An omnidirectional reverse inclined surface missile with a deceleration device

Abstract

The present invention provides an omnidirectional anti-inclined surface missile with a deceleration device, comprising a guidance component, an on-board control module, a warhead, an inclined nozzle speed-increasing engine, an electric servo, a deceleration device, a flight engine, a tail assembly and a launch engine; the guidance component, the on-board control module, the warhead, the inclined nozzle speed-increasing engine, the electric servo, the deceleration device, the flight engine, the tail assembly and the launch engine are sequentially connected from head to tail to form the missile; the electric servo executes actions according to control instructions to make the missile fly along the planned ballistic trajectory until it hits the target. The present invention can achieve omnidirectional strikes on buildings and has the ability to precisely strike and suppress targets in urban warfare.

Description

Technical Field

[0001] The present invention relates to the technical field of guided ammunition, and particularly relates to an omnidirectional anti-slope missile with a deceleration device. Background Art

[0002] Urban warfare is one of the main forms of modern warfare. In the city, the streets and alleys are crisscrossed, and the buildings are tall and dense. Such combat conditions make urban warfare have the following characteristics: 1. Difficult to attack and easy to defend: The urban buildings can be used as shelters and fortresses, with good protection and concealment; 2. Small combat scale: The width of urban streets and alleys is limited, which is not conducive to group combat, and individual soldiers or teams are the main combat scale; 3. Widespread use of light weapons: The combat positions are mainly semi-enclosed spaces such as rooms, and there are many buildings blocking between positions, which is not conducive to the use of heavy weapons, and the combat weapons are mainly light weapons. Based on the above three characteristics of urban warfare, in traditional urban warfare, due to the obstruction of buildings, combatants often need to move to the side of the building directly opposite the target to attack the target taking the building as a shelter. Such a combat method will expose the combatants to the threat of enemy fire, resulting in casualties. Among the existing urban warfare weapons, most can only conduct frontal attacks and do not have the ability to bypass buildings and strike the side of them. Summary of the Invention

[0003] In view of this, the present invention provides an omnidirectional anti-slope missile with a deceleration device, which can achieve omnidirectional strikes on buildings and has the ability to accurately strike and suppress targets in urban warfare.

[0004] The technical solution adopted by the present invention is as follows:

[0005] An omnidirectional anti-slope missile with a deceleration device, the missile includes a guidance component, an on-board control module, a warhead, an inclined nozzle speed-increasing engine, an electric servo, a deceleration device, a flight engine, a tail fin assembly and a launch engine;

[0006] The guidance component, the on-board control module, the warhead, the inclined nozzle speed-increasing engine, the electric servo, the deceleration device, the flight engine, the tail fin assembly and the launch engine are sequentially connected from head to tail to form the missile;

[0007] The launch engine provides the initial power for the missile to be ejected. The missile flies towards the opposite side of the target during the delivery stage, and the flight engine provides power for the delivery stage of the missile. When the missile flies to a predetermined position, the deceleration device operates to make the missile enter the deceleration stage. When the guidance component detects that the missile's attitude changes to head-down, the mechanism from the deceleration device to the tail is jettisoned. After that, the missile enters the attitude adjustment stage and the attack stage. The obliquely arranged nozzle speed-up engine provides power for the missile to accelerate, and the gas acts on the rudder vane of the electric actuator to adjust the direction of the missile's head to point towards the target. The guidance component calculates the position and attitude information of the missile body in real time, and transmits the position and attitude information to the on-board control module. The on-board control module communicates with the electric actuator, generates corresponding trajectory correction control commands according to the missile flight timing sequence and sends them to the electric actuator. The electric actuator is used to execute actions according to the control commands to make the missile fly along the planned trajectory until it hits the target.

[0008] Further, the deceleration device includes a connecting cylinder, a compression spring, a deceleration parachute cabin housing, a push plate, a deceleration parachute, a connecting stud, a connecting cover, and two sets of ignition devices;

[0009] The deceleration parachute cabin housing is a cylinder with one end open and one end closed. The closed end is fixedly connected to the connecting cylinder, and the end face of the closed end and the inner wall of the connecting cylinder form a separation chamber I. One set of ignition devices is installed on the connecting cylinder. When the pressure in the separation chamber I reaches a certain value, the deceleration parachute cabin housing separates from the connecting cylinder. One end of the compression spring is fixed to the inner wall of the closed end, and the other end is fixed to the push plate. The deceleration parachute is fixed inside the deceleration parachute cabin housing. The connecting cover is fixedly connected to the open end of the deceleration parachute cabin housing, pressing the deceleration parachute between the push plate and the inner wall of the connecting cover, and the compression spring is in a compressed state. The other set of ignition devices is arranged on the connecting cover, and a separation chamber II is provided inside the connecting cover. When the pressure in the separation chamber II reaches a certain value, the connecting cover separates from the deceleration parachute cabin housing.

