A smart weapon system for countering stealth targets and its guidance method

Abstract

The present invention discloses an intelligent weapon system and guidance method for countering hidden targets. The system includes a reconnaissance and guidance platform and a missile. The reconnaissance and guidance platform is a flying platform used to detect targets and land on or fly alongside them. The flying platform is equipped with a guidance signal source, an image detector, and a communication cable assembly. The reconnaissance and guidance platform communicates with a ground control station via a communication cable assembly. The image detector is used to detect the target's location. The guidance signal source is used to provide guidance signals to the missile. The missile is equipped with a detector and a guidance computer. The detector detects the guidance signal, and the guidance computer generates control instructions based on the guidance signal to control the missile's flight toward the target. This invention can accurately detect and strike hidden targets.

Description

Technical Field

[0001] This invention relates to the field of weapon system technology, specifically to an intelligent weapon system for countering stealth targets and its guidance method. Background Technology

[0002] In the battlefield, a concealed target refers to a target that is hidden behind obstacles such as bunkers or buildings, or that employs electronic defense measures such as electromagnetic interference, making it difficult for the attacker to detect or attack.

[0003] Based on the characteristics of concealed targets, when the attacker needs to attack concealed targets, it will face the following difficulties: (1) Difficulty in target detection: The target is hidden between bunkers and buildings, making it difficult for direct-view sighting devices to detect the target. Some concealed targets also have electronic jamming capabilities, interfering with equipment such as reconnaissance drones, making the target difficult to detect; (2) Difficulty in target attack: The target and the line of sight in the attack direction are blocked by buildings, and conventional target designators such as laser illuminators and radio radars cannot illuminate the target. Weapons using this type of guidance system cannot attack the target; (3) Difficulty in information transmission: The buildings between the target and the attacker have an obstructing effect on the wireless communication link, making it difficult to realize the control commands and information feedback between the reconnaissance / attack drone and the ground station.

[0004] In summary, in order to address the challenges of detection, attack, and information transmission when striking concealed targets, it is necessary to develop a weapon system capable of accurately detecting and striking concealed targets. Summary of the Invention

[0005] In view of this, the present invention provides an intelligent weapon system and guidance method for countering stealth targets, which can accurately detect and strike stealth targets.

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

[0007] A smart weapon system for countering stealth targets, comprising a reconnaissance and guidance platform and missiles;

[0008] The reconnaissance and guidance platform is a flight platform used to detect targets and land on or accompany them. The flight platform carries a guidance signal source, an image detector, and a communication cable assembly. The reconnaissance and guidance platform communicates with the ground control station via the communication cable assembly. The image detector is used to detect the location of the target. The guidance signal source is used to provide guidance signals for the missile.

[0009] The missile carries a detector and a guidance computer. The detector is used to detect the guidance signal, and the guidance computer generates control commands based on the guidance signal to control the missile to fly toward the target.

[0010] Furthermore, the flight platform is a quadcopter unmanned aerial vehicle, including a frame, power unit and control cabin;

[0011] The frame is a flat plate structure with a plate-shaped arm extending from each of the four corners. The power assembly is fixedly connected to each arm. The power assembly includes a motor and a propeller. The motor drives the propeller to generate lift. A control cabin is fixed to the upper surface of the frame and is fixedly connected to the guidance signal source. An image detector is fixed below the head of the frame, and a communication cable assembly is fixed at the bottom of the frame.

[0012] Furthermore, the quadcopter drone also includes a sound insulation component, which includes a sound insulation ring and a sound insulation ring mounting shell. The sound insulation ring is installed on the inner wall of the sound insulation ring mounting shell and is located around the power component. Both the sound insulation ring and the sound insulation ring mounting shell are hollow cylindrical, and the sound insulation ring is installed on the inner wall of the sound insulation ring mounting shell. The bottom end face of the sound insulation ring mounting shell is provided with a mounting arm, which is used to fix the sound insulation ring mounting shell to the drone arm.

