A detachable guided rocket for a 40mm rocket launcher

Abstract

The present invention discloses a detachable guided rocket for a 40mm rocket launcher, which adopts a direct-nozzle range-extending engine and installs a separation mechanism between the direct-nozzle range-extending engine and its rear booster engine, so that the booster engine and the launching system are separated from the front missile body after the work is completed, thereby avoiding the adverse effect of the jet acting on the tail wing when the direct-nozzle range-extending engine is working. Moreover, after separation, the direct-nozzle nozzle of the direct-nozzle range-extending engine is exposed, which does not affect the thrust generated by the direct-nozzle range-extending engine. At the same time, the direct-nozzle range-extending engine solution effectively improves the engine thrust utilization efficiency, and on the basis of ensuring the flight stability of the rocket, the rocket has the ability to accurately strike and suppress moving and stationary targets at long range.

Description

Technical Field

[0001] The present invention relates to the technical field of guided rockets, and in particular to a detachable guided rocket for a 40mm rocket launcher. Background Art

[0002] The 40mm individual rocket launcher (Bazooka) is a conventional infantry assault weapon platform for close-range countermeasures against personnel, tanks, armored vehicles, and fortifications. Its low cost, lightweight, simple operation, and portability make it highly sought after and widely deployed by various countries, with a total inventory exceeding one million. However, the platform's current ammunition is unguided rockets. With a CEP (Circular Error Probable) of 0.45m, the maximum range against stationary targets is only 300m. Even without high accuracy, the rocket's flight distance is only approximately 1,500m. This significantly limits the 40mm platform's effectiveness in long-range combat.

[0003] To increase the range of 40mm rockets, installing a range-extending engine can be achieved. Due to the limited caliber of the 40mm rocket launcher, the range-extending engine must be installed in an over-caliber position to ensure sufficient total impulse. In this installation position, the range-extending engine, along with the 40mm booster engine and tail boom, must be designed with an inclined nozzle to ensure the engine can generate thrust to propel the rocket. However, this design approach presents another problem: due to manufacturing and installation errors, the rocket's tail fins are often asymmetrical. When the range-extending engine is operating, the high-speed combustion gas ejected from the nozzle generates aerodynamic forces on the asymmetrical tail fins, causing the rocket to produce a coning motion. This coning motion has three impacts on the rocket's flight: first, it increases the rocket's drag; second, it reduces the thrust component of the range-extending engine on the rocket's velocity, reducing the range-extending engine's acceleration effect; and third, it reduces the rocket's flight stability. The first two impacts reduce the range-extending engine's effectiveness, and the last can even cause the rocket to become unstable.

[0004] In order to improve the combat effectiveness of ammunition for 40mm rocket launchers and solve the application problems of extended-range engines in rockets, it is necessary to propose a detachable guided rocket for 40mm rocket launchers. Summary of the Invention

[0005] In view of this, the present invention provides a detachable guided rocket for a 40mm rocket launcher, which does not affect the thrust generated by the extended-range engine, while avoiding the adverse effects of the jet acting on the tail fin when the extended-range engine is working. On the basis of ensuring the flight stability of the rocket, the rocket has the ability to accurately strike and suppress moving and stationary targets at long range.

[0006] The technical solution adopted in the present invention is as follows:

[0007] A detachable guided rocket for a 40mm rocket launcher, comprising a guidance cabin, a control cabin, a warhead, an actuator, a direct-injection tube range-extending engine, a detachment mechanism, a booster engine, and a launch system;

[0008] The guidance cabin is set at the head of the guided rocket. The guidance cabin, control cabin, warhead, actuator, direct injection tube range extender engine, separation mechanism, booster engine and launch system are connected in sequence to form a guided rocket.

[0009] The launch system provides initial power for the rocket, and the booster engine is used to increase the speed of the rocket after it flies away from the launch tube. After the booster engine finishes working, the front and rear parts of the guided rocket are separated by the separation mechanism, and the straight-injection tube range-extending engine continues to provide flight power for the rocket; the guidance cabin communicates with the control cabin, transmits different guidance information to the control cabin, and the control cabin communicates with the actuator, sends the generated trajectory correction control instructions to the actuator, and the actuator is used to execute actions according to the control instructions to make the rocket fly until it hits the target.