[0010] Further, the deceleration device includes a connecting cylinder, a deceleration plate cabin housing, a compression spring, a rotating shaft, a deceleration plate, a torsion spring, a push plate, a connecting cover, and two sets of ignition devices;

[0011] The spoiler compartment housing is a cylinder open at one end and closed at the other end. The closed end is fixedly connected to the connecting cylinder, and a separation chamber I is formed between the end face of the closed end and the inner wall of the connecting cylinder. One set of ignition devices is installed on the connecting cylinder. When a certain pressure is reached in the separation chamber I, the spoiler compartment housing is separated from the connecting cylinder. One end of the compression spring is fixed to the inner wall of the closed end, and the other end is fixed to the push plate. The spoiler is rotatably connected to the cylinder through a rotating shaft, fits on the outer circumferential surface of the cylinder, and a torsion spring is sleeved on the rotating shaft. At the same time, the radially extending rod of the spoiler extends into the spoiler compartment housing and engages with the axial locking pin of the push plate to limit the rotation of the spoiler. The connecting cover is fixedly connected to the open end of the spoiler compartment housing, squeezing the push plate to keep the compression spring in a compressed state. Another set of ignition devices is arranged on the connecting cover, and a separation chamber II is provided inside the connecting cover. When a certain pressure is reached in the separation chamber II, the connecting cover is separated from the spoiler compartment housing. Under the action of the compression spring, the radially extending rod of the spoiler is separated from the axial locking pin of the push plate, and the spoiler rotates outward by 90° along the rotating shaft under the action of the torsion spring.

[0012] Further, the connecting cylinder is a cylinder open at one end and closed at the other end. A circular ring boss is provided at the port of the open end. The inner surface of the circular ring boss is provided with threads, and a serrated cut angle is provided on the inner end face of the circular ring boss. At a certain pressure, the serrated cut angle breaks.

[0013] Further, a serrated cut angle is provided on the cavity of the separation chamber II. At a certain pressure, the serrated cut angle breaks to realize the separation of the connecting cover from the connected component.

[0014] Further, the push plate is a structural member in which two circular plates are connected into one body by a connecting rod, and an axial locking pin is provided on the outer surface of one of the circular plates.

[0015] Advantageous effects:

[0016] 1. The flight process of the missile of the present invention is divided into four stages: the delivery stage, the deceleration stage, the attitude adjustment stage, and the attack stage. With the cooperation of each mechanism, the missile attitude and flight trajectory are adjusted, so as to bypass buildings and strike targets. It can strike the front side, rear side, left side, right side, and top of buildings from the launch point, which better solves the problem of striking targets protected by buildings in urban warfare and has the ability to achieve omnidirectional and precise strikes on buildings within 50 meters to 1000 meters.

[0017] Secondly, the present invention contains two sets of power systems, namely a flight engine and a speed increasing engine, and ensures the speed requirements of the missile during the launch and delivery section and the attack stage of the flight process through a multi-stage thrust scheme.

[0018] Furthermore, a deceleration device is used for deceleration, so that the flight speed of the missile rapidly decreases when it flies to the opposite side of the building target azimuth. Then, the missile quickly changes from the launch direction to vertically downward, reducing the overload requirement for subsequent turning flight to meet the strike on targets in all directions of the building. Moreover, the present invention realizes the simultaneous throwing off of the redundant weight at the rear of the missile body during deceleration, reducing the difficulty of subsequent turning flight of the missile.

[0019] Finally, the present invention adopts an actuator combining an acceleration engine and an electric servo. This scheme enables the electric servo to generate control force using aerodynamic force when the acceleration engine is not working, and to generate control force using the gas generated by the working of the acceleration engine when the flight speed of the missile is relatively low after deceleration, ensuring the maneuverability of the missile under low-speed conditions.

