A gun-launched sub-munition flip accelerated attack rotorcraft assembly

Abstract

This invention discloses a gun-launched, tumble-and-accelerate rotor loitering munition assembly, relating to the field of smart munitions technology. It includes a mother munition, a cluster frame, and several rotor loitering munitions. The cluster frame is mounted within the mother munition, and the several rotor loitering munitions are mounted within the cluster frame. Each rotor loitering munition includes a body and a deceleration and spin-damping device. The deceleration and spin-damping device is mounted on the tail end of the body via explosive bolts. The body is cylindrical, with rectangular grooves arrayed on its surface. A folding mechanism is installed within these rectangular grooves and is hinged to the body. A payload compartment is located at the top of the body, and an electrical compartment is located at the bottom. The electrical compartment houses a control system, which is electrically connected to the folding mechanism. This invention can launch multiple rotor loitering munitions simultaneously, improving weapon launch efficiency. The deceleration and spin-damping device prevents the device from malfunctioning or becoming uncontrollable due to excessive descent or rotational speed of the loitering munitions.

Description

Technical Field

[0001] This invention belongs to the field of intelligent munitions technology, specifically relating to a rotor loitering munition component for artillery-launched mother-daughter type flip-up acceleration attack. Background Technology

[0002] A loitering munition is an information-based munition launched from existing weapon platforms, capable of loitering within a target area and performing various combat missions depending on its payload, including reconnaissance, location, surveillance, relay, jamming, decoy, damage, and damage assessment. It is highly effective against time-sensitive targets, reverse-slope targets, and targets operating in corridors.

[0003] Loitering munitions can be divided into fixed-wing loitering munitions and rotary-wing loitering munitions according to their layout. Rotary-wing loitering munitions have the advantage of better mobility compared to fixed-wing loitering munitions, and can flexibly cope with combat scenarios with dense obstacles.

[0004] Currently, rotary-wing loitering munitions typically employ folding motor arms to reduce their size, facilitating storage, transportation, and launch as projectiles, utilizing existing weapon platforms. During launch, the folded arms unfold, transforming the munition from projectile form to unmanned aerial vehicle (UAV) form. In the terminal guidance phase, the munition reverses the rotation of its motors and propellers during descent, generating thrust opposite to the lift produced during deployment. This results in an attack acceleration greater than g, increasing the munition's terminal guidance velocity.

[0005] Existing rotor loitering munition designs still have some problems: rotor loitering munitions are small in size, and launching only one loitering munition per launch results in low launch efficiency. During launch, some launch devices will cause the projectile to rotate in order to make the launched projectile more stable. The rotation of the loitering munition during launch is not conducive to the stable flight of the loitering munition after it is converted into a drone.

[0006] Therefore, how to provide a loitering munition assembly that employs a cannon-launched mother-daughter system and can launch multiple rotor loitering munitions at once with a flip-acceleration attack capability has become a problem that needs to be solved by those skilled in the art. Summary of the Invention

[0007] In view of this, the present invention provides a rotor loitering munition assembly for gun-launched mother-daughter type tumbler acceleration attack, which can effectively solve the problems in the background art.

[0008] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0009] A gun-launched, tumble-and-accelerate rotor loitering munition assembly includes a mother munition, a cluster frame, and several rotor loitering munitions. The cluster frame is mounted in the mother munition, and the several rotor loitering munitions are mounted in the cluster frame. Each rotor loitering munition includes a munition body, explosive bolts, and a deceleration and spin reduction device. The deceleration and spin reduction device is mounted on the tail end of the munition body via the explosive bolts. The munition body is cylindrical, and its surface is arrayed with rectangular grooves. A folding mechanism is disposed in the rectangular grooves and is hinged to the munition body. A payload compartment is disposed at the top of the munition body, and an electrical compartment is disposed at the bottom of the munition body. A control system is disposed in the electrical compartment and is electrically connected to the folding mechanism.

[0010] Furthermore, the folding mechanism includes a propeller, a connector, a motor, a projectile, and a folding arm. One end of the folding arm is hinged to the projectile, and the other end of the folding arm is equipped with a motor. The propeller is mounted on the connector, and the center of the connector is threadedly connected to the motor shaft.

[0011] Furthermore, it also includes a torsion spring, which is disposed at the hinge between the folding arm and the projectile, for the ejection and holding of the folding arm in place.

[0012] Furthermore, it also includes a battery compartment, which is located inside the missile body and is electrically connected to the electrical compartment.