[0010] Furthermore, the direct injection range extender engine comprises an engine housing, an ignition device, a propellant and a thermal insulation layer;

[0011] The engine casing is a cylindrical cavity with one end closed and a trumpet-shaped opening on the other end face. The large end faces backward as the engine nozzle, and the direction of the opening is consistent with the axis direction of the engine casing; the propellant is arranged inside the engine casing, one end is connected to the ignition device, and the other end is in contact with the inner wall surface of the open end of the engine casing through the thermal insulation layer; a through hole is opened in the middle of the thermal insulation layer, which is connected to the trumpet-shaped opening; the other end of the engine casing extends out of the plane where the large end of the trumpet-shaped opening is located, and a stepped through hole is provided radially on the inner wall surface of the extended end.

[0012] Furthermore, the separation mechanism includes a separation mechanism housing, a compression spring, a push plate and an explosive bolt;

[0013] The separation mechanism housing is a cylindrical cavity with one end open, and a plurality of threaded holes are evenly distributed along the circumference on the inner wall of the cavity, which is used to connect to the direct injection pipe range extender engine through explosive bolts; the push plate is fixed to the closed end of the separation mechanism housing by a compression spring; the explosive bolts are used to connect the separation mechanism to the direct injection pipe range extender engine;

[0014] When the separation mechanism is fixedly connected to the direct injection pipe extended range engine, the compression spring is compressed and the push plate closes the nozzle outlet of the direct injection pipe extended range engine; when the explosive bolt acts, the separation mechanism is separated from the direct injection pipe extended range engine, the compression spring returns to its original length, and drives the push plate to push the separation mechanism away from the direct injection pipe extended range engine.

[0015] Furthermore, the separation mechanism includes a separation mechanism housing, a compression spring, a push plate and an explosive bolt;

[0016] The separation mechanism housing is a cylindrical cavity with one end open, and a plurality of threaded holes are evenly distributed along the circumference on the inner wall of the cavity, and the positions of the threaded holes correspond to the positions of the stepped through holes. The push plate is fixed to the closed end of the separation mechanism housing by a compression spring. The explosive bolt is used to be radially installed in the stepped through hole and the threaded hole to connect the separation mechanism to the direct injection pipe extended range engine.

[0017] When the separation mechanism is fixedly connected to the direct injection pipe extended-range engine, the compression spring is compressed and the push plate closes the trumpet-shaped opening of the direct injection pipe extended-range engine; when the explosive bolt acts, the separation mechanism is separated from the direct injection pipe extended-range engine, the compression spring returns to its original length, and drives the push plate to push the separation mechanism away from the direct injection pipe extended-range engine.

[0018] Furthermore, the actuator adopts an electric servo, a pulse engine, a maintenance correction component or a two-dimensional correction component.

[0019] Furthermore, the guidance cabin adopts a laser semi-active guidance head, an infrared guidance head, an image guidance head, a satellite receiver or an inertial guidance component.

[0020] Furthermore, the launch system adopts a tail boom assembly or a launch engine equipped with propellant.

[0021] Beneficial effects:

[0022] 1. The present invention adopts a direct-nozzle range-extender engine and installs a separation mechanism between the direct-nozzle range-extender engine and its rear booster engine, so that the 40 mm diameter part of the launch system and the booster engine are separated from the front body after the work is completed, avoiding the adverse effects of the jet acting on the tail fin when the direct-nozzle range-extender engine is working, reducing the weight of the guidance section rocket, making the rocket have a greater normal acceleration under the same control force, and improving the maneuverability of the rocket; after separation, the direct-nozzle nozzle of the direct-nozzle range-extender engine is exposed, which does not affect the thrust generated by the direct-nozzle range-extender engine. At the same time, the direct-nozzle solution effectively improves the engine thrust utilization efficiency, and on the basis of ensuring the flight stability of the rocket, the rocket has the ability to accurately strike and suppress moving and stationary targets at long range.