[0013] Furthermore, the bottom of the control cabin is provided with threaded holes for fixing to the frame with screws; the front of the control cabin is a windward surface, and the rear end of the windward surface is provided with an electrical interface for connecting to the electrical interface on the guidance signal source; the upper rear end of the control cabin is provided with two guide rails for cooperating with the guide grooves provided on the guidance signal source; at the same time, the control cabin achieves mechanical connection with the guidance signal source through spring pins.

[0014] Furthermore, the guidance signal source adopts a laser analog light source, a laser irradiator, an infrared signal source, a radio signal source, or a satellite signal source; the lower end face of the guidance signal source is provided with two guide grooves and holes for insertion and engagement with spring pins.

[0015] Furthermore, the image detector includes a camera and a gimbal, with the gimbal rotatably mounted on the head of the control cabin and the camera rotatably mounted on the gimbal.

[0016] Furthermore, the communication cable assembly includes a communication cable, a cable compartment, and a cable dispenser;

[0017] The cable compartment includes a cable compartment base, a cable compartment shell, and a cable compartment cover. The cable compartment shell is a hollow cylindrical structure with one end semi-closed and the other end open. The open end is closed by the cable compartment cover, and the semi-closed end is connected to the cable compartment base via a bearing. The cable compartment base is fixed to the frame by screws. The opening at the semi-closed end allows the communication cable to extend out, pass through the cable compartment base, and connect to the control compartment. A cylinder is provided inside the cable compartment shell, and the communication cable is wound on it and extends out through a through hole on the wall of the cable compartment shell into the cable dispenser. The outer wall of the cable compartment shell is hinged to the cable dispenser, and the hinge is located at the through hole.

[0018] Furthermore, the wire feeder includes a wire feeder housing, a spring, a wire feeder cover, and a wire feeder clamp;

[0019] The cable feeder housing is a cylindrical structure open at one end, with a threaded inner wall at the open end, connected to the cable feeder cover via threads. The closed end has a through hole for the communication cable to enter. The cable feeder cover is a cylindrical structure open at both ends, with an annular boss on one end face for engaging with the open end of the cable feeder housing. The outer cylindrical wall of the cable feeder cover has a threaded surface for threaded connection with the inner wall of the cable feeder housing. A guide groove is formed on the inner wall of the cable feeder cover, and the guide groove is made of conductive material. The cable feeder clamp is a cylindrical structure placed inside the cable feeder cover. The cylinder has a through hole along its axial direction for the communication cable to pass through. A slider is provided on the outer circumference of the cylinder, which cooperates with the guide groove of the cable feeder cover to form a closed loop. An electromagnet clamp is provided on the outward-facing end face of the cylinder. The spring is placed inside the cable feeder housing, with one end fixed to the inner end face of the closed end of the cable feeder housing and the other end fixed to the inner end face of the cable feeder clamp.

[0020] Furthermore, the communication cable assembly includes a communication cable and a cable compartment. The communication cable is coated with non-curing adhesive and is wound around a cylinder inside the cable compartment. The communication cable extends from the upper end face and the outer peripheral face of the cable compartment and is electrically connected to the control compartment and the ground control station, respectively.

[0021] A method for guiding stealth targets, employing the aforementioned weapon system, with the guidance method as follows:

[0022] Step 1: The attacking side installs the selected guidance signal source onto the reconnaissance guidance platform;

[0023] Step 2: The attacking side deploys a reconnaissance and guidance platform, which uses an image detector to detect the location of the concealed target and transmits the image information to the ground control station via a communication cable assembly.

[0024] Step 3: The ground control station selects the concealed target to be attacked based on the returned image information and transmits the target image to the reconnaissance and guidance platform through the communication cable assembly;

[0025] Step 4: After receiving the image information of the target to be attacked, the reconnaissance and guidance platform flies towards the target and then lands on the target or flies alongside the target.