[0020] 2. The deceleration device of the present invention includes two separations. During the first separation, the missile simultaneously throws off the redundant weight at the rear of the missile body during deceleration, reducing the difficulty of subsequent turning flight of the missile. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is the ballistic schematic diagram of the present invention;

[0022] Figure 2 is the working flow chart of the present invention;

[0023] Figure 3 is the overall structure schematic diagram of the present invention;

[0024] Figure 4 is the structure schematic diagram of the missile body after separating from the deceleration device of the present invention;

[0025] Figure 5 is the structure schematic diagram of the deceleration stage of the present invention adopting the deceleration parachute scheme;

[0026] Figure 6 is the structure schematic diagram of the deceleration stage of the present invention adopting the deceleration plate scheme;

[0027] Figure 7 is the structure schematic diagram of the acceleration engine;

[0028] Figure 8 is the structure schematic diagram of the deceleration device of the deceleration parachute scheme;

[0029] Figure 9 is the structure schematic diagram of the deceleration parachute cabin shell section;

[0030] Figure 10(a) is the structure schematic diagram of the connecting cover, and Figure 10(b) is the cross-sectional view of Figure 10(a);

[0031] Figure 11 is the structure schematic diagram of the deceleration device of the deceleration plate scheme;

[0032] Figure 12(a) is a schematic structural diagram of the speed brake compartment housing section, and Figure 12(b) is a left view of Figure 12(a);

[0033] Among them, 1 - guidance component, 2 - on-board control module, 3 - warhead, 4 - inclined nozzle speed-increasing engine, 5 - electric actuator, 6 - deceleration device, 7 - flight engine, 8 - tail assembly, 9 - launch engine, 10 - bottom of combustion chamber, 11 - igniter I, 12 - engine housing, 13 - propellant, 14 - connecting cylinder, 15 - igniter II, 16 - sealing cover I, 17 - separation powder I, 18 - compression spring I, 19 - deceleration parachute compartment housing, 20 - push plate I, 21 - screw, 22 - deceleration parachute, 23 - connecting stud, 24 - connecting cover, 25 - separation powder II, 26 - sealing cover II, 27 - igniter III, 28 - speed brake compartment housing, 29 - compression spring II, 30 - speed brake, 31 - push plate II. Specific implementation mode

[0034] The present invention will be described in detail below with reference to the accompanying drawings and by way of examples.

[0035] This embodiment provides an omnidirectional anti-inclined surface missile with a deceleration device, using a 40-mm rocket launcher as a launch platform. As Figure 3 shown, the omnidirectional anti-inclined surface missile includes a guidance component 1, an on-board control module 2, a warhead 3, an inclined nozzle speed-increasing engine 4, an electric actuator 5, a deceleration device 6, a flight engine 7, a tail assembly 8 and a launch engine 9.

[0036] In this embodiment, the guidance component 1 adopts an inertial guidance system, which is composed of inertial navigation devices and fuses and is installed at the head of the missile. The inertial navigation devices include an acceleration measurement device, an attitude measurement device and a position calculation device. The acceleration measurement device can sense the acceleration of the missile body movement; the attitude measurement device can sense the attitude and attitude change rate of the missile body movement; the position calculation device can calculate the position information of the missile body according to the integration of the missile body acceleration and attitude. The guidance component 1 sends the movement information of the missile to the on-board control module 2.

[0037] The on-board control module 2 is composed of a wireless setting receiving module, an on-board computer and an on-board power supply. Among them, the wireless setting receiving module is used to receive the geomagnetic reference, target position information, altitude information, meteorological condition information and ephemeris data wirelessly transmitted by the ground simple fire control setting device module before shooting, as well as information such as the rocket launcher elevation angle and firing direction calculated by the ground simple fire control. The on-board computer manages the platform working process, and performs calculations according to the missile position information and attitude information transmitted by the guidance component 1, plans the flight trajectory, generates control instructions, and sends the generated control instructions to the electric actuator 5. The on-board power supply uses a thermal battery, which is activated by the launch overload and is used to supply power to the on-board electrical system.

[0038] In addition to the inertial guidance system used in the embodiments, satellite guidance, laser semi-active guidance, television guidance, and infrared guidance can also be used. When other guidance systems are adopted, attitude measurement elements need to be added to the onboard control module 2.

[0039] The warhead 3 is composed of a security mechanism, detonator tubes, and the warhead body.

