Disc type folding cruise missile ammunition suitable for dense loading of large caliber rocket projectiles

Abstract

This invention relates to a disc-type folding loitering munition suitable for dense loading of large-caliber rockets, and pertains to the field of unmanned aerial vehicle (UAV) technology. It includes a mother missile, loitering munition bodies, a deceleration parachute, and a partition plate. The mother missile serves as the delivery carrier for the loitering munition bodies, responsible for long-range delivery. The loitering munition bodies are densely loaded in rows within the mission payload compartment of the mother missile, and are isolated and protected by the partition plate. The deceleration parachute is installed on the loitering munition body to decelerate the munitions after release, enabling them to reach normal operating speed. The loitering munition bodies of this invention can be densely loaded onto the mother missile, forming a swarm of loitering munitions after deployment, increasing firepower density and improving combat effectiveness. It is also suitable for loading large-caliber rockets, reducing onboard space occupation and improving usability. Furthermore, the tilt-rotor technology enhances the flight maneuverability of the loitering munitions.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a disc-shaped folding loitering submunition suitable for dense loading of large-caliber rockets. Background Technology

[0002] With the development of loitering munition technology, capabilities such as reconnaissance-strike integration, precision strikes, and swarm networking have gradually matured. For long-range strikes in complex battlefield scenarios, loitering munitions need to possess long-range precision delivery and excellent battlefield mobility, as well as low-altitude loitering capabilities in complex environments. Currently, the loitering munition systems deployed in combat by various countries are mainly fixed-wing loitering munitions, which suffer from problems such as high cruising speed, poor maneuverability, and large flight target size, making them difficult to adapt to the loitering combat requirements in complex environments. Rotary-wing loitering munition systems have overcome the problems of high maneuverability and low-altitude loitering in complex environments to some extent, but they still have drawbacks such as limited control range, short endurance, and limited payload.

[0003] Taking into account operational requirements and the current state of loitering munition research, the use of rotor loitering submunitions densely loaded with large-caliber rockets has become a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a disc-type folding loitering submunition suitable for dense loading of large-caliber rockets. The loitering submunition body can be densely loaded on the parent rocket, forming a swarm of loitering munitions after deployment, which increases the firepower density and improves the combat effectiveness. It can also be used for loading of large-caliber rockets, reducing the space occupied on the rocket and improving ease of use. Furthermore, the use of tilt rotor technology improves the flight maneuverability of the loitering submunition.

[0005] To achieve the above objectives, the present invention provides a disc-type folding loitering munition suitable for dense loading of large-caliber rockets, comprising: a mother rocket, loitering munition bodies, a deceleration parachute, and a partition plate; the mother rocket serves as the delivery carrier for the loitering munition bodies, responsible for long-range delivery of the loitering munitions; the loitering munition bodies are densely loaded in rows within the mission payload compartment of the mother rocket, and the partition plate isolates and protects the loitering munition bodies; the deceleration parachute is installed on the loitering munition bodies to decelerate the munitions after release, enabling the loitering munition bodies to reach normal operating speed.

[0006] Furthermore, the loitering submunition body includes an airframe structure, an electrical system, a power system, and a mission payload; the electrical system and the mission payload are both located inside the airframe structure, with the mission payload located at the center of the airframe structure and the electrical system arranged around the mission payload; the power system is installed on the airframe structure and is electrically connected to the electrical system.

[0007] Furthermore, the fuselage structure includes a cabin, a fuselage partition, and fuselage arms; the cabin is enclosed by a bottom plate and a top cover; the fuselage partition is located inside the cabin and is used to separate the electrical system from the mission payload; multiple fuselage arms are provided and are evenly distributed around the perimeter of the cabin.

[0008] Furthermore, the fuselage structure also includes an arm turning mechanism, through which the cabin is connected to the arm.

[0009] Furthermore, the boom turning mechanism includes a body connecting frame, a boom sleeve, a tension spring, a tension spring positioning shaft, and a check mechanism; the body connecting frame is fixedly connected to the base plate, the boom sleeve is fixedly connected to the boom, a tension spring is connected to one side of the inner wall of the body connecting frame, one end of the tension spring positioning shaft is connected to the tension spring, and the other end extends out of the body connecting frame; one side of the boom sleeve is hinged to the body connecting frame, and the other end is connected to the check mechanism, and a locking mechanism is connected to the convex shaft of the check mechanism on the tension spring positioning shaft.