[0026] Step 5: The reconnaissance and guidance platform activates the guidance signal source, which then emits a guidance signal;

[0027] Step Six: The attacking side launches missiles;

[0028] Step 7: The missile detects the guidance signal emitted by the guidance signal source through the signal detector. The guidance computer generates control commands based on the guidance signal and controls the missile to fly towards the target.

[0029] Beneficial effects:

[0030] 1. This invention employs a distributed weapon system, utilizing a highly concealed and mobile reconnaissance and guidance platform to detect and designate targets, and then strikes targets with highly offensive missiles, thereby enhancing the ability to detect and strike concealed targets.

[0031] Secondly, the wired transmission method provides stronger anti-interference capabilities; since the cable is mounted on the reconnaissance and guidance platform, the platform can continue to fly even if the cable gets tangled in obstacles, making it more adaptable to complex combat environments.

[0032] 2. An adaptive closed-loop control scheme for the deployment speed of communication cables is adopted to ensure that the deployment speed of the cables matches the flight speed of the reconnaissance and guidance platform. This avoids both the obstruction of flight speed by the communication cables and the waste of working distance caused by the sagging of the communication cables.

[0033] 3. Soundproofing components were installed around the motor of the reconnaissance and guidance platform, which improved the platform's concealment during operation and thus enhanced its battlefield survivability. Attached Figure Description

[0034] Figure 1 This is a schematic diagram illustrating the working principle of the present invention;

[0035] Figure 2 This is a flowchart of the process of the present invention;

[0036] Figure 3(a) is a schematic diagram of the reconnaissance and guidance platform from an oblique upward view in this invention; Figure 3(b) is a schematic diagram of the reconnaissance and guidance platform from an oblique downward view in this invention; Figure 3(c) is an exploded view of the reconnaissance and guidance platform in this invention.

[0037] Figure 4 Exploded view of the power assembly;

[0038] Figure 5(a) is an external view of the control cabin, and Figure 5(b) is a top view of the control cabin;

[0039] Figure 6 This is a diagram of the external shape of the guiding signal source;

[0040] Figure 7 Exploded view of the control cabin and guidance signal source structure;

[0041] Figure 8 This is a schematic diagram of the structure in which the control cabin and guidance signal source work together.

[0042] Figure 9 This is a diagram of the image detector structure.

[0043] Figure 10 An exploded view of the communication cable assembly structure;

[0044] Figure 11 This is a structural diagram of the wire feeder housing;

[0045] Figure 12 This is a structural diagram of a wire-laying clamp;

[0046] Figure 13 Here is a structural diagram of the wire feeder cover;

[0047] Figure 14 This is a schematic diagram of the wire feeder structure;

[0048] Figure 15 Diagram of adaptive closed-loop control circuit for wire feeder;

[0049] Figure 16(a) is a structural diagram of the cable compartment housing II and the communication cable of the non-curing adhesive cable laying scheme, and Figure 16(b) is an exploded view of the cable compartment housing II and the communication cable of the non-curing adhesive cable laying scheme.

[0050] Among them, 1-frame, 2-power assembly, 3-soundproofing assembly, 4-control cabin, 5-guide signal source, 6-image detector, 7-communication cable assembly, 8-landing gear, 9-propeller, 10-motor, 11-soundproofing ring, 12-soundproofing ring mounting shell, 13-spring I, 14-pressure screw, 15-positioning pin, 16-pan-tilt head, 17-camera, 18-cable pod base, 19-bearing I, 20-cable pod shell I, 21-cable pod cover, 22-cable feeder shell, 23-spring II, 24-cable feeder clamp, 25-cable feeder cover, 26-communication cable, 27-bearing II, 28-cable pod shell II. Detailed Implementation

[0051] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0052] This invention provides an intelligent weapon system for countering stealth targets, such as... Figure 1 As shown, it includes a reconnaissance and guidance platform and missiles.