[0040] As Figure 7 shown, the inclined nozzle speed-increasing engine 4 includes a combustion chamber bottom 10, igniter I 11, an engine housing 12, and a propellant 13. The combustion chamber bottom 10 is threadedly connected to the engine housing 12 to close the open end of the engine housing 12, and together with the inner cavity of the engine housing 12, it forms a closed combustion chamber. The propellant 13 is located in the combustion chamber formed by the combustion chamber bottom 10 and the inner cavity of the engine housing 12. When igniter I 11 ignites it, the gas generated during its combustion is ejected through four nozzles on the engine housing, increasing the speed during the attitude adjustment stage and the attack stage of the missile. The engine housing 12 is a cylindrical housing, and the cavity is used to place the propellant 13; four inclined nozzles are provided on the outer circumference of the engine housing 12, and the layout of these four inclined nozzles is in phase with the four rudder blades of the electric actuator 5, and the nozzles of the inclined nozzles face the four rudder blades of the electric actuator 5. When the inclined nozzle speed-increasing engine 4 operates, igniter I 11 ignites the propellant 13, the propellant 13 burns in the combustion chamber and generates gas, and the gas is ejected from the four inclined nozzles of the engine housing 12. This gas acts on the rudder blades of the electric actuator 5. When the rudder blades of the electric actuator 5 move, a control force will be generated to adjust the attitude of the missile body. At the same time, the ejected gas generates thrust to increase the speed of the missile.

[0041] As Figure 8 shown, the deceleration device 6 adopts a deceleration parachute scheme, including a connecting cylinder 14, igniter II 15, sealing cover I 16, separating powder I 17, compression spring I 18, deceleration parachute cabin housing 19, push plate I 20, screw 21, deceleration parachute 22, connecting stud 23, connecting cover 24, separating powder II 25, sealing cover II 26, and igniter III 27.

[0042] The connecting cylinder 14 is a cylinder with one open end and one closed end. The closed end has a stepped surface, and the outer circumference of the stepped end is a threaded surface for connecting to the electric actuator 5. A separating powder chamber I is provided at the closed end, and the separating powder chamber I is communicated with the inside of the cylinder; a circular ring boss is provided at the port of the open end, and the inner surface of the circular ring boss is provided with threads for connecting to the deceleration parachute cabin housing 19. A serrated cut angle is provided on the inner end face of the circular ring boss. Under a certain pressure, the serrated cut angle breaks, which is called a shear key. The separating powder I 17 and igniter II 15 are located in the separating powder chamber at the end face of the connecting cylinder 14, and the sealing cover I 16 is threadedly connected to the closed end of the connecting cylinder 14 to seal the separating powder chamber I to the outside.

[0043] As Figure 9 shown, the deceleration parachute cabin housing 19 is a cylinder with one end open and one end closed. The outer circumference of the closed end has a cylindrical platform with a threaded outer wall for connecting to the connecting cylinder 14. Four light holes are provided along the radial direction on the outer circumference of the open end for connecting to the connecting cover 24. Four screw holes are provided along the radial direction in the middle for fixing the suspension lines of the deceleration parachute 22. One end of the compression spring I 18 is fixed to the inner wall of the closed end of the deceleration parachute cabin housing 19, and the other end is fixed to the push plate I 20. After the deceleration parachute 22 is folded, it is placed on the push plate I 20, and its suspension lines are fixed to the deceleration parachute cabin housing 19 by screws 21, and the screws 21 cooperate with the four screw holes of the deceleration parachute cabin housing 19.

[0044] As shown in Fig. 10(a), the connecting cover 24 is a cylinder with a step. It has a large-diameter section and a small-diameter section. Four cylindrical light holes are provided along the radial direction in the small-diameter section. When the connecting cover 24 cooperates with the deceleration parachute cabin housing 19, these four light holes are coaxial with the four light holes on the deceleration parachute cabin housing 19. There is a cylindrical step hole at the bottom of each hole in the small-diameter section, and the inner wall of the step hole is a threaded surface for fixing to the connecting stud 23. The four cylindrical light holes communicate with each other inside the connecting cover 24, and the radial sectional view at the cylindrical light holes is shown in Fig. 10(b). The connecting cover 24 is provided with a cylindrical separation chamber II along the axial direction, and the separation chamber II communicates with the four cylindrical light holes. The separation powder II 25 and the sub-igniter III 27 are placed in the separation chamber II, and the rear part of the separation chamber II is sealed by the sealing cover II 26. The cavity of the separation chamber II is provided with a serrated cut angle, which is called a shear key. At a certain pressure, the serrated cut angle breaks to realize the separation of the connecting cover from the connected components.