[0010] Furthermore, the electrical system includes an image and data transmission data link, an IMU circuit board, a flight controller, a lithium-ion battery, a power management baseboard, a satellite positioning module, a camera, and an external interface. The image and data transmission data link, IMU circuit board, and satellite positioning module are connected to the flight controller via serial cables or pin headers to transmit data and receive power. The lithium-ion batteries are divided into four groups and connected to the power management baseboard, which supplies power to both the power system and the electrical system. The camera is fixed to the outer wall of the baseboard and connected to the image and data transmission data link and the flight controller to sense external image information. The external interface is connected to the baseboard for exchanging data with external devices, facilitating debugging and testing.

[0011] Furthermore, the power system includes a brushless motor, a propeller, an electronic speed controller, a motor base, and a torsion servo. The motor base is connected to the arm via a connecting sleeve. The brushless motor is fixed to the motor base, and the propeller is fixed to the shaft of the brushless motor via a propeller clamp. The electronic speed controller is fixed to the power management base plate and connected via a power cable. The torsion servo is built into the arm and fixed with bolts, driving the motor and propeller to tilt around the arm axis, generating thrust with variable direction. The electronic speed controller is powered by the power management base plate and receives control signals from the flight controller.

[0012] The beneficial effects of this invention are as follows:

[0013] This invention provides a disc-type folding loitering submunition suitable for dense loading of large-caliber rockets. The loitering submunition body can be densely loaded on the parent rocket, forming a swarm of loitering munitions after deployment, which increases firepower density and improves combat effectiveness. In addition, the loitering submunition adopts a foldable arm that can be used for loading large-caliber rockets, reducing the space occupied on the rocket and improving ease of use. Furthermore, by designing a variable propulsion tilt rotor power system, the flight maneuverability of the loitering submunition is improved. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of the present invention;

[0015] Figure 2 This is a schematic diagram of the structure of the partition plate of the present invention;

[0016] Figure 3 This is a three-dimensional structural diagram of the present invention;

[0017] Figure 4 This is a top view of the loitering submunition body of the present invention;

[0018] Figure 5 This is a front view of the loitering submunition body of the present invention;

[0019] Figure 6 This is a side view of the loitering submunition body of the present invention;

[0020] Figure 7 This is a schematic diagram of the installation structure of the electrical system of the present invention;

[0021] Figure 8 This is a schematic diagram of the power system of the present invention;

[0022] Figure 9 This is a state diagram of the power system of the present invention;

[0023] Figure 10 This is a diagram showing the state of the arm turning mechanism of the present invention when it is folded.

[0024] Figure 11 This is a diagram showing the state of the arm turning mechanism of the present invention when it is deployed;

[0025] Figure 12 This is a trajectory diagram of the loitering submunition of the present invention.

[0026] In the figure:

[0027] 1-Paragon, 2-Loitering Submunition Body, 3-Deceleration Parachute, 4-Separation Plate; 2-1-Airframe Structure; 2-2-Electrical System; 2-3-Power System; 2-4-Arm Twisting Mechanism; 2-5-Mission Payload; 2-1-1-Base Plate; 2-1-2-Top Cover; 2-1-3-Airframe Separation Plate; 2-1-4-Arm; 2-2-1-Data Link for Image and Data Transmission; 2-2-2-IMU Circuit Board; 2-2-3-Flight Controller; 2-2-4-Lithium-ion Battery; 2-2 -5-Power management base plate; 2-2-6-Satellite positioning module; 2-2-7-Camera; 2-2-8-External interface; 2-3-1-Brushless motor; 2-3-2-Propeller; 2-3-3-Electronic speed controller; 2-3-4-Motor base; 2-3-5-Torsion servo; 2-3-6-Connecting sleeve; 2-4-1-Airframe connecting frame; 2-4-2-Arm sleeve; 2-4-3-Tension spring; 2-4-4-Tension spring positioning shaft; 2-4-5-Check mechanism. Detailed Implementation

[0028] To achieve the above objectives and effects, the technical means and structure adopted by the present invention will be described in detail with reference to the accompanying drawings, focusing on the features and functions of the preferred embodiments of the present invention.