[0053] The reconnaissance and guidance platform is used to detect targets in the battlefield environment and transmit target information to the attacking side's ground control station. After the ground control station selects the target, the reconnaissance and guidance platform lands on the target or flies alongside the target. It uses a quadcopter UAV as the flight platform. The quadcopter UAV carries a guidance signal source 5, an image detector 6, and a communication cable assembly 7. The reconnaissance and guidance platform communicates with the ground control station via the communication cable assembly 7. The image detector 6 is used to detect the location of the target. The guidance signal source 5 is used to provide guidance signals for missiles. In addition to the above-mentioned quadcopter UAV form, the reconnaissance and guidance platform can also be in the form of an unmanned vehicle or a robot.

[0054] Specifically, in this embodiment, as Figures 3(a) to 3(c)As shown, the reconnaissance and guidance platform includes a frame 1, a power unit 2, a soundproofing unit 3, a control cabin 4, a guidance signal source 5, an image detector 6, and a communication cable assembly 7.

[0055] The frame 1 has a rectangular layout, with a rectangular flat plate structure in the middle, on which several screw holes are drilled for mounting the control compartment 4 and the communication cable assembly 7. A plate-shaped arm extends from each of the four corners of the rectangular flat plate structure, with four screw holes on each arm for mounting the power assembly 2, the sound insulation assembly 3, and the landing gear 8. The control compartment 4 is fixed to the upper surface of the frame 1, and the control compartment 4 is fixedly connected to the guidance signal source 5. The lower part of the head of the frame 1 is used to fix the image detector 6, and the bottom of the frame 1 is used to fix the communication cable assembly 7.

[0056] like Figure 4 As shown, the power unit 2 includes a motor 10 and a propeller 9. The motor 10 drives the propeller 9 to generate lift. The four motors 10 rotate at different speeds, resulting in different lift generated by the propellers 9, thereby enabling changes in the trajectory and attitude of the reconnaissance and guidance platform.

[0057] The sound insulation component 3 includes a sound insulation ring 11 and a sound insulation ring mounting shell 12. The sound insulation ring 11 is installed on the inner wall of the sound insulation ring mounting shell 12 and is located on the periphery of the power component 2. Both the sound insulation ring 11 and the sound insulation ring mounting shell 12 are hollow cylindrical. The sound insulation ring 11 is installed on the inner wall of the sound insulation ring mounting shell 12. The material of the sound insulation ring 11 is a sound insulation material, such as sound insulation foam, used to attenuate the sound generated when the motor 10 and the propeller 9 rotate, thereby improving the stealth of the reconnaissance and guidance platform. The bottom end face of the sound insulation ring mounting shell 12 is provided with a mounting arm, and one end of the mounting arm has a threaded hole. The sound insulation ring 11 mounting shell is fixed to the arm by screws.

[0058] The control cabin 4 contains a flight control computer, an inertial navigation system, and a power supply. The flight control computer controls the flight trajectory and attitude of the reconnaissance and guidance platform, the motion control of the gimbal 16 in the image detector 6, the timing control of the guidance signal source 5, the deployment rate control of the communication cable 26, and the reception and transmission of communication data. The inertial navigation system measures the acceleration and angular rate of the reconnaissance and guidance platform during flight, calculates its flight speed, trajectory, attitude angles, and other information, and transmits this information to the flight control computer. The power supply provides electrical power to all electrical components on the entire reconnaissance and guidance platform.

[0059] As shown in Figures 5(a) and 5(b), the control cabin 4 has threaded holes at its bottom, which are used to fix it to the frame 1 with screws; the front of the control cabin 4 is the windward side, and the rear end of the windward side has an electrical interface for connecting to the electrical interface on the guidance signal source 5; the upper rear end of the control cabin 4 has two guide rails for engaging with the guide grooves on the guidance signal source 5; simultaneously, the control cabin 4 achieves a mechanical connection with the guidance signal source 5 through spring pins. Figure 8As shown, the spring pin includes spring I13, pressure screw 14 and positioning pin 15. One end of the positioning pin 15 is provided with two limiting blocks, which are limited by pressure screw 14. Spring I13 is installed in the hole of control cabin 4. When the guidance signal source 5 is initially installed, spring I13 is pressed on the bottom surface of guidance signal source 5 until it enters the corresponding hole at the bottom of guidance signal source 5.

