An omnidirectional reverse slope missile based on thrust vectoring

Abstract

The present invention provides an omnidirectional anti-inclined surface missile based on thrust redirection, which includes a reverse wing assembly, an electric servo, an on-board control module, a warhead, a thrust reversal engine, a guidance component, a connecting cylinder, a flight engine, a tail wing assembly and a launch engine; the reverse wing assembly, the electric servo, the on-board control module, the warhead, the thrust reversal engine, the connecting cylinder, the flight engine, the tail wing assembly and the launch engine are sequentially connected from head to tail to form the missile; the guidance component is arranged at the tail of the thrust reversal engine and is located in the connecting cylinder at the same time; 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 to an omnidirectional anti-slope missile based on thrust deflection. 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. It is easy to defend and difficult to attack: The urban buildings can be used as shelters and fortresses, with good protection and concealment; 2. The combat scale is small: 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. Light weapons are widely used: 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 directly opposite the building where the target is located 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 their sides. Summary of the Invention

[0003] In view of this, the present invention provides an omnidirectional anti-slope missile based on thrust deflection, 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 based on thrust deflection, the missile includes a reverse wing assembly, an electric servo, an on-board control module, a warhead, a thrust reverser, a guidance component, a connecting cylinder, a flight engine, a tail wing assembly and a launch engine;

[0006] The reverse wing assembly, the electric servo, the on-board control module, the warhead, the thrust reverser, the connecting cylinder, the flight engine, the tail wing assembly and the launch engine are sequentially connected from head to tail to form the missile; the guidance component is arranged at the tail of the thrust reverser and is located inside the connecting cylinder at the same time;

[0007] At launch, the reverse fin assembly serves as the missile's head. 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 release phase, and the flight engine provides power for the release phase of the missile. When the missile flies to a predetermined position, the thrust reverser engine separates from the connecting cylinder. At this time, the assembly continues to fly as the missile's head, and the thrust reverser engine operates, causing the separated missile to enter the deceleration and attitude adjustment phase. The thrust reverser engine provides power for the missile to accelerate, and the gas acts on the rudder of the electric servo, adjusting the direction of the missile's head to point towards the target. Then the missile enters the attack phase. 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 servo, generates corresponding trajectory correction control commands in combination with the missile flight timing sequence, and sends them to the electric servo. The electric servo 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.

[0008] Further, the reverse fin assembly includes a fin nacelle housing, fins, fin locking rings, linear motors, fin locking insurance, and a fin deployment control circuit;

[0009] The fin nacelle housing consists of two parts: a conical section and a cylindrical section. The head of the conical section is rotatably connected to the fins, and a locking rod is provided at the tip of the fin. The end of the cylindrical section is used to connect to the electric servo. The cylindrical section is provided with a safety hole along the radial direction for the insertion and extraction of the fin locking insurance. The fin locking insurance is used to control the on-off of the fin deployment control circuit. The fin deployment control circuit controls the linear motor, and the fin locking ring is fixedly connected to the output end of the linear motor;

[0010] When the fins are in the folded state, the fin locking ring moves linearly under the drive of the linear motor and is sleeved on the locking rod at the tip of the fin to complete the locking of the fins. When unlocking, the fin locking ring separates from the tip of the fin under the drive of the linear motor.

[0011] Further, the thrust reverser engine includes a combustion chamber bottom, an engine housing, thrust reverser propellant, a sealing cover, an igniter, and separation gunpowder;

[0012] The engine housing includes a cylindrical section and a conical section. The outer circumference of the cylindrical section is provided with an inclined nozzle. The end of the cylindrical section is fixedly connected to the combustion chamber bottom. The combustion chamber bottom and the inner cavity of the engine housing together form a closed combustion chamber, and the thrust reverser propellant is arranged in the combustion chamber. The conical section is used to be fixedly connected to the connecting cylinder, and at the same time, the end face of the conical section is used to connect to the guidance component. A separation chamber is provided inside the conical section. The separation chamber is isolated from the combustion chamber by a sealing cover. The igniter and separation gunpowder are placed inside the separation chamber. The igniter ignites both the thrust reverser propellant and the separation gunpowder simultaneously. When a certain pressure is reached inside the separation chamber, the engine housing separates from the connecting cylinder.