[0023] Secondly, the present invention improves the range and hit accuracy of the 40mm rocket by adopting a direct injection tube extended-range engine, a control cabin and an actuator, thereby enhancing its combat effectiveness;

[0024] 2. The separation mechanism of the present invention has a simple structure and is easy to separate the front and rear parts of the guided rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1It is a schematic diagram of the overall structure of the present invention;

[0026] Figure 2 This is a schematic structural diagram of the direct injection range extender engine of the present invention;

[0027] Figure 3(a) and Figure 3(b) are schematic diagrams of the structure of the separation mechanism in the compressed state and the restored state respectively;

[0028] Figure 4 This is a schematic diagram of the connection between the separation mechanism and the direct injection pipe range extender engine.

[0029] Among them, 1-guidance cabin, 2-control cabin, 3-warhead, 4-electric servo, 5-direct injection tube extended range engine, 6-separation mechanism, 7-boost engine, 8-tail boom assembly, 9-engine housing, 10-ignition device, 11-propellant, 12-thermal insulation layer, 13-explosive bolt, 14-separation mechanism housing, 15-compression spring, 16-push plate. DETAILED DESCRIPTION

[0030] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0031] The present invention provides a detachable guided rocket for a 40mm rocket launcher, such as Figure 1 As shown, the guided rocket includes a guidance cabin 1, a control cabin 2, a warhead 3, an actuator, a direct-injection tube range-extending engine 5, a separation mechanism 6, a booster engine 7 and a launch system; the guidance cabin 1 is arranged at the head of the guided rocket, and the guidance cabin 1, the control cabin 2, the warhead 3, the actuator, the direct-injection tube range-extending engine 5, the separation mechanism 6, the booster engine 7 and the launch system are connected in sequence to constitute a guided rocket.

[0032] Guidance pod 1 uses a semi-active laser seeker as a guidance component, mounted on the guided rocket's nose. During flight, a ground-based laser transmitter illuminates the target. The semi-active laser seeker in guidance pod 1 receives the laser signal scattered by the target and generates a missile-target line-of-sight angle deviation signal, which is transmitted in real time to control pod 2. In addition to semi-active laser guidance, guidance pod 1 can also utilize other guidance components, including infrared seekers, image seekers, satellite receivers, and inertial guidance units.

[0033] The control cabin 2 consists of a wireless positioning receiver module, an attitude measurement device, a flight control computer, and a power supply. The wireless positioning receiver module is used to receive information such as the seeker bit rate, altitude, weather conditions, and firing direction before firing. The attitude measurement device integrates inertial devices and geomagnetic elements, capable of measuring information such as the roll angle, pitch, yaw angular velocity, and acceleration during the guided rocket's motion to meet the requirements of various control laws. The flight control computer manages the platform's workflow and calculates information received from the satellite positioning device and the attitude measurement device to plan the flight trajectory, generate control commands, and transmit these commands to the electric servo 4. The onboard power supply uses a thermal battery, activated by launch overload, to power the onboard electrical system.

[0034] The warhead 3 is composed of a security mechanism, a detonating tube and a warhead body.

[0035] In this embodiment, the actuator is an electric servo 4, which consists of a rudder blade, a transmission mechanism, a motor, and a driver. It receives commands from the controller in the control cabin 2 to generate control force and torque, thereby causing the rocket to fly along a pre-set trajectory. In addition to the electric servo 4, the actuator can also be replaced by a pulse engine, a maintenance component, and a two-dimensional correction component.

[0036] The extended-range engine adopts a direct-injection nozzle scheme to provide the thrust required for the extended range of guided rockets. Figure 2 As shown, the direct injection range extender engine 5 includes an engine housing 9, an ignition device 10, a propellant 11 and a thermal insulation layer 12.