[0060] The guidance signal source 5 employs a laser analog light source, a laser illuminator, an infrared signal source, a radio signal source, or a satellite signal source; the connection between the guidance signal source 5 and the control cabin 4 uses a quick-connect design. Users can select the appropriate guidance signal source 5 based on their needs and quickly install the chosen source onto the reconnaissance and guidance platform. For example... Figure 6 As shown, the lower end face of the guidance signal source 5 has two guide grooves and holes for inserting and engaging with the spring pin. During installation, the user can first align the guide grooves of the guidance signal source 5 with the guide rail of the control cabin 4, and then push the guidance signal source 5 along the guide rail towards the control cabin 4. At this time, the positioning pin 15 is blocked by the lower end face of the guidance signal source 5, and the spring I 13 is in a compressed state. When the spring pin on the control cabin 4 aligns with the hole at the bottom of the guidance signal source 5, the positioning pin 15 disengages from the obstruction of the lower end face of the guidance signal source 5 and, under the thrust of the spring I 13, pushes into the hole at the bottom of the guidance signal source 5, thus fixing the guidance signal source 5 to the control cabin 4. Figure 7 , Figure 8 As shown.

[0061] like Figure 9 As shown, the image detector 6 includes a camera 17 and a gimbal 16. The gimbal 16 is mounted on the head of the control cabin 4 and can rotate relative to the control cabin 4. The camera 17 is mounted on the gimbal 16 and can rotate relative to the gimbal 16. Driven by the gimbal 16, the camera 17 can rotate to capture the battlefield environment and transmit the captured image information to the ground control station through the communication cable 26.

[0062] like Figure 10 As shown, the communication cable assembly 7 includes a communication cable 26, a cable compartment, and a cable dispenser.

[0063] Communication cable 26 connects the flight control computer in control cabin 4 to the ground control station and facilitates information exchange between the two.

[0064] The cable compartment includes a cable compartment base 18, a cable compartment shell I 20, and a cable compartment cover 21. The cable compartment shell I 20 is a hollow cylindrical structure with one end semi-closed and the other end open. The open end is closed by the cable compartment cover 21, and the semi-closed end is connected to the cable compartment base 18 via a bearing I 19. The cable compartment shell I 20 can rotate freely relative to the cable compartment base 18. The cable compartment base 18 is fixed to the frame 1 by screws. A through hole is opened on the side of the cable compartment base 18, which communicates with the hole in the cable compartment base 18 where the bearing I 19 is installed. The communication cable 26, extending from the opening at the semi-closed end, passes through the through hole on the cable compartment base 18 to the outside of the cable compartment base 18 and connects to the control compartment 4. A cylinder is provided inside the cable compartment shell I 20, on which the communication cable 26 is wound and extends through the through hole on the wall of the cable compartment shell I 20 into the cable dispenser. The outer wall of the cable compartment shell I 20 is hinged to the cable dispenser, and the hinge is located at the through hole. Hinge lugs are provided on both sides of the through hole.

[0065] The wire feeder includes a wire feeder housing 22, a spring II 23, a wire feeder cover 25, and a wire feeder clamp 24; such as Figure 11 As shown, the cable dispenser housing 22 is a cylindrical structure open at one end. The inner wall of the open end is threaded, and it is connected to the cable dispenser cover 25 via threads. The closed end has a through hole for the communication cable 26 to enter and a connecting hinge lug. It is connected to the hinge lug on the cable compartment housing I 20 via bearing II 27, ensuring that the cable dispenser housing 22 and the cable compartment housing I 20 can rotate with a single degree of freedom. Figure 13 As shown, the payer cover 25 is a cylindrical structure open at both ends. One end face has an annular boss for engaging with the open end of the payer housing 22. The outer cylindrical wall of the payer cover 25 is threaded for threaded connection with the inner wall of the payer housing 22. A guide groove is formed on the inner wall of the payer cover 25, and the guide groove portion is made of conductive material. Figure 12 As shown, the wire feeder clamp 24 is a cylindrical structure and is placed in the wire feeder cover 25. The cylinder has a through hole along its axial direction for the communication cable 26 to pass through. A slider is provided on the outer circumference of the cylinder, which cooperates with the guide groove of the wire feeder cover 25 to form a closed circuit. An electromagnet clamp is provided on the outward end face of the cylinder. The spring II 23 is placed in the wire feeder housing 22, with one end fixedly connected to the inner end face of the closed end of the wire feeder housing 22, and the other end fixedly connected to the inner end face of the wire feeder clamp 24.