[0013] Furthermore, the connecting cylinder includes a connecting cylinder housing and a compression spring;

[0014] One end of the connecting cylinder housing is open and the other end is closed. The shape of the inner wall of the open end matches the conical section of the engine housing. The compression spring is located inside the connecting cylinder housing and is fixedly connected to the end face of the closed end.

[0015] Furthermore, the conical section of the engine housing is radially fixedly connected to the connecting cylinder housing through connecting studs. Both the conical section of the engine housing and the connecting cylinder housing are provided with mounting holes for mounting the connecting studs, and the mounting holes communicate with the separation chamber of the engine housing; the cavity of the separation chamber is provided with a serrated cut angle, and at a certain pressure, the connection between the connecting cylinder and the engine housing is separated by fracture at the serrated cut angle.

[0016] Furthermore, the connecting stud is a cylinder with three unequal diameters. The diameter of the upper cylinder is the largest, and it is pressed tightly against the connecting cylinder during mating; the middle part is a smooth cylinder for restricting the axial movement of the engine housing and the connecting cylinder; the lower part is a cylinder with a threaded surface, and its diameter is smaller than that of the smooth cylinder in the middle for threaded connection with the conical section of the engine housing.

[0017] Advantageous effects:

[0018] The flight process of the missile of the present invention is divided into three stages: the release stage, the deceleration and attitude adjustment stage, and the attack stage. With the cooperation of various mechanisms, the attitude and flight trajectory of the missile 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, and preferably solves the problem of striking targets protected by buildings in urban warfare, and has the ability to achieve all-round and precise strikes on buildings within 50 meters to 1000 meters;

[0019] Secondly, the present invention contains two sets of power systems, namely a flight engine and a speed increase engine, and through a multi-stage thrust scheme, the speed requirements of the missile during the launch and release stage and the attack stage in the flight process are guaranteed;

[0020] Furthermore, a reverse thrust engine is used for rapid direction change, and the engine gas acts on the rudder blades to increase the rudder effect, so that the turning radius of the missile is smaller and the maneuverability is stronger during direction change; moreover, the present invention adopts an actuator combining a reverse thrust engine and an electric rudder servo. This scheme enables the electric rudder servo to generate control force using aerodynamic force when the reverse thrust engine is not working, and generate control force using the gas generated by the working of the reverse thrust engine when the flight speed of the missile is relatively low after deceleration, ensuring the control effect of the missile under a large range of flight speed changes;

[0021] Finally, the present invention realizes the separation of the missile from the flight engine, the tail fin assembly, and the launch engine during the reverse flight of the missile, reducing the flight weight and enabling the missile to have better flight characteristics. Description of the Drawings

[0022] Figure 1 Schematic diagram of the ballistic trajectory of the present invention;

[0023] Figure 2 Flow chart of the operation of the present invention;

[0024] Figure 3 Schematic diagram of the overall structure of the present invention;

[0025] Figure 4 Schematic diagram of the structure of the projectile body after reversal;

[0026] Figures 5(a) and 5(b) are respectively schematic diagrams of the reverse wing assembly in the wing locked and deployed states;

[0027] Figure 6(a) is a schematic diagram of the structure of the thrust reverser engine, Figure 6(b) is a left view of Figure 6(a), and Figure 6(c) is a radial cross-sectional view of Figure 6(a);

[0028] Figure 7(a) is a schematic diagram of the structure of the connecting cylinder, and Figure 7(b) is a radial cross-sectional view of Figure 7(a);

[0029] Figure 8 Schematic diagram of the structure of the separation mechanism;

[0030] Figure 9 Schematic diagram of the structure of the connecting stud;

[0031] Among them, 1 - reverse wing assembly, 2 - electric servo, 3 - on-board control module, 4 - warhead, 5 - thrust reverser engine, 6 - guidance component, 7 - connecting cylinder, 8 - flight engine, 9 - tail wing assembly, 10 - launch engine, 11 - wing compartment housing, 12 - wing, 13 - wing locking ring, 14 - linear motor, 15 - wing locking safety, 16 - wing opening control circuit, 17 - bottom of combustion chamber, 18 - engine housing, 19 - thrust reversal propellant, 20 - igniter, 21 - sealing cover, 22 - separation powder, 23 - connecting stud, 24 - guidance compartment housing, 25 - connecting cylinder housing, 26 - compression spring. Detailed implementation manners

[0032] The following takes examples in conjunction with the accompanying drawings to describe the present invention in detail.