[0029] This invention comprehensively considers operational requirements and the current state of loitering munition research, employing a large-caliber rocket-propelled, densely packed rotor-wing loitering munition. The loitering munition folds to fit the shape of the large-caliber rocket's magazine, and after being ejected, it undergoes a "munition-machine" conversion, enabling it to maneuver and loiter over the battlefield. The rocket delivers the loitering munition over a long distance, releasing multiple rotor-wing loitering munitions via a scattering method. This compensates for the shortcomings of rotor-wing loitering munitions in terms of endurance, control range, and payload, responding to the requirements of long-range loitering reconnaissance and strike operations.

[0030] like Figure 1-12 As shown, this invention provides a disc-type folding loitering munition suitable for dense loading of large-caliber rockets, comprising: a mother rocket 1, loitering munition bodies 2, a deceleration parachute 3, and a partition plate 4; the mother rocket 1 is the delivery carrier for the loitering munition bodies 2, responsible for the long-distance delivery of the loitering munitions; the loitering munition bodies 2 are densely loaded in rows within the mission payload compartments 2-5 of the mother rocket 1, and are isolated and protected by the partition plate 4; the deceleration parachute 3 is installed on the loitering munition bodies 2 to decelerate the munitions after release, enabling the loitering munition bodies 2 to reach a working speed that allows for safe deployment and flight.

[0031] In this embodiment, the loitering submunition body 2 includes an airframe structure 2-1, an electrical system 2-2, a power system 2-3, and a mission payload 2-5. The electrical system 2-2 and the mission payload 2-5 are both located inside the airframe structure 2-1. The airframe structure 2-1 adopts a disc-shaped shape to adapt to the loading requirements of large-caliber rockets. The mission payload 2-5 is located in the center of the airframe structure 2-1, and the electrical system 2-2 is arranged around the mission payload 2-5. The power system 2-3 is installed on the airframe structure 2-1 and is connected to the electrical system 2-2 through a power supply line and a control signal line.

[0032] The fuselage structure 2-1 includes a cabin, a fuselage partition plate 2-1-3, and fuselage arms 2-1-4. The cabin is enclosed by a bottom plate 2-1-1 and a top cover 2-1-2. The fuselage partition plate 2-1-3 is located inside the cabin and is used to separate the electrical system 2-2 from the mission payload 2-5, thereby achieving the encapsulation of the fuselage structure 2-1 and facilitating the replacement and maintenance of the mission payload 2-5. Multiple fuselage arms 2-1-4 are provided and are evenly distributed around the perimeter of the cabin.

[0033] The fuselage structure 2-1 also includes an arm turning mechanism 2-4, and the cabin is connected to the arm 2-1-4 through the arm turning mechanism 2-4. The boom turning mechanism 2-4 includes a body connecting frame 2-4-1, a boom sleeve 2-4-2, a tension spring 2-4-3, a tension spring positioning shaft 2-4-4, and a check mechanism 2-4-5. The body connecting frame 2-4-1 is fixedly connected to the base plate 2-1-1, and the boom sleeve 2-4-2 is fixedly connected to the boom 2-1-4. A tension spring 2-4-3 is connected to one side of the inner wall of the body connecting frame 2-4-1. One end of the tension spring positioning shaft 2-4-4 is connected to the tension spring 2-4-3, and the other end extends out of the body connecting frame 2-4-1. One side of the boom sleeve 2-4-2 is hinged to the body connecting frame 2-4-1, and the other end is connected to the check mechanism 2-4-5. A convex shaft for locking the check mechanism 2-4-5 is connected to the tension spring positioning shaft 2-4-4. Tension spring 2-4-3 is fixed to tension spring positioning shaft 2-4-4, providing elastic force to the stop mechanism 2-4-5. This positions the convex shaft on tension spring positioning shaft 2-4-4 at one end of the slot in the stop mechanism 2-4-5, preventing the arm sleeve 2-4-2 from springing back after unfolding. When folding, simply press one end of tension spring positioning shaft 2-4-4 that extends out of the body connecting frame 2-4-1.

