecting stud 23 is pushed out, the speed bump compartment housing 28 and the connecting cover 24 lose their fixation; under the condition, a pressure spring II 29 in the shell 28 of the speed reducing plate cabin pushes a push plate II 31, so that the connecting cover 24 is pushed away from the speed reducing device 6, and the front part and the rear part of the missile body are separated; meanwhile, the axial locking pin of the push plate II 31 is pulled out from the radial extending rod of the speed reducing plate 30, the speed reducing plate 30 is unlocked, and the speed reducing plate is unfolded in place under the action of the torsional spring force, so that the resistance area of the projectile body is increased, and the projectile body is decelerated, as shown in fig. 6. After the projectile decelerates, when the projectile attitude sensitive to the inertia device in the guidance assembly 1 meets the requirement that the head of the projectile faces downwards (if guidance systems other than inertia guidance are adopted, the projectile attitude is measured by an attitude measuring element in the projectile loading control module 2), the igniter II 15 in the connecting cylinder 14 ignites the separation powder I17, the generated gas is gathered in a closed cavity formed by the sealing cover I16, the connecting cylinder 14 and the end face of the speed reducing plate cabin shell 28, the pressure in the cavity is rapidly increased, the pressure exceeds the stress threshold value of the shear key of the connecting cylinder 14, then the shear key is sheared, as the speed reducing plate cabin shell 28 is connected with the shear key of the connecting cylinder 14 through threads, after the shear key is sheared, the speed reducing plate cabin shell 28 is separated from the connecting cylinder 14, and the projectile is thrown away from the deceleration part of the deceleration device 6.

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.