[0033] This embodiment provides an omnidirectional anti-slope missile based on thrust redirection, using a 40-mm rocket launcher as the launch platform. As Figure 3 shown, this omnidirectional anti-slope missile includes a reverse wing assembly 1, an electric servo 2, an on-board control module 3, a warhead 4, a thrust reverser engine 5, a guidance component 6, a connecting cylinder 7, a flight engine 8, a tail wing assembly 9, and a launch engine 10.

[0034] The reverse wing assembly 1, electric actuator 2, missile-borne control module 3, warhead 4, thrust-vectoring engine 5, connecting cylinder 7, flight engine 8, tail assembly 9 and launch engine 10 are sequentially connected from head to tail to form a missile. The guidance assembly 6 is arranged at the tail of the thrust-vectoring engine 5 and is located inside the connecting cylinder 7 at the same time. During launch, the reverse wing assembly 1 serves as the missile head. When reverse motion starts, the front and rear parts of the missile body separate at the connection between the thrust-vectoring engine 5 and the connecting cylinder 7, and the missile body flies in the separated form. After reverse motion, the form is as shown in Figure 4 shown. At this time, the missile head is the guidance assembly 6, and the missile tail is the reverse wing assembly 1.

[0035] As shown in Fig. 5(a), the reverse wing assembly 1 includes a wing nacelle housing 11, wings 12, wing locking rings 13, linear motors 14, wing locking safeties 15 and wing deployment control circuits 16.

[0036] The wing nacelle housing 11 consists of a conical section and a cylindrical section. The outer circumference of the conical section is provided with the same number of long grooves as the number of wings 12 for the folding and deployment of the wings 12. The head of the conical section is rotatably connected to the wings 12, and locking rods are provided at the wing tips of the wings 12. The end of the cylindrical section is provided with threads for connection to the electric actuator 2. The cylindrical section is provided with safety holes along the radial direction for the insertion and extraction of the wing locking safeties 15. At the same time, a number of antenna holes are radially opened in the cylindrical section. When a satellite guidance assembly is adopted, it is used for the installation of the satellite receiver antenna. When other guidance methods are adopted, the antenna holes can be left empty.

[0037] When the missile is in the service state, standby launch state and the state before reverse motion after launch, the wings 12 in the reverse wing assembly 1 need to be folded in the wing nacelle housing 11 and kept locked. Only after the missile is launched and the reverse motion is completed, the wings 12 will deploy. The deployment and locking of the wings 12 are controlled by the wing locking rings 13, linear motors 14, wing locking safeties 15 and wing deployment control circuits 16. The outer wall of the wing locking ring 13 is fixedly connected to the output shaft of the linear motor 14 and moves linearly with the output shaft of the linear motor 14. The linear motor 14 is connected to the wing deployment control circuit 16. When the wing deployment control circuit 16 is not powered or does not send an action signal to the linear motor 14, the output shaft of the linear motor 14 controls the wing locking ring 13 to be sleeved on the locking rod at the wing tip part of the wing 12, and the wing 12 is in the folded state and locked. When the wing deployment control circuit 16 is powered and sends an action signal to the linear motor 14, the output shaft of the linear motor 14 drives the wing locking ring 13 to move, losing the restraint on the locking rod at the wing tip part of the wing 12. As shown in Fig. 5(b), the wing 12 is automatically deployed under the action of a torsion spring (or leaf spring) at its wing root part.

[0038] The wing locking safety 15 is inserted into the safety hole of the wing compartment housing 11 before the missile is launched, acting as a switch for the wing deployment control circuit 16. When the wing locking safety 15 is located in the safety hole of the wing compartment housing 11, the power supply of the wing deployment control circuit 16 is not connected to the circuit. When the wing locking safety 15 (operated by the shooter) is pulled out from the safety hole of the wing compartment housing 11, the power supply of the wing deployment control circuit 16 is connected to the circuit and supplies power to the circuit. The wing deployment control circuit 16 consists of a power supply (lithium battery), a chip, a forward overload switch, and a reverse overload switch. After the wing deployment control circuit 16 is connected to its internal power supply and sequentially receives the forward overload switch signal and the reverse overload switch signal in sequence, it outputs an action signal to the linear motor 14.