[0034] The electrical system 2-2 includes a data transmission link 2-2-1, an IMU circuit board 2-2-2, a flight controller 2-2-3, a lithium-ion battery 2-2-4, a power management baseboard 2-2-5, a satellite positioning module 2-2-6, a camera 2-2-7, and an external interface 2-2-8. The data transmission link 2-2-1, the IMU circuit board 2-2-2, and the satellite positioning module 2-2-6 are connected to the flight controller 2-2-3 via serial cables or pin headers to transmit data and obtain power. The IMU circuit board is responsible for sensing the missile's attitude and acceleration information, and the satellite positioning module is responsible for acquiring the loitering munition's real-time position information for navigation fusion. Device 2-2-3 is responsible for fusing and summarizing information from multiple sensors and outputting control signals for multiple motors and servos. Due to space constraints, lithium-ion batteries 2-2-4 are divided into four groups and connected to the power management base plate 2-2-5. The power management base plate 2-2-5 supplies power to the power system 2-3 and the electrical system 2-2. Camera 2-2-7 is fixed on the base plate 2-1-1 to sense external image information. This camera is connected to the image data transmission link 2-2-1 and the flight controller 2-2-3 via a serial cable, and is responsible for sending image information and acquiring camera trigger signals, respectively. External interface 2-2-8 is connected to the base plate 2-1-1 for connecting and exchanging data with external devices, facilitating debugging and testing.

[0035] The power system 2-3 includes a brushless motor 2-3-1, a propeller 2-3-2, an electronic speed controller 2-3-3, a motor base 2-3-4, and a torsion servo 2-3-5. The motor base 2-3-4 is connected to the arm 2-1-4 via a connecting sleeve 2-3-6. The brushless motor 2-3-1 is fixed to the motor base 2-3-4. The propeller 2-3-2 is fixed to the shaft of the brushless motor 2-3-1 via a propeller clamp. The electronic speed controller 2-3-3 is fixed to the power management unit. The motor speed is adjusted by connecting the power cord to plate 2-2-5. The torsion servo 2-3-5, built into arm 2-1-4 and secured with bolts, generates the torsional torque of the arm, driving its axial rotation. This design facilitates blade arrangement in the folded state. The brushless motor 2-3-1, motor base 2-3-4, and propeller 2-3-2 are designed in an inverted configuration. The brushless motor 2-3-1 and propeller 2-3-2 can tilt around the axis of arm 2-1-4, generating thrust in variable direction. Figure 9 The diagram illustrates how the torsion servo 2-3-5 generates tilt thrust; the electronic speed controller 2-3-3 is powered through the power management base plate 2-2-5 and receives control signals from the flight controller 2-2-3.

[0036] refer to Figure 12Upon detecting an enemy target, a rocket densely loaded with this type of loitering munition is launched and flies to the target area. During flight, the loitering munitions are powered on, complete self-checks, and perform attitude alignment. At altitude H, the parent rocket sequentially releases multiple loitering munition bodies equipped with drag chute. When a loitering munition body detects free fall, it triggers a mechanical switch on the parachute, deploying the parachute to provide braking force. Simultaneously, the wings extend to complete the missile-machine interface transition. When the loitering munition body detects stable descent velocity, the system begins driving a brushless motor to provide lift and maintain stable attitude. After attitude stabilization, the connection between the drag chute and the loitering munition body is severed. The time from release to attitude stabilization is t1. Subsequently, the loitering munition body loiters at altitude h above the target for a loitering endurance time of t2, achieving high-speed, high-maneuverability flight through a tilt-shift propulsion system. The target position is observed via a downward-facing camera, and the first-person perspective image is transmitted to the ground station via a data link. Ground station operators analyze the data and send a confirmation attack command. The loitering munition body locks onto the target and descends to altitude h above the target. a The high-altitude top-attack guided attack has begun.

[0037] This invention provides a disc-type folding loitering munition suitable for dense loading of large-caliber rockets. The loitering munition body can be densely loaded onto the parent rocket, forming a swarm of loitering munitions after deployment, increasing firepower density and improving combat effectiveness. Furthermore, the loitering munition uses a foldable arm to accommodate large-caliber rocket loading, reducing onboard space occupation and improving usability. The variable-propulsion tilt rotor propulsion system enhances the loitering munition's flight maneuverability. It employs a two-layer airframe structure, with the electrical system mounted on the outer layer and the mission payload on the inner layer, facilitating the installation and replacement of cylindrical mission payloads. An inverted motor facilitates blade arrangement and prevents the blades from jamming when the arm folds. The arm is deployed and fixed in position in one go using elastic potential energy, reducing additional driving force and suitable for one-time arm turning. The rotor loitering munition, densely loaded with large-caliber rockets, has significant value and importance.