[0066] By controlling the current flowing through the electromagnet, the friction between the electromagnet clamp and the communication cable 26 is controlled, thereby controlling the speed at which the communication cable 26 is laid out. The principle is as follows:

[0067] like Figure 14 and Figure 15As shown, since the slider on the wire feeder clamp 24 and the guide groove on the wire feeder cover 25 form a closed loop, when the slider is in different positions in the guide groove, according to the resistance law, the resistance value connected in the closed loop is also different, resulting in different voltage values ​​connected in parallel with the resistor, which in turn causes different currents through the electromagnet clamp, resulting in different electromagnet attraction forces, and thus different pressures exerted by the electromagnet clamp on the communication cable 26. This allows for control of the friction between the electromagnet clamp and the communication cable 26. The greater the friction, the slower the wire feed speed; the smaller the friction, the faster the wire feed speed. When the reconnaissance and guidance platform's flight speed increases, a faster cable release speed is required. If the friction between the electromagnet clamp and the communication cable 26 is high at this time, the cable release clamp 24 will move towards the cable release nozzle under the pull of the cable. At this time, the resistance of the circuit increases, resulting in a larger voltage across the resistor. With the total voltage remaining constant, the voltage across the electromagnet decreases. According to Ohm's law, the current through the electromagnet also decreases, the electromagnet's attraction force decreases, the friction between the electromagnet clamp and the communication cable 26 decreases, and the cable release speed increases. When the reconnaissance and guidance platform's flight speed decreases... The cable feeding speed needs to be slowed down, otherwise the cable will sag under gravity, resulting in wasted cable length. If the friction between the electromagnet clamp and the communication cable 26 is small at this time, the cable feeding clamp 24 will move away from the cable feeder opening under the pull of the spring II 23. At this time, the resistance of the circuit decreases, and the voltage across the resistor is smaller. With the total voltage remaining unchanged, the voltage across the electromagnet increases. According to Ohm's law, the current through the electromagnet also increases, the electromagnet's attraction force increases, the friction between the electromagnet clamp and the communication cable 26 increases, and the cable feeding speed slows down.

[0068] In addition to the electromechanical cable laying scheme described above, the cable laying device can also be installed without the cable laying device assembly, as shown in Figures 16(a) and 16(b). The communication cable assembly includes a communication cable 26 and a cable compartment. The cable compartment includes a cable compartment seat 18, a cable compartment housing II 28, and a cable compartment cover 21. The cable compartment housing II 28 is a hollow cylindrical structure with one end semi-closed and the other end open. The open end is closed by the cable compartment cover 21, and the semi-closed end is connected to the cable compartment seat 18 through a bearing I 19. The cable compartment housing II 28 can rotate freely relative to the cable compartment seat 18. The cable compartment seat 18 is fixed to the frame 1 by screws. The opening at the semi-closed end allows the communication cable 26 to extend out, pass through the cable compartment seat 18, and connect to the control compartment 4 electrically. A cylinder is provided inside the cable compartment housing II 28, on which the communication cable 26 is wound and extends directly through the through hole on the wall of the cable compartment housing II 28. Simultaneously, a non-curing adhesive is applied to the cable to increase cable feeding damping. In this solution, the non-curing adhesive remains viscous for a certain period, allowing the cable to be fed freely. Furthermore, the adhesive properties of the non-curing adhesive create damping between the cables, preventing them from sag under their own weight and avoiding wasted cable length. While this cable feeding solution cannot achieve adaptive closed-loop control like a cable feeder assembly, it is simpler in structure and lower in cost.