[0039] When using an autopilot to stabilize the missile, the reverse wing assembly 1 can be dispensed with, and its position can be replaced by a component with the same shape as the wing compartment housing 11 to ensure the aerodynamic shape of the missile.

[0040] The electric servo 2 includes a rudder vane, a transmission mechanism, a motor, and a driver, and receives a control command given by the missile-borne control module 3 to cause the rudder vane to deflect. When the thrust reverser 5 is not working, the aerodynamic force acting on the rudder vane generates a control force and a control moment under the deflection of the rudder vane; when the thrust reverser 5 is working, the gas ejected from its nozzle acts on the rudder vane to generate a control force and a control moment. The control force and the control moment generated by the deflection of the rudder vane cause the missile body to fly along a pre-set trajectory.

[0041] The missile-borne control module 3 consists of a wireless setting reception module, an on-board computer, and an on-board power supply. Among them, the wireless setting reception 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 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 work process, performs calculations based on the missile position information and attitude information transmitted by the guidance component 6, generates corresponding trajectory correction control commands in combination with the missile flight time sequence, and sends them to the electric servo 2. 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.

[0042] The warhead 4 consists of a security mechanism, detonator tubes, and a warhead body.

[0043] As shown in Figure 6(a), the thrust reverser 5 includes a combustion chamber bottom 17, an engine housing 18, a thrust reverse propellant 19, an igniter 20, a sealing cover 21, and separation gunpowder 22.

[0044] The engine housing 18 includes a cylindrical section and a conical section. As shown in Fig. 6(b), four inclined nozzles are provided on the outer circumference of the cylindrical section. The layout of these four inclined nozzles is in phase with the four fins of the electric actuator 2, and the nozzles of the nozzles face the four fins of the electric actuator 2. The end of the cylindrical section is connected to the bottom of the combustion chamber 17 by a thread. The bottom of the combustion chamber 17 and the inner cavity of the engine housing 18 together form a closed combustion chamber. The reverse propellant 19 is arranged in the combustion chamber. The gas generated during its combustion is ejected through the four nozzles on the engine housing 18 to decelerate and reverse-accelerate the projectile body. The conical section of the engine housing 18 is used to be fixedly connected to the connecting cylinder 7, and at the same time, the end face of the conical section is used to be connected to the guidance component 6. A cylindrical separation chamber is provided axially in the conical section. The separation chamber is isolated from the combustion chamber by a sealing cover 21. The igniter 20 and the separation gunpowder 22 are placed inside the separation chamber. The igniter 20 has two ignition heads. One is used to ignite the reverse propellant 19, and the other is used to ignite the separation gunpowder 22. These two ignition heads act simultaneously. Four cylindrical light holes are spaced 90° apart along the radial direction on the right side of the separation chamber of the engine housing 18. The four cylindrical light holes communicate with the separation chamber. A sawtooth cut angle is provided on the cavity of the separation chamber, which is called a shear key. At a certain pressure, the connection between the connecting cylinder 7 and the engine housing 18 is separated at the sawtooth cut angle. As shown in Fig. 6(c). Cylindrical stepped holes are provided at the bottom of the four cylindrical light holes. The inner wall of the stepped hole is a threaded surface for fixing to the connecting stud 23.