[0038] 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 disc-shaped folding loitering submunition suitable for dense loading of large-caliber rockets, characterized in that, include: The system comprises a mother missile, loitering submunition bodies, a deceleration parachute, and a partition plate. The mother missile serves as the delivery carrier for the loitering submunition bodies, responsible for long-range delivery. The loitering submunition bodies are densely packed in rows within the mission payload compartment of the mother missile, and are isolated and protected by the partition plate. The deceleration parachute is installed on the loitering submunition bodies to decelerate the submunitions after they are released, enabling the loitering submunition bodies to reach their normal operating speed. The loitering submunition body includes an airframe structure, an electrical system, a power system, and a mission payload. The airframe structure adopts a disc-shaped shape to accommodate the loading requirements of large-caliber rockets. The electrical system and mission payload are both located inside the airframe structure, with the mission payload located at the center of the airframe structure and the electrical system arranged around the mission payload. The power system is mounted on the airframe structure and is electrically connected to the electrical system. The airframe structure includes a cabin, an airframe partition, and airframe arms; the cabin is enclosed by a bottom plate and a top cover; the airframe partition is located inside the cabin and is used to separate the electrical system from the mission payload; multiple airframe arms are provided and are evenly distributed around the perimeter of the cabin. The fuselage structure also includes an arm turning mechanism, and the cabin is connected to the arm through the arm turning mechanism; The boom turning mechanism includes a body connecting frame, a boom sleeve, a tension spring, a tension spring positioning shaft, and a check mechanism. The body connecting frame is fixedly connected to the base plate, and the boom sleeve is fixedly connected to the boom. A tension spring is connected to one side of the inner wall of the body connecting frame. One end of the tension spring positioning shaft is connected to the tension spring, and the other end extends out of the body connecting frame. One side of the boom sleeve is hinged to the body connecting frame, and the other end is connected to the check mechanism. A convex shaft for locking the check mechanism is connected to the tension spring positioning shaft. Upon detecting the enemy target, a rocket densely loaded with this type of loitering munition is launched and flies to the target area. During flight, the loitering munitions are powered on, complete self-checks, and perform attitude alignment. At an altitude H, the parent rocket sequentially releases multiple loitering munition bodies equipped with drag chute. When a loitering munition body detects free fall, it triggers a mechanical switch on the parachute, deploying the drag chute to provide braking force to the loitering munition body. Simultaneously, the wings extend to complete the missile-machine transition. When the loitering munition body detects that the descent velocity has stabilized, the system begins to drive the brushless motor to provide lift and maintain a stable attitude. After attitude stabilization, the connection between the drag chute and the loitering munition body is severed. The time from release to attitude stabilization is t1. Subsequently, the loitering munition body loiters at an altitude h above the target for a loitering endurance time of t2, achieving high-speed, high-maneuverability flight through a tilt-shift propulsion system. The target position is observed through a downward-looking camera, and the first-person perspective image is transmitted to the ground station via a data link. Ground station operators analyze the data and send a confirmation attack command. The loitering munition body locks onto the target and descends to an altitude h above the target. a The high-altitude top-attack guided attack has begun.

2. The disc-shaped folding loitering submunition suitable for dense loading of large-caliber rockets as described in claim 1, characterized in that, The electrical system includes an image and data transmission data link, an IMU circuit board, a flight controller, lithium-ion batteries, a power management baseboard, a satellite positioning module, a camera, and external interfaces. The image and data transmission data link, IMU circuit board, and satellite positioning module are connected to the flight controller via serial cables or pin headers to transmit data and receive power. The lithium-ion batteries are divided into four groups and connected to the power management baseboard, which supplies power to both the power system and the electrical system. The camera is fixed to the outer wall of the baseboard and connected to the image and data transmission data link and the flight controller to sense external image information. The external interfaces are connected to the baseboard for exchanging data with external devices, facilitating debugging and testing.

3. A disc-shaped folding loitering submunition suitable for dense loading of large-caliber rockets as described in claim 2, characterized in that, The power system includes a brushless motor, a propeller, an electronic speed controller, a motor base, and a torsion servo. The motor base is connected to the arm via a connecting sleeve. The brushless motor is fixed to the motor base, and the propeller is fixed to the shaft of the brushless motor via a propeller clamp. The electronic speed controller is fixed to the power management base plate and connected via a power cable. The torsion servo is built into the arm and fixed with bolts, driving the motor and propeller to tilt around the arm axis, generating thrust with variable direction. The electronic speed controller is powered by the power management base plate and receives control signals from the flight controller.

Images