[0045] A threaded hole is provided on the end face of the large-diameter section of the connecting cover 24 for connecting to the flight engine 7.

[0046] The connecting stud 23 is a cylinder with three unequal diameters. The upper cylinder has the largest diameter and is pressed against the deceleration parachute cabin housing 19 during cooperation. The middle part is a smooth cylinder for restricting the axial movement of the deceleration parachute cabin housing 19 and the connecting cover 24. The lower part is a cylinder with a threaded surface, and its diameter is slightly smaller than that of the smooth cylinder in the middle. It is used to cooperate with the inner wall of the step hole of the connecting cover 24 to fix the deceleration parachute cabin housing 19 and the connecting cover 24.

[0047] The working principle of the deceleration device 6 is as follows: When the missile is in the service state and has not entered the deceleration stage after launch, the connecting cylinder 14 is connected to the end face of the deceleration parachute cabin housing 19; the connecting cover 24 is connected to the deceleration parachute cabin housing 19, and the deceleration parachute 22 is pressed between the first push plate 20 and the inner wall of the connecting cover 24, and the first compression spring 18 is in a compressed state. When the missile flies to a specified height and distance, the third igniter 27 ignites the second separation gunpowder 25, and the generated gas causes the pressure in the sealed cavity formed by the lower end face of the connecting stud 23, the second sealing cover 26, and the second separation chamber of the connecting cover 24 to rise sharply. After the pressure exceeds the stress threshold of the shear key, the shear key is cut off. At this time, the connecting stud 23 loses its fixation to the connecting cover 24 and is pushed away from the connecting cover 24 and the deceleration parachute cabin housing 19 under the action of the gas pressure; since the connecting stud 23 is pushed out, the deceleration parachute cabin housing 19 loses its fixation to the connecting cover 24; under this condition, the first compression spring 18 in the deceleration parachute cabin housing 19 pushes the first push plate 20 and the deceleration parachute 22, and then pushes the connecting cover 24 away from the deceleration device 6, realizing the separation of the front and rear parts of the missile; at the same time, the deceleration parachute 22 is pushed out of the deceleration parachute cabin housing 19, and the deceleration parachute 22 is opened under the action of the air to decelerate the missile. After the missile body decelerates, when the attitude of the missile body sensed by the inertial device in the guidance component 1 satisfies that the head of the missile body faces downward (if other guidance systems except inertial guidance are adopted, the attitude of the missile body is measured by the attitude measurement element in the missile-borne control module 2), the igniter II 15 in the connecting cylinder 14 ignites the separation gunpowder I 17, and the generated gas accumulates in the first separation chamber formed by the first sealing cover 16, the connecting cylinder 14, and the end face of the deceleration parachute cabin housing 19, and at the same time causes the pressure in the cavity of the first separation chamber to rise sharply. After the pressure exceeds the stress threshold of the shear key of the connecting cylinder 14, the shear key is cut off. Since the deceleration parachute cabin housing 19 is connected to the shear key of the connecting cylinder 14 by a thread, after the shear key is cut off, the deceleration parachute cabin housing 19 is separated from the connecting cylinder 14, realizing the throwing away of the deceleration part of the deceleration device 6 by the missile.

[0048] The flight engine 7 is used to provide the first-stage speed increase for the missile after the missile body platform is launched. When precision launch is not required, the range can reach 1500 m.

[0049] The tail fin assembly 8 is arranged between the flight engine 7 and the launch engine 9 of the missile and is composed of a tail rod and tail fins, and is used to stabilize the flight attitude of the missile body and provide the rotation speed when leaving the tube.

[0050] The launch engine 9 is arranged at the tail of the missile and is used to launch the missile out of the 40-mm rocket launcher at a certain initial velocity and direction. The launch system of the 40-mm standard rocket can also be used as the launch system of the present invention to replace the launch engine 9.