[0013] Furthermore, the deceleration and anti-spin device includes a parachute compartment, a spring, a support plate, a parachute pack, and a parachute compartment cover. An explosive bolt is provided on the bottom outer end face of the parachute compartment. One end of the spring is located at the bottom of the parachute compartment, the support plate is located at the other end of the spring, the parachute pack is located on the support plate, and the parachute compartment cover is fixed to the top of the parachute compartment by the explosive bolt.

[0014] Furthermore, the bundle frame is symmetrically divided into left and right parts along the axial direction.

[0015] Furthermore, a constraint ring is provided on the outside of the cluster frame.

[0016] Furthermore, the top ends of the left and right sides of the cluster frame are provided with buckles.

[0017] Furthermore, the bundle frame is made of engineering plastic.

[0018] Furthermore, the payload bay can carry warheads, seekers, reconnaissance payloads, or electronic jamming payloads, depending on the mission.

[0019] The beneficial effects of this invention are as follows:

[0020] 1. This invention can be folded and loaded into the mother shell using a cluster frame, and can form a mother-daughter structure with shells of different types and sizes without the need for a new weapon launching device. At the same time, the mother-daughter structure allows the mother shell to carry multiple of the invention's devices, improving weapon launching efficiency.

[0021] 2. After the bundle frame separates from the mother projectile after it leaves the barrel, the present invention will trigger a deceleration and rotation reduction device to reduce the descent speed and rotation speed of the device, and prevent the device from going out of control or malfunctioning due to excessive descent or rotation speed.

[0022] 3. In the terminal guidance phase, the present invention can achieve large attitude maneuvers through the controller to make the projectile flip and make the propeller thrust direction face the target, thereby improving the projectile-target convergence speed during the terminal guidance process. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the main structure of the projectile of the present invention;

[0024] Figure 2 This is a side view of the projectile of the present invention;

[0025] Figure 3 This is a cross-sectional view of the projectile of the present invention;

[0026] Figure 4 This is a bottom view of the projectile of the present invention;

[0027] Figure 5 This is a schematic diagram of the folded state of the projectile of the present invention;

[0028] Figure 6 This is a schematic diagram of the bundle frame in its loaded state according to the present invention;

[0029] Figure 7 This is a schematic diagram of the cluster frame separating and releasing loitering munitions according to the present invention;

[0030] Figure 8 This is a schematic diagram of the loading of the mother missile of the present invention;

[0031] Figure 9 This is a top view of the deceleration and anti-rotation device of the present invention;

[0032] Figure 10 This is a side view of the deceleration and anti-rotation device of the present invention;

[0033] Figure 11 This is a cross-sectional view of the deceleration and anti-rotation device of the present invention;

[0034] Figure 12 This is a schematic diagram showing the connection between the projectile body and the deceleration and anti-spin device of the present invention;

[0035] Figure 13 This is a schematic diagram of a typical operational procedure for a rotary-wing loitering munition.

[0036] In the diagram: 1. Propeller; 2. Connector; 3. Motor; 4. Folding arm; 5. Torsion spring; 6. Missile body; 7. Electrical compartment; 8. Battery compartment; 9. Payload compartment; 10. Cluster frame; 11. Deceleration and spin reduction device; 12. Rotor-wing loitering munition; 13. Mother missile; 14. Parachute canopy; 15. Explosive bolt; 16. Parachute pack; 17. Support plate; 18. Compression spring; 19. Parachute compartment. Detailed Implementation

[0037] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0038] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "horizontal," "inner," "outer," and "one side," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0039] Example 1

[0040] like Figure 1-13 As shown, this embodiment discloses a rotor loitering munition assembly for artillery-launched mother-daughter type flip-over acceleration attack, including a mother munition 13, a cluster frame 10 and several rotor loitering munitions 12. The cluster frame 10 is loaded with rotor loitering munitions 12 and is loaded in the mother munition 13. After the mother munition 13 is launched from the weapon launch platform, the cluster frame 10 separates from the mother munition 13 and separates along the axial direction to release the rotor loitering munitions 12.

[0041] As a preferred embodiment of the present invention, the cluster frame 10 is equipped with three rotor loitering munitions 12. The cluster frame 10 can be made of engineering plastic or other rigid materials and is a hollow cylinder. It is divided into two symmetrical parts along the axial direction. When in use, the three rotor loitering munitions 12 are placed inside the cluster frame 10 and the two parts are combined into one. Before installation, a constraint ring (not shown) can be used to ensure that they do not separate. The constraint ring is removed after the mother munition is loaded. After the mother munition 13 is launched from the weapon launch platform, the cluster frame 10 separates from the mother munition 13. Since there is no external force to restrain it, the cluster frame 10 separates along the axial direction and scatters the three rotor loitering munitions 12.