[0045] In this embodiment, the guidance component 6 adopts an inertial guidance system, which consists of inertial navigation devices and fuzes and is installed in the guidance cabin housing 24. The inertial guidance 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 movement of the missile body; the attitude measurement device can sense the attitude and attitude change rate of the movement of the missile body; the position calculation device can calculate the position information of the missile body according to the integration of the acceleration and attitude of the missile body. The inertial guidance cabin housing 24 not only serves to place and protect the guidance component 6, but also plays a role in maintaining the aerodynamic shape of the projectile body. In the service state and the pre-reverse stage of the flight process, the guidance component 6 is wrapped inside the connecting cylinder 7. In the reverse stage of the flight process, the connecting cylinder 7 and the subsequent parts (flight engine 8, tail fin assembly 9, and launch engine 10) are separated from the front part of the projectile body, and the guidance component 6 is exposed and serves as the head of the projectile body. The attitude measurement device integrates inertial devices and geomagnetic elements and can measure information such as the roll angle, pitch, yaw angular velocity, and acceleration during the movement of the projectile body to meet the requirements of various control laws. The guidance component 6 sends the movement information of the missile to the on-board control module 3.

[0046] When an external guidance scheme other than this embodiment is adopted, the guidance component 6 and the guidance cabin housing 24 can be replaced with corresponding seeker heads.

[0047] As shown in Fig. 7(a), the connecting cylinder 7 is composed of a connecting cylinder housing 25 and a compression spring 26. One end of the connecting cylinder housing 25 is open and the other end is closed. The outer wall is a cylindrical surface, and the inner cavity is a combination of a cone and a cylinder. The slope of the conical surface is the same as the slopes of the conical section of the engine housing 18 and the outer wall of the guidance cabin housing 24. The compression spring 26 is fixedly connected to the end face of the cylindrical groove. Four cylindrical light holes are radially spaced 90° at the conical section of the inner cavity of the connecting cylinder housing 25. As shown in Fig. 7(b), these four light holes communicate with the conical inner wall of the connecting cylinder housing 25, and when the connecting cylinder housing 25 is properly fitted with the engine housing 18, these four light holes need to be coaxially aligned with the four cylindrical light holes of the thrust reverser engine housing 18.

[0048] As Figure 8 shown, the separation mechanism of the projectile body is composed of a thrust reverser engine 5, a guidance component 6 and a connecting cylinder 7, and specifically includes the components of the thrust reverser engine 5, the guidance component 6, the guidance cabin housing 24, the components of the connecting cylinder and the connecting stud 23. The guidance cabin housing 24 is threadedly connected to the engine housing 18. The engine housing 18 and the guidance cabin housing 24 are inserted into the inside of the connecting cylinder housing 25. The conical outer walls of the engine housing 18 and the guidance cabin housing 24 are in contact with the conical inner wall of the connecting cylinder housing 25. At this time, the compression spring 26 of the connecting cylinder 7 is compressed by the guidance cabin housing 24, and the four radially cylindrical light holes of the engine housing 18 are aligned with the four radially cylindrical light holes of the connecting cylinder housing 25. As Figure 9 shown, the connecting stud 23 is a cylinder with three different diameters. The upper part is a frustum with the largest diameter among the three sections, which is pressed tightly against the connecting cylinder housing 25 during fitting; the middle part is a smooth cylinder, which is used to restrict the axial movement of the connecting cylinder housing 25 and the engine housing 18; the lower part is a cylinder with a threaded surface, and its diameter is smaller than that of the smooth cylinder in the middle part, which is used to cooperate with the threaded inner wall of the shear key of the engine housing 18 to fix the connecting cylinder housing 25 and the engine housing 18. In terms of the fitting relationship, the connecting stud 23 is inserted into the four radially cylindrical light holes of the engine housing 18 and the connecting cylinder housing 25. The lower threaded section thereof cooperates with the threaded inner wall of the stepped hole inner wall of the engine housing 18, and the upper cylindrical platform presses tightly against the connecting cylinder housing 25. At this time, a sealed cavity is formed by the lower end face of the connecting stud 23, the sealing cover 21 and the separation chamber of the engine housing 18, and a separation charge 22 and an igniter head of the igniter 20 are placed therein.

[0049] The working principle of the separation mechanism is as follows: When in the service state and the reverse pre-stage of the flight state, the reverse thrust engine 5 and the guidance component 6 are fixed to the connecting cylinder 7 under the fixation of the connecting stud 23, and the separation mechanism is in the connected state. When entering the reverse section of the flight state, the ignition head of the igniter 20 ignites the separation gunpowder 22, and the generated gas causes the pressure in the closed cavity formed by the lower end face of the connecting stud 23, the sealing cover 21, and the separation chamber of the reverse thrust engine housing 18 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 engine housing 18 and the connecting cylinder housing 25, and is pushed away from the engine housing 18 and the connecting cylinder housing 25 under the action of the gas pressure; since the connecting stud 23 is pushed out, the engine housing 18 and the connecting cylinder housing 25 lose their fixation; under this condition, the compression spring 26 in the cylindrical groove of the connecting cylinder housing 25 pushes the front part of the projectile away from the connecting cylinder 7 to achieve separation.