[0051] The overall working process of this embodiment is as follows:

[0052] During operation, after the shooter enters the position, according to the instructions of the superior command system, the shooter uses the simple fire control setting device module to set the geomagnetic and geographic reference information, target position information, meteorological condition information, ephemeris data, altitude information, and the elevation angle and azimuth calculated by the simple fire control on the missile. After completing the above operations, the shooter loads the fully equipped ammunition into the rocket launcher, places the rocket launcher on the shoulder, adjusts the launch angle to the set range through the rocket launcher sighting device, and activates the guidance component 1 to complete the initial alignment of the inertial navigation device. Then the shooter pulls the trigger to ignite the launch engine 9. After the launch engine 9 is ignited, it pushes the missile body to accelerate to the predetermined speed, and the missile enters the delivery stage and flies towards the opposite side of the target, as Figure 1 , Figure 2 shown; about 0.5 s after leaving the muzzle, the thermal battery works stably and normally; during the flight, the flight engine 8 provides power for the delivery stage of the missile, and the guidance component 1 calculates the real-time position, attitude and other motion states of the missile body in real time; when the missile flies to the predetermined position, the igniter Ⅲ 27 of the deceleration device 6 ignites the separation charge Ⅱ 25, so that the missile separates from the flight engine 7, the tail fin assembly 8 and the launch engine 9 at the rear of the missile body starting from the deceleration device 6. At the same time, the deceleration parachute 22 is pushed out and opened, and the missile quickly decelerates, and the missile enters the deceleration stage, as Figure 5 shown; when the attitude of the missile body becomes head-down after deceleration, the igniter Ⅱ 15 in the connecting cylinder 14 of the deceleration device 6 ignites the separation charge Ⅰ 17. Under the action of the gas, the deceleration parachute cabin housing 19 separates from the connecting cylinder 14, realizing the throwing away of the deceleration part of the deceleration device 6, and the missile enters the attitude adjustment stage in the state as Figure 4 shown. After entering the attitude adjustment stage, the igniter Ⅰ 11 of the inclined nozzle speed increasing engine 4 ignites the propellant 13; after the propellant 13 is ignited, the gas generated by it acts on the rudder vane of the electric actuator 5, generating a control force to adjust the attitude of the missile body to the direction towards the target; this gas also has the effect of accelerating the missile. After the missile body enters the attack stage, the guidance component 1 continues to work, continuously calculating the motion information of the missile body; after the on-board computer receives the spatial position information of the missile body and the attitude information output by the attitude measuring device, it generates a control command; the control command is transmitted to the electric actuator 5 to control the missile body to fly along the planned trajectory until it hits the target.

[0053] Another embodiment using the deceleration plate 30 as the deceleration scheme is as follows:

[0054] Since the interfaces of the deceleration devices used in the deceleration plate scheme and the deceleration parachute scheme for the front and rear parts of the missile body are the same, the other components of the missile body in the deceleration plate scheme are the same as the corresponding components of the missile body in the deceleration parachute scheme. The difference lies only in the structure of the deceleration device 6. Here, only the structure of the deceleration device 6 in the deceleration plate scheme is introduced.

[0055] As Figure 11As shown, the deceleration device 6 includes a connecting cylinder 14, an igniter II 15, a sealing cover I 16, a separating powder I 17, a deceleration plate cabin housing 28, a compression spring II 29, a rotating shaft, a deceleration plate 30, a push plate II 31, a connecting stud 23, a connecting cover 24, a sealing cover II 26, an igniter III 27, and a separating powder II 25.

[0056] As shown in Fig. 12(a), the deceleration plate cabin housing 28 is a cylinder with one end open and one end closed. The closed end is fixedly connected to the connecting cylinder 14. There are four light holes along the radial direction on the outer circumference of the open end for connecting with the connecting cover 24. One end of the compression spring II 29 is fixed to the inner wall of the closed end of the deceleration plate cabin housing 28, and the other end is fixed to the push plate II 31. The push plate II 31 is a structural member formed by connecting two circular plates with a connecting rod. Four axial locking pins are evenly distributed at intervals on the outer surface of one of the circular plates, and the locking pins are used to insert into the through holes of the radially protruding rods on the deceleration plate 30.

[0057] There are four deceleration plates 30 in total. Each deceleration plate is in the shape of a quarter-cylindrical thin-walled shell, and its inner wall fits the shape of the outer wall in the middle of the deceleration plate cabin housing 28. The root of the deceleration plate 30 has a connecting arm with a through hole, and it is installed on the deceleration plate cabin housing 28 through a rotating shaft. The deceleration plate 30 is provided with a radially protruding rod perpendicular to the deceleration plate 30, and there is a through hole on the radially protruding rod. When the deceleration plate 30 is in the folded state, the axial locking pins on the push plate II 31 can be inserted into the through holes of the radially protruding rod.