[0042] The rotary loitering munition 12 includes a munition body 6 and a deceleration and spin reduction device 11. The munition body 6 is cylindrical, and four rectangular grooves are arranged in an array along the surface of the munition body 6. Four sets of folding mechanisms and torsion springs 5 ​​are arranged in the four rectangular grooves of the munition body 6. The folding mechanism includes a propeller 1, a connector 2, a motor 3, and a folding arm 4. The propeller 1 is connected through the connector 2. The middle of the connector 2 is threadedly connected to the motor shaft of the motor 3. When the propeller 1 is working, the thrust generated is upward. The motor 3 is bolted to one end of the folding arm 4. The other end of the folding arm 4 is set in the rectangular groove and connected to the munition body 6 through a rotating shaft and torsion spring 5. When the motor 3 is installed and working, the motor shaft faces downward.

[0043] The missile body 6 contains an electrical compartment 7, a battery compartment 8, and a payload compartment 9. The payload compartment 9 is located at the top of the missile body 6, while the electrical compartment 7 and the battery compartment 8 are located at the bottom of the missile body 6. The electrical compartment 7 contains a control system, and the motor 3, the payload compartment 9, and the battery compartment 8 are all electrically connected to the electrical compartment 7.

[0044] The payload compartment 9 can carry different types of mission payloads, such as different types of warheads and seekers, reconnaissance payloads, electronic jamming payloads, etc.

[0045] When the rotor loitering munition 12 attacks, the electrical compartment 7 will cause the rotor loitering munition 12 to flip, align the payload compartment 9 with the target, and the propeller 1 will generate thrust in the same direction as the line connecting the munition and the target. It will also increase the speed of the motor 3 to increase the speed of the munition meeting the target, so that the rotor loitering munition 12 can accelerate towards the target. During the flight, the rotor loitering munition 12 will adjust its attitude to track the target until the munition and the target meet.

[0046] The main body of the deceleration and anti-spin device 11 consists of a parachute compartment 19 and a parachute compartment cover 14. The parachute compartment 19 and the parachute compartment cover 14 are connected by explosive bolts. The lower end of the parachute compartment cover 14 is connected to the rotor loitering munition 12 by explosive bolts 15. The lower end of the compression spring 18 is fixedly connected to the bottom of the parachute compartment 19, and the upper end is fixedly connected to the bottom of the support plate 17. The compression spring 18 is in a compressed state before the deceleration and anti-spin device 11 is working. The parachute pack 16 is placed on the top of the support plate 17.

[0047] The deceleration and spin reduction device 11 operates after the rotor loitering munition 12 separates from the cluster frame 10, reducing the descent speed and rotation speed of the rotor loitering munition 12. The rotor loitering munition 12 separates from the deceleration and spin reduction device 11 when its flight speed and rotation speed are reduced to a certain level.

[0048] Before use, first fold the folding arm 4 of the rotor loitering munition 12 along the pivot and insert it into the corresponding rectangular groove of the munition body 2. Then, install the deceleration and spin reduction device 11 on the top of the three rotor loitering munitions 12 and load them into the cluster frame 10. Then, load the cluster frame 10 into the mother munition 13, which can be a munition of the same caliber as a 130 rocket or grenade.

[0049] When in use, the mother missile 13 is launched from the corresponding weapon launch platform. After the mother missile 13 reaches a certain altitude or flies a certain distance, it separates from the cluster frame 10 and turns on the power of the rotor loitering munition 12 and the cluster frame 10. Since there is no external force to restrain it, the cluster frame 10 separates into two parts along the axis and releases three rotor loitering munitions 12.

[0050] At this time, the deceleration and spin reduction parachute in the deceleration and spin reduction device 11 of the rotor loitering munition 12 is deployed, and the rotor loitering munition 12 begins to reduce its descent speed and rotation speed. When the speed is lower than the set speed, the deceleration and spin reduction device 11 cuts off the deceleration and spin reduction parachute and separates from the munition body 6.

[0051] The four folding arms 4 of the missile body 6 unfold under the action of torsion springs 5, and the four motors 3 start working under the control of the control system in the electrical compartment 7. The motors 3 drive the propellers 1 to rotate and generate upward thrust, which can overcome the gravity of the missile body 6. By adjusting the speed of the four propellers 1 through the control system, the missile body 6 can be controlled to hover or fly.