[0050] The flight engine 8 is used to provide the first-stage speed increase for the projectile after the missile is launched. When precision launch is not required, the range can reach 1500 m.

[0051] The tail fin assembly 9 is arranged between the flight engine 8 and the launch engine 10 of the projectile, and is composed of a tail rod and tail fins, and is used to stabilize the flight attitude of the projectile and provide the rotation speed when leaving the tube.

[0052] The launch engine 10 is arranged at the tail of the projectile and is used to launch the projectile out of the 40-mm rocket launcher at a certain initial velocity and direction. The launch system of the 40-mm standard rocket projectile can also be used as the launch system of the present invention to replace the launch engine 10.

[0053] The overall working process of this embodiment is as follows:

[0054] 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 geographical reference information, target position information, meteorological condition information, altitude information, and the elevation angle and azimuth calculated by the simple fire control on the projectile platform. After completing the above operations, the shooter loads the full-round projectile 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 6 to complete the initial alignment of the inertial navigation device. The shooter pulls out the wing locking insurance 15 of the reverse wing assembly 1, and at this time, the wing opening control circuit 16 of the reverse wing assembly 1 is activated; then the shooter pulls the trigger to ignite the launch engine 10, and after the launch engine 10 is ignited, it pushes the projectile to accelerate to the predetermined speed, such as Figure 1 、 Figure 2As shown, the missile flies towards the opposite side of the target during the release phase. The launch overload generated during this process activates the thermal battery on the missile and the igniter 20 of the reverse thrust engine 5 at the same time. Meanwhile, the forward overload switch of the wing deployment control circuit 16 of the reverse wing assembly 1 is activated. Approximately 0.5 s after leaving the muzzle, the thermal battery operates stably and normally. During the flight, the guidance component 6 calculates in real time the motion states of the missile body such as its real-time position and attitude. When the missile body flies to the predetermined position, the igniter 20 of the reverse thrust engine 5 ignites the reverse thrust propellant 19 and the separation gunpowder 22 simultaneously. After the reverse thrust propellant 19 is ignited, a thrust opposite to the flight direction of the missile body is generated, causing the missile body to decelerate and then fly in the direction opposite to the original velocity direction. The missile enters the deceleration and attitude adjustment phase. After the separation gunpowder 22 is ignited, the gas generated by it pushes out the connecting stud 23, realizing the separation of the front and rear parts of the missile body. When the reverse thrust engine 5 starts to operate, the reverse overload switch in the wing deployment control circuit 16 of the reverse wing assembly 1 senses the reverse acceleration and is activated. At this time, the wing deployment control circuit 16 sends an action command signal to the linear motor 14, and the linear motor 14 drives the wing locking ring 13 to move, releasing the lock of the wing 12, and the wing 12 opens in place. At this time, the reverse wing assembly 1 serves as the tail of the missile body, and the guidance component 6 serves as the head of the missile body. The missile body enters the reverse flight phase in this form. After the missile body enters the reverse flight phase, the guidance component 6 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 corresponding control commands in combination with the missile flight timing sequence. The control commands are transmitted to the electric actuator 2. When the missile head direction is adjusted to point to the target, the missile enters the attack phase, and the electric actuator 2 controls the missile body to fly along the planned trajectory until it hits the target.

[0055] In summary, the above is only a preferred embodiment of the present invention and is not intended 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 within the protection scope of the present invention.