[0069] The missile carries a signal detector and a guidance computer. The type of the signal detector matches the type of guidance signal source 5 on the reconnaissance and guidance platform. The signal detector can detect or receive the guidance signals emitted by guidance signal source 5 and transmit them to the guidance computer. The guidance computer can generate flight control commands based on the guidance signals detected by the signal detector to control the missile to fly towards the target.

[0070] like Figure 2 As shown, the guidance method is as follows:

[0071] Step 1: The attacking side selects guidance signal source 5 according to operational requirements and installs the selected guidance signal source 5 on the reconnaissance guidance platform;

[0072] Step 2: The attacking side deploys a reconnaissance and guidance platform. The reconnaissance and guidance platform deploys communication cable 26 through communication cable assembly 7 and adaptively adjusts the deployment speed of communication cable 26 according to the flight speed. The reconnaissance and guidance platform uses image detector 6 to detect the location of the concealed target and transmits the image information to the ground control station through communication cable 26.

[0073] Step 3: The ground control station selects the concealed target to be attacked based on the returned image information and transmits the target image to the reconnaissance and guidance platform through communication cable 26;

[0074] Step 4: After receiving the image information of the target to be attacked, the reconnaissance and guidance platform flies towards the target and then lands on the target or flies alongside the target.

[0075] Step 5: The reconnaissance and guidance platform activates guidance signal source 5, which emits a guidance signal;

[0076] Step Six: The attacking side launches missiles;

[0077] Step 7: The missile detects the guidance signal emitted by guidance signal source 5 through the signal detector. The guidance computer on the missile generates control commands based on the guidance signal and controls the missile to fly towards the target.

[0078] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An intelligent weapon system for countering stealth targets, characterized in that, Including reconnaissance and guidance platforms and missiles; The reconnaissance and guidance platform is a flight platform used to detect targets and land on or accompany them. The flight platform carries a guidance signal source, an image detector, and a communication cable assembly. The reconnaissance and guidance platform communicates with the ground control station via the communication cable assembly. The image detector is used to detect the location of the target. The guidance signal source is used to provide guidance signals for the missile. The missile is equipped with a detector and a guidance computer. The detector is used to detect the guidance signal, and the guidance computer generates control commands based on the guidance signal to control the missile to fly toward the target. The communication cable assembly includes a communication cable, a cable compartment, and a cable dispenser. The cable compartment includes a cable compartment base, a cable compartment shell, and a cable compartment cover. The cable compartment shell is a hollow cylindrical structure with one end semi-closed and the other end open. The open end is closed by the cable compartment cover, and the semi-closed end is connected to the cable compartment base via a bearing. The cable compartment base is fixed to the frame by screws. The opening at the semi-closed end allows the communication cable to extend out, pass through the cable compartment base, and connect to the control compartment. A cylinder is provided inside the cable compartment shell, on which the communication cable is wound and extends through a through hole on the wall of the cable compartment shell into the cable dispenser. The outer wall of the cable compartment shell is hinged to the cable dispenser, and the hinge is located at the through hole. The wire feeder includes a wire feeder housing, a spring, a wire feeder cover, and a wire feeder clamp. The wire feeder housing is a cylindrical structure open at one end, with a threaded inner wall at the open end, which is threaded to the wire feeder cover. The closed end has a through hole for the communication cable to enter. The wire feeder cover is a cylindrical structure open at both ends, with an annular boss on one end face for engaging with the open end of the wire feeder housing. The outer cylindrical wall of the wire feeder cover is threaded for threaded connection with the inner wall of the wire feeder housing. The inner wall has a guide groove, which is made of conductive material. The wire feeder clamp is a cylindrical structure placed in the wire feeder cover. The cylinder has a through hole along its axial direction for the communication cable to pass through. A slider is provided on the outer circumference of the cylinder, which cooperates with the guide groove of the wire feeder cover to form a closed circuit. An electromagnet clamp is provided on the outward end face of the cylinder. The spring is placed in the wire feeder housing, with one end fixed to the inner end face of the closed end of the wire feeder housing and the other end fixed to the inner end face of the wire feeder clamp.