[0037] The engine housing 9 is a cylindrical cavity, closed at one end and provided with a trumpet-shaped opening on the other end face. The large end faces rearward and serves as the engine nozzle, with the opening oriented in the same direction as the axis of the engine housing 9. The propellant 11 is disposed within the engine housing 9, connected at one end to the igniter 10 and in contact with the inner wall surface of the open end of the engine housing 9 through a thermal insulation layer 12 at the other end, to prevent deformation or damage to the lower end face of the engine housing 9 at high temperatures. When the propellant 11 burns, a large amount of combustion gas is generated, which is ejected from the nozzle of the engine housing 9, generating thrust to propel the rocket into flight. A through hole is provided in the center of the thermal insulation layer 12, communicating with the trumpet-shaped opening to allow the combustion gas generated by the combustion of the propellant 11 to pass through. The other end of the engine housing 9 extends beyond the plane of the large end of the trumpet-shaped opening, and a stepped through hole is provided radially on the inner wall surface of the extended end. The stepped through hole is a light hole.

[0038] The separation mechanism 6 includes a separation mechanism housing 14, a compression spring 15, a push plate 16 and an explosive bolt 13; the explosive bolt 13 is a stepped cylinder, a part of the outer circumference of the small diameter section is smooth, which cooperates with the stepped through hole on the engine housing 9, and a part is a threaded surface, which is threadedly connected to the separation mechanism housing 14; the inside of the explosive bolt 13 is hollow, used to place gunpowder.

[0039] The separation mechanism housing 14 is a cylindrical cavity with one end open, and a plurality of threaded holes are evenly distributed along the circumference on the inner wall of the cavity, which is used to connect with the direct injection pipe range extender engine 5 through the explosive bolt 13; Figure 4 As shown, the push plate 16 is fixed to the closed end of the separation mechanism housing 14 through a compression spring 15; the explosive bolt 13 is used to connect the separation mechanism 6 and the direct injection pipe range extender engine 5.

[0040] As shown in Figure 3(a) and Figure 3(b), when the separation mechanism 6 is fixedly connected to the direct injection tube extender engine 5, the compression spring 15 is compressed and the push plate 16 closes the nozzle outlet of the direct injection tube extender engine 5; when the explosive bolt 13 acts, the separation mechanism 6 is separated from the direct injection tube extender engine 5, the compression spring 15 restores its original length, and drives the push plate 16 to push the separation mechanism 6 away from the direct injection tube extender engine 5, so that the front and rear parts of the rocket are separated.

[0041] In this embodiment, the launch system utilizes a propellant-loaded tail boom assembly 8. This assembly, located at the rear of the rocket and consisting of a boom, propellant, and tail fins, is used to launch the rocket and ensure stability during the flight phase from launch to separation. In addition to the propellant-loaded tail boom assembly 8, the launch system can also utilize a launch engine for launch.

[0042] The working process of this embodiment is as follows:

[0043] Before launching, the front and rear parts of the guided rocket are not separated, the direct injection tube range extender engine 5 and the separation mechanism 6 are fixedly connected by the explosive bolt 13, the compression spring 15 is compressed, and the push plate 16 presses against the lower end surface of the range extender engine housing 9.

[0044] During operation, after entering the position and following instructions from the superior command system or using forward sighting equipment to determine the target status, the shooter loads the guided rocket into the 40mm rocket launcher, places the rocket launcher on his shoulder, and adjusts the launch angle to the set range using the rocket launcher's sighting device. The tail boom assembly 8 provides the rocket with initial power. The shooter pulls the trigger to ignite the propellant in the tail boom assembly 8. The ignition of the propellant accelerates the rocket to a predetermined speed. The launch overload generated during this process also activates the thermal battery in the control cabin 2. Once the thermal battery is operating normally and stably, it begins to power the various electrical components on the rocket. The booster engine 7 begins to operate some time after the rocket leaves the launch tube, continuing to increase the rocket's speed.

[0045] When the booster engine 7 finishes working, the flight control computer in the control cabin 2 outputs a separation command, the explosive bolt 13 in the separation mechanism 6 acts, the separation mechanism housing 14 and the engine housing 9 are no longer fixedly connected, the compression spring 15 returns to its original length, and the push plate 16 pushes the separation mechanism 6 away from the direct injection tube range extender engine 5, separating the front and rear of the rocket.