Claims

1. An omnidirectional reverse slope missile based on thrust vectoring, characterized in that, The missile includes a reverse fin assembly, an electric actuator, an on-board control module, a warhead, a thrust reverser, a guidance component, a connecting cylinder, a flight engine, a tail fin assembly, and a launch engine; The reverse fin assembly, the electric actuator, the on-board control module, the warhead, the thrust reverser, the connecting cylinder, the flight engine, the tail fin assembly, and the launch engine are sequentially connected from head to tail to form the missile; the guidance component is arranged at the tail of the thrust reverser and is located inside the connecting cylinder at the same time; During launch, the reverse fin assembly serves as the head of the missile, and 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 thrust reverser is separated from the connecting cylinder. At this time, the assembly continues to fly as the head of the missile, and the thrust reverser works, causing the separated missile to enter the deceleration and attitude adjustment stage. The thrust reverser provides power for the missile to accelerate, and the gas acts on the rudder of the electric actuator to adjust the direction of the missile head to point at the target. Then the missile enters the attack stage. 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 ballistic trajectory until it hits the target.

2. The omnidirectional reverse slope missile based on thrust vectoring as claimed in claim 1, wherein The reverse fin assembly includes a fin nacelle housing, fins, a fin locking ring, a linear motor, a fin locking safety device, and a fin deployment control circuit; The fin nacelle housing consists of a conical section and a cylindrical section. The head of the conical section is rotatably connected to the fin. A locking rod is provided at the tip of the fin. The end of the cylindrical section is used to connect to the electric actuator. The cylindrical section is provided with a safety hole in the radial direction for inserting and removing the fin locking safety device. The fin locking safety device is used to control the on-off of the fin deployment control circuit. The fin deployment control circuit controls the linear motor, and the fin locking ring is fixedly connected to the output end of the linear motor; When the fins are in the folded state, the fin locking ring moves linearly under the drive of the linear motor and is sleeved on the locking rod at the tip of the fin to complete the locking of the fin. When unlocking, the fin locking ring is separated from the tip of the fin under the drive of the linear motor.

3. The omnidirectional reverse slope missile based on thrust deflection as claimed in claim 1, wherein, The thrust reverser includes a combustion chamber bottom, an engine housing, a thrust reversal propellant, a sealing cover, an igniter, and separation gunpowder; The engine housing includes a cylindrical section and a conical section. An inclined nozzle is provided on the outer circumference of the cylindrical section. The end of the cylindrical section is fixedly connected to the combustion chamber bottom. The combustion chamber bottom and the inner cavity of the engine housing together form a closed combustion chamber. The thrust reversal propellant is arranged in the combustion chamber. The conical section is used to be fixedly connected to the connecting cylinder, and at the same time, the end face of the conical section is used to connect to the guidance component. A separation chamber is provided inside the conical section. The separation chamber is isolated from the combustion chamber by a sealing cover. The igniter and the separation gunpowder are placed inside the separation chamber. The igniter ignites the thrust reversal propellant and the separation gunpowder at the same time. When a certain pressure is reached inside the separation chamber, the engine housing is separated from the connecting cylinder.

4. The omnidirectional reverse slope missile based on thrust vectoring according to claim 3, characterized in that The connecting cylinder includes a connecting cylinder housing and a compression spring; One end of the connecting cylinder housing is open and the other end is closed. The shape of the inner wall of the open end matches the conical section of the engine housing. The compression spring is located inside the connecting cylinder housing and is fixedly connected to the end face of the closed end.

5. The omnidirectional reverse slope missile based on thrust vectoring as claimed in claim 4, wherein The conical section of the engine housing is radially fixedly connected to the connecting cylinder housing through connecting studs. Both the conical section of the engine housing and the connecting cylinder housing are provided with mounting holes for mounting the connecting studs, and the mounting holes communicate with the separation chamber of the engine housing; the cavity of the separation chamber is provided with a serrated cut angle, and at a certain pressure, the connection between the connecting cylinder and the engine housing is separated by fracture at the serrated cut angle.

6. The omnidirectional anti-inclined surface missile based on thrust deflection as claimed in claim 5, wherein The connecting stud is a cylinder with three different diameters. The upper part of the cylinder has the largest diameter and is pressed against the connecting cylinder during fitting; the middle part is a smooth cylinder for restricting the axial movement of the engine housing and the connecting cylinder; the lower part is a threaded cylinder with a diameter smaller than that of the smooth cylinder in the middle for threaded connection with the conical section of the engine housing.

Images