[0052] During the attack, the control system in the electrical compartment 7 controls the missile body 6 to perform large-attitude maneuvers to achieve a roll, so that the payload compartment 9 is aligned with the target, and the propeller 1 generates thrust in the same direction as the line connecting the missile and the target. At this time, the payload compartment 9 is usually equipped with a warhead and a seeker. Under the control of the control system in the electrical compartment 7, the speed of the four motors 3 reaches the limit, thereby increasing the speed of the missile-target convergence, so that the missile body 6 accelerates towards the target, and adjusts the attitude of the missile body 6 to track the target during the flight until the missile-target convergence.

[0053] Example 2

[0054] The difference between this embodiment and the previous embodiment is that the top ends of the left and right parts of the cluster frame 10 in this embodiment are provided with buckles, and the cluster frame 10 in this embodiment is connected by buckles without the need for constraint rings.

[0055] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the technical scope of the present invention. Therefore, any minor modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A rotor-borne loitering munition assembly for artillery-launched, cluster-type, tumble-and-accelerate attack, characterized in that: The system includes a mother missile, a cluster frame, and several rotor loitering munitions. The cluster frame is loaded in the mother missile, and the several rotor loitering munitions are loaded in the cluster frame. Each rotor loitering munition includes a missile body and a deceleration and spin reduction device. The deceleration and spin reduction device is installed at the tail end of the missile body by explosive bolts. The missile body is cylindrical, and its surface is arrayed with rectangular grooves. A folding mechanism is provided in the rectangular grooves and is hinged to the missile body. A payload compartment is provided at the top of the missile body, and an electrical compartment is provided at the bottom of the missile body. A control system is provided in the electrical compartment and is electrically connected to the folding mechanism. The folding mechanism includes a propeller, a connector, a motor, and a folding arm. One end of the folding arm is hinged to the projectile, and the other end of the folding arm is equipped with a motor. The propeller is mounted on the connector, and the center of the connector is threaded to the motor shaft. When the propeller is working, the thrust generated is upward. The motor is bolted to one end of the folding arm, and the other end of the folding arm is set in a rectangular groove and connected to the projectile through a rotating shaft and a torsion spring. When the motor is installed and working, the motor shaft faces downward. The motor drives the propeller to rotate and generate upward thrust, which can overcome the weight of the projectile. The control system adjusts the speed of each propeller to control the projectile to hover or fly. When the rotor loitering munition attacks, the electrical compartment will cause the rotor loitering munition to perform large-attitude maneuvers and flips, aligning the payload compartment with the target. The propeller will generate thrust in the same direction as the line connecting the munition and the target, and the motor speed will reach its limit to increase the speed at which the munition and the target meet. This will cause the rotor loitering munition to accelerate towards the target and adjust its attitude to track the target during flight until the munition and the target meet.

2. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 1, characterized in that, It also includes a torsion spring, which is located at the hinge between the folding arm and the projectile, and is used to extend and maintain the folding arm.

3. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 1, characterized in that, It also includes a battery compartment, which is located inside the missile body and is electrically connected to the electrical compartment.

4. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 1, characterized in that, The deceleration and anti-spinning device includes a parachute compartment, a spring, a support plate, a parachute pack, and a parachute compartment cover. An explosive bolt is provided on the bottom outer end face of the parachute compartment. One end of the spring is located at the bottom of the parachute compartment, the support plate is located at the other end of the spring, the parachute pack is located on the support plate, and the parachute compartment cover is fixed to the top of the parachute compartment by the explosive bolt.

5. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 1, characterized in that, The cluster frame is a hollow cylindrical structure, and it is symmetrically divided into left and right parts along the axial direction.

6. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 5, characterized in that, The bundle frame is provided with a constraint ring on its exterior.

7. A gun-launched, cluster-type, tumble-and-accelerate rotor-borne loitering munition assembly according to claim 5, characterized in that, The top ends of the left and right parts of the cluster frame are provided with buckles.

8. The gun-launched, cluster-type, tumble-and-accelerate rotor loitering munition assembly according to claim 1, characterized in that, The cluster frame is made of engineering plastic.

9. A gun-launched, cluster-type, tumble-and-accelerate rotor-borne loitering munition assembly according to claim 1, characterized in that, The payload bay carries warheads, seekers, reconnaissance payloads, or electronic jamming payloads, depending on the mission.

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