[0046] After the front and rear parts of the rocket are separated, the flight control computer in the control cabin 2 outputs an ignition signal for the direct-injection tube range-extending engine 5 according to the set timing. The ignition device 10 in the direct-injection tube range-extending engine 5 acts to ignite the propellant 11. The combustion of the propellant 11 produces gas which is ejected from the nozzle of the engine casing 9 to generate thrust, thereby increasing the speed and range of the rocket.

[0047] The laser illuminator on the ground launches towards the target, and the laser semi-active seeker in the guidance cabin 1 receives the laser signal scattered by the target, and calculates the missile-target line-of-sight angle deviation and outputs it to the flight control computer in the control cabin 2; after receiving the missile-target line-of-sight angle deviation signal and the attitude information output by the attitude measurement device, the flight control computer generates a trajectory correction control instruction; the control cabin 2 communicates with the electric servo 4, transmits the trajectory correction control instruction to the electric servo 4, and controls the rocket to fly along the planned trajectory until it hits the target.

[0048] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A detachable guided rocket for a 40mm bazooka, characterized in that: The guided rocket includes a guidance cabin, a control cabin, a warhead, an actuator, a direct injection tube extended-range engine, a separation mechanism, a booster engine and a launch system; The guidance cabin is set at the head of the guided rocket. The guidance cabin, control cabin, warhead, actuator, direct injection tube range extender engine, separation mechanism, booster engine and launch system are connected in sequence to form a guided rocket. The launch system provides initial power for the rocket, and the booster engine is used to increase the speed of the rocket after it leaves the launch tube. After the booster engine finishes working, the front and rear parts of the guided rocket are separated by a separation mechanism, and the direct injection tube range extender engine continues to provide flight power for the rocket. The guidance cabin communicates with the control cabin to transmit different guidance information to the control cabin. The control cabin communicates with the actuator and sends the generated trajectory correction control instructions to the actuator. The actuator is used to execute actions according to the control instructions to make the rocket fly until it hits the target. The direct injection range extender engine comprises an engine casing, an ignition device, a propellant and a thermal insulation layer; the engine casing is a cylindrical cavity, one end of which is closed, and a trumpet-shaped opening is provided on the end surface of the other end, with the large end facing rearward as the engine nozzle, and the direction of the opening is consistent with the axis direction of the engine casing; the propellant is arranged inside the engine casing, one end of which is connected to the ignition device, and the other end is in contact with the inner wall surface of the open end of the engine casing through the thermal insulation layer; a through hole is provided in the middle of the thermal insulation layer, which is connected to the trumpet-shaped opening; the other end of the engine casing extends out of the plane where the large end of the trumpet-shaped opening is located, and a stepped through hole is provided radially on the inner wall surface of the extended end; The separation mechanism includes a separation mechanism housing, a compression spring, a push plate and an explosive bolt; the separation mechanism housing is a cylindrical cavity with one end open, and a plurality of threaded holes are evenly distributed along the circumference on the inner wall of the cavity, and correspond to the positions of the stepped through holes, and are used to connect to the direct injection pipe extended range engine through the explosive bolts; the push plate is fixed to the closed end of the separation mechanism housing by the compression spring; the explosive bolt is used to be radially installed in the stepped through hole and the threaded hole to connect the separation mechanism to the direct injection pipe extended range engine; When the separation mechanism is fixedly connected to the direct injection pipe extended range engine, the compression spring is compressed and the push plate closes the nozzle outlet of the direct injection pipe extended range engine; when the explosive bolt acts, the separation mechanism is separated from the direct injection pipe extended range engine, the compression spring returns to its original length, and drives the push plate to push the separation mechanism away from the direct injection pipe extended range engine.

2. The detachable guided rocket for a 40mm bazooka according to claim 1, characterized in that: The actuator adopts an electric steering gear, a pulse engine, a maintenance component or a two-dimensional correction component.

3. The detachable guided rocket for a 40mm bazooka according to claim 1, characterized in that: The guidance cabin adopts a laser semi-active guidance head, an infrared guidance head, an image guidance head, a satellite receiver or an inertial guidance component.

4. The detachable guided rocket for a 40mm bazooka according to claim 1, characterized in that: The launching system adopts a tail fin and tail rod assembly or a launching engine equipped with propellant.

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