[0058] The diameter in the middle of the deceleration plate cabin housing 28 is smaller than that at both ends. The four deceleration plates 30 are rotationally connected to the outer circumference in the middle through a rotating shaft and fit on the outer circumferential surface. In the folded state, the outer surface of the deceleration plate 30 is flush with the outer surface of the connecting cylinder 14. There are torsion springs at the shaft joints, and the torsion springs are sleeved on the rotating shaft. There is a deceleration plate groove opened axially and facing each other at the middle shaft joint. This groove can ensure that the connecting arm of the deceleration plate passes through and provides a rotating space during folding. At the same time, the radially protruding rod of the deceleration plate 30 extends into the deceleration plate cabin housing 28 and engages with the axial locking pins of the push plate II 31 to limit the rotation of the deceleration plate 30.

[0059] The structures of the connecting cylinder 14, the igniter II 15, the sealing cover I 16, the separating powder I 17, the connecting cover 24, and the connecting stud 23 are the same as those of the corresponding components in the deceleration parachute solution.

[0060] The working principle of the deceleration device 6 is as follows: When the missile is in the service state and has not entered the deceleration section after launch, the connecting cylinder 14 is connected to the end face of the deceleration plate cabin housing 28; the connecting cover 24 is connected to the deceleration plate cabin housing 28; the compression spring II 29 is compressed by the push plate II 31; the deceleration plate 30 is folded on the deceleration plate cabin housing 28, and the axial locking pin of the push plate II 31 is inserted into the radially protruding rod of the deceleration plate 30. When the missile body flies to the specified height and distance, the sub-igniter III 27 ignites the separation gunpowder II 25, and the gas generated by it causes the pressure in the closed cavity formed by the lower end face of the connecting stud 23, the sealing cover II 26 and the separation chamber II of the connecting cover 24 to rise sharply. After the pressure exceeds the stress threshold of the shear key, the shear key is cut off. At this time, the connecting stud 23 loses its fixation with the connecting cover 24 and is pushed away from the deceleration plate cabin housing 28 and the connecting cover 24 under the action of the gas pressure; since the connecting stud 23 is pushed out, the deceleration plate cabin housing 28 and the connecting cover 24 lose their fixation; under this condition, the compression spring II 29 in the deceleration plate cabin housing 28 pushes the push plate II 31, and then pushes the connecting cover 24 away from the deceleration device 6, realizing the separation of the front and rear parts of the missile body; at the same time, the axial locking pin of the push plate II 31 is withdrawn from the radially protruding rod of the deceleration plate 30, and the deceleration plate 30 loses its lock and unfolds in place under the action of the torsion spring force, increasing the resistance area of the missile body and decelerating the missile body, as Figure 6 shown. After the missile body decelerates, when the attitude of the missile body sensed by the inertial device in the guidance component 1 satisfies that the head of the missile body faces downward (if other guidance systems except inertial guidance are adopted, the attitude of the missile body is measured by the attitude measurement element in the missile-borne control module 2), the igniter II 15 in the connecting cylinder 14 ignites the separation gunpowder I 17, and the gas generated by it accumulates in the closed cavity formed by the sealing cover I 16, the connecting cylinder 14 and the end face of the deceleration plate cabin housing 28, and at the same time causes the pressure in the cavity to rise sharply. After the pressure exceeds the stress threshold of the shear key of the connecting cylinder 14, the shear key is cut off. Since the deceleration plate cabin housing 28 is connected to the shear key of the connecting cylinder 14 by a thread, after the shear key is cut off, the deceleration plate cabin housing 28 is separated from the connecting cylinder 14, realizing the throwing away of the deceleration part of the deceleration device 6 by the missile body.

[0061] In summary, the above is only a preferred embodiment of the present invention and is not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An omnidirectional reverse slope missile with a deceleration device, characterized in that The missile includes a guidance component, an on-board control module, a warhead, an inclined nozzle speed-up engine, an electric actuator, a deceleration device, a flight engine, a tail assembly, and a launch engine; The guidance component, on-board control module, warhead, inclined nozzle speed-up engine, electric actuator, deceleration device, flight engine, tail assembly, and launch engine are sequentially connected from head to tail to form the missile; The launch engine provides initial power for the missile to be ejected. The missile flies towards the opposite side of the target when entering the delivery stage, and the flight engine provides power for the delivery stage of the missile. When the missile flies to a predetermined position, the deceleration device operates to make the missile enter the deceleration stage. When the guidance component detects that the attitude of the missile becomes head-down, the mechanism from the deceleration device to the tail is jettisoned. Then the missile enters the attitude adjustment stage and the attack stage. The inclined nozzle speed-up engine provides power for the missile to accelerate, and the gas acts on the rudder vane of the electric actuator to adjust the head direction of the missile to point to the target. The guidance component calculates the position and attitude information of the missile body in real time, and transmits the position and attitude information to the on-board control module. The on-board control module communicates with the electric actuator, generates corresponding trajectory correction control commands according to the missile flight time sequence and sends them to the electric actuator. The electric actuator is used to execute actions according to the control commands to make the missile fly along the planned ballistic trajectory until it hits the target.