2. The anti-stealth target intelligent weapon system as described in claim 1, characterized in that, The flight platform is a quadcopter unmanned aerial vehicle, including a frame, power unit and control cabin; The frame is a flat plate structure with a plate-shaped arm extending from each of the four corners. The power assembly is fixedly connected to each arm. The power assembly includes a motor and a propeller. The motor drives the propeller to generate lift. A control cabin is fixed to the upper surface of the frame and is fixedly connected to the guidance signal source. An image detector is fixed below the head of the frame, and a communication cable assembly is fixed at the bottom of the frame.

3. The anti-stealth target intelligent weapon system as described in claim 2, characterized in that, The quadcopter drone also includes a sound insulation component, which includes a sound insulation ring and a sound insulation ring mounting shell. The sound insulation ring is installed on the inner wall of the sound insulation ring mounting shell and is located around the power component. Both the sound insulation ring and the sound insulation ring mounting shell are hollow cylindrical. The sound insulation ring is installed on the inner wall of the sound insulation ring mounting shell. The bottom end face of the sound insulation ring mounting shell is provided with a mounting arm, which is used to fix the sound insulation ring mounting shell to the drone arm.

4. The anti-stealth target intelligent weapon system as described in claim 2, characterized in that, The bottom of the control cabin is provided with threaded holes for fixing to the frame with screws; the front of the control cabin is the windward side, and the rear end of the windward side is provided with an electrical interface for connecting to the electrical interface on the guidance signal source; the upper rear end of the control cabin is provided with two guide rails for cooperating with the guide grooves on the guidance signal source; at the same time, the control cabin achieves mechanical connection with the guidance signal source through spring pins.

5. The anti-stealth target intelligent weapon system as described in claim 4, characterized in that, The guidance signal source adopts a laser analog light source, a laser irradiator, an infrared signal source, a radio signal source, or a satellite signal source; the lower end face of the guidance signal source is provided with two guide grooves and holes for insertion and engagement with spring pins.

6. The anti-stealth target intelligent weapon system as described in claim 2, characterized in that, The image detector includes a camera and a pan-tilt unit. The pan-tilt unit is rotatably mounted on the head of the control cabin, and the camera is rotatably mounted on the pan-tilt unit.

7. The anti-stealth target intelligent weapon system as described in claim 1, characterized in that, The communication cable assembly includes a communication cable and a cable compartment. The communication cable is coated with non-curing adhesive and is wound around a cylinder inside the cable compartment. The communication cable extends from the upper end face and the outer peripheral face of the cable compartment and is electrically connected to the control compartment and the ground control station, respectively.

8. A method for guiding stealth targets, characterized in that, Using the weapon system as described in claim 1, the guidance method is as follows: Step 1: The attacking side installs the selected guidance signal source onto the reconnaissance guidance platform; Step 2: The attacking side deploys a reconnaissance and guidance platform, which uses an image detector to detect the location of the concealed target and transmits the image information to the ground control station via a communication cable assembly. Step 3: The ground control station selects the concealed target to be attacked based on the returned image information and transmits the target image to the reconnaissance and guidance platform through the communication cable assembly; Step 4: After receiving the image information of the target to be attacked, the reconnaissance and guidance platform flies towards the target and then lands on the target or flies alongside the target. Step 5: The reconnaissance and guidance platform activates the guidance signal source, which then emits a guidance signal; Step Six: The attacking side launches missiles; Step 7: The missile detects the guidance signal emitted by the guidance signal source through the signal detector. The guidance computer generates control commands based on the guidance signal and controls the missile to fly towards the target.

Images