2. The omnidirectional reverse inclined plane missile with a deceleration device according to claim 1, characterized in that The deceleration device includes a connecting cylinder, a compression spring, a deceleration parachute cabin housing, a push plate, a deceleration parachute, a connecting stud, a connecting cover, and two sets of ignition devices; The deceleration parachute cabin housing is a cylinder with one end open and one end closed. The closed end is fixedly connected to the connecting cylinder, and the end face of the closed end and the inner wall of the connecting cylinder form a separation charge chamber I. One set of ignition devices is installed on the connecting cylinder. When the pressure in the separation charge chamber I reaches a certain value, the deceleration parachute cabin housing is separated from the connecting cylinder. One end of the compression spring is fixed on the inner wall of the closed end, and the other end is fixed on the push plate. The deceleration parachute is fixed in the deceleration parachute cabin housing. The connecting cover is fixedly connected to the open end of the deceleration parachute cabin housing, and presses the deceleration parachute between the push plate and the inner wall of the connecting cover. The compression spring is in a compressed state. The other set of ignition devices is arranged on the connecting cover, and a separation charge chamber II is arranged in the connecting cover. When the pressure in the separation charge chamber II reaches a certain value, the connecting cover is separated from the deceleration parachute cabin housing.

3. The omnidirectional reverse inclined surface missile with a deceleration device as claimed in claim 1, wherein, The deceleration device includes a connecting cylinder, a deceleration plate cabin housing, a compression spring, a rotating shaft, a deceleration plate, a torsion spring, a push plate, a connecting cover, and two sets of ignition devices; The speed brake compartment housing is a cylinder with one end open and one end closed. The closed end is fixedly connected to the connecting cylinder, and a separation chamber I is formed between the end face of the closed end and the inner wall of the connecting cylinder. One set of ignition device is installed on the connecting cylinder. When a certain pressure is reached in the separation chamber I, the speed brake compartment housing is separated from the connecting cylinder. One end of the compression spring is fixed to the inner wall of the closed end, and the other end is fixed to the push plate. The speed brake is rotatably connected to the cylinder through a rotating shaft and fits on the outer circumferential surface of the cylinder. A torsion spring is sleeved on the rotating shaft. At the same time, the radially extending rod of the speed brake extends into the speed brake compartment housing and engages with the axial locking pin of the push plate to limit the rotation of the speed brake. The connecting cover is fixedly connected to the open end of the speed brake compartment housing, and the push plate is pressed to make the compression spring in a compressed state. Another set of ignition device is arranged on the connecting cover. A separation chamber II is arranged in the connecting cover. When a certain pressure is reached in the separation chamber II, the connecting cover is separated from the speed brake compartment housing. Under the action of the compression spring, the radially extending rod of the speed brake is separated from the axial locking pin of the push plate, and the speed brake rotates outward 90° along the rotating shaft under the action of the torsion spring.

4. The omnidirectional anti-inclined surface missile with a deceleration device according to claim 2 or 3, characterized in that, The connecting cylinder is a cylinder with one end open and one end closed. A circular ring boss is provided at the port of the open end. The inner surface of the circular ring boss is provided with threads, and a serrated cut angle is provided at the inner end face of the circular ring boss. At a certain pressure, the serrated cut angle breaks.

5. The omnidirectional anti-inclined surface missile with a deceleration device according to claim 2 or 3, characterized in that, A serrated cut angle is provided on the cavity of the separation chamber II. At a certain pressure, the serrated cut angle breaks to realize the separation of the connecting cover from the connected component.

6. The omnidirectional reverse inclined plane missile with a deceleration device as claimed in claim 3, wherein The push plate is a structural member in which two circular plates are connected into one body by a connecting rod. An axial locking pin is provided on the outer surface of one of the circular plates.

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