A towed hard-kill active protection weapon and its launching method

Abstract

The present invention provides a towed hard-kill active protection weapon, which includes a tow rope and a weapon body. The weapon body includes a directional warhead, a proximity fuse, a strapdown inertial navigation device, an electric servo and fins; the proximity fuse is used for operating insurance and releasing insurance after launch, and completing target detection; the directional warhead is used for generating fragments by explosion to destroy the incoming target; the strapdown inertial navigation device is used for measuring and calculating the attitude and position of the weapon body, and cooperating with the carrier aircraft to complete initial transfer alignment; the tow rope is used for providing the traction force of the carrier aircraft to the weapon body, and at the same time for the carrier aircraft to supply power to the weapon body and transmit various signals; the servo acts according to the control command transmitted from the carrier aircraft to generate a control force, causing the attitude of the weapon body to change; the fins are used for providing the aerodynamic force required for the flight and maneuver of the weapon body. The present invention is simple and reliable, has high safety, and enables the carrier aircraft to have the ability to destroy incoming targets from the rear for the first time.

Description

Technical Field

[0001] The present invention belongs to the technical field of air-based active protection weapons, and in particular relates to a towed hard-kill active protection weapon and a launching method thereof. Background Art

[0002] Hard-kill active protection weapons are commonly used as self-defense weapons for airborne platforms. Their primary purpose is to proactively destroy incoming targets and protect the carrier platform. Currently, carrier aircraft lack these weapons. This is primarily because incoming targets are fast, small, and often attack from behind. While conventional air-to-air missiles possess significant maneuverability, they lack the ability to quickly lock onto and quickly turn behind the carrier aircraft to intercept, lock onto, and destroy the incoming missile. Because these missiles have such low interception efficiency, carrier aircraft are rarely considered to possess hard-kill active protection capabilities.

[0003] It can be seen from this that currently known traditional air-based platforms have almost no active protection measures for hard kill. Summary of the Invention

[0004] The technical problem to be solved by the present invention is: the present invention proposes a towed hard-kill active protection weapon and a launching method, which has the characteristics of simplicity, reliability, high safety, small size, light weight and low cost, and can enable the carrier aircraft to have the ability to destroy the rear attacking targets for the first time.

[0005] The technical solution adopted by the present invention is: a towed hard-kill active protection weapon, comprising a towing rope and a weapon body, wherein the weapon body comprises a directional warhead, a proximity fuze, a strapdown inertial navigation device, an electric servo and wings;

[0006] The proximity fuze is used to operate the safety and release the safety after launch, and to complete target detection;

[0007] The directional warhead is used to explode and generate fragments to destroy the incoming target;

[0008] The strapdown inertial navigation unit is used to measure and calculate the weapon body's attitude and position, and to coordinate with the carrier aircraft to complete the initial transfer alignment;

[0009] The towing rope is used to provide the carrier aircraft with traction force to the weapon body, and is also used by the carrier aircraft to supply power to the weapon body and transmit various signals;

[0010] The servo operates according to the control instructions transmitted from the carrier aircraft, generates control force, and changes the posture of the weapon body;

[0011] The wings are used to provide the aerodynamic force required for the flight and maneuvering of the weapon body.

[0012] Further, when the proximity fuse detects that the target approaches the set distance and the attitude of the weapon body conforms to the regulations without threatening the safety of the carrier aircraft, the directional warhead is detonated.

[0013] Further, the directional warhead detonates both forwardly and circumferentially. Under static conditions, the angle between the fragment dispersion angle and the axis of the projectile body is not greater than 90 degrees.

[0014] Further, the various signals transmitted by the tow rope include the information required for transfer alignment sent by the carrier aircraft to the strapdown inertial navigation device of the weapon body, self-check instructions, servo control instructions, self-check return information of the weapon body, transfer alignment return information, start-up and navigation information of the strapdown inertial navigation device, and proximity fuse status information.

[0015] Further, the servo is an electric servo or a gas cylinder servo and includes control surfaces.

[0016] A launching method for a towed hard-kill active protection weapon, comprising:

[0017] In the initial state, the wings and control surfaces of the weapon body are folded and placed in the towed launcher of the carrier aircraft.

[0018] When the carrier aircraft flies to the danger zone, the carrier aircraft powers on the weapon body, and the weapon body completes self-check.

[0019] The carrier aircraft performs transfer alignment with the strapdown inertial navigation device in the maneuver control cabin and maintains the alignment state for pre-launch preparation.

[0020] When the carrier aircraft flies into the danger zone and detects an incoming target, the transfer alignment is terminated, the strapdown inertial navigation device is started, the firing data is set, and the weapon body is launched.

[0021] The weapon body uploads its own position and attitude information to the carrier aircraft in real time through the tow rope.

[0022] The carrier aircraft tracks the incoming target in real time and calculates the maneuvering commands for the weapon body in real time according to the incoming target information, the position and speed information of the carrier aircraft itself, and the position, speed, and attitude information of the weapon body.

[0023] When the distance between the weapon body and the carrier aircraft reaches the set distance a, the carrier aircraft starts to send control commands to the weapon body through the tow rope, causing the weapon body to move to the intermediate position between the incoming target and the carrier aircraft according to the maneuvering commands, and controlling the weapon body to block the incoming target.

[0024] When the weapon body is at a safe distance from the carrier aircraft and its attitude and control are normal, the proximity fuse is armed and starts to detect the incoming target; during the process of the proximity fuse detecting the incoming target, the weapon body moves according to the maneuvering commands of the carrier aircraft and always remains at the intermediate position between the incoming target and the carrier aircraft.

[0025] When the approaching target is detected by the proximity fuse inside the weapon projectile and is close to the effective damage distance of the directional warhead of the weapon projectile, and when it is determined that the attitude and control of the weapon projectile are normal and it does not pose a threat to the carrier aircraft, the proximity fuse detonates the directional warhead;

[0026] The directional warhead of the weapon projectile explodes, generating fragments to damage the approaching target and completing the operation.

[0027] Furthermore, the self-check information of the weapon projectile includes the servo communication feedback information, the proximity fuse communication feedback information, and the strapdown inertial navigation device communication and the initial information of the gyroscope and accelerometer.

[0028] Furthermore, the launching method further includes: if the weapon projectile gets out of control or other unexpected situations occur during the launching process, the carrier aircraft cuts off the tow rope and releases the weapon projectile.

[0029] The advantages of the present invention compared with the prior art are:

[0030] The towed hard-kill active protection weapon of the present invention can be specifically used to intercept targets behind the carrier aircraft. Since this hard-kill weapon is towed by the carrier aircraft and the flight direction is the same as that of the carrier aircraft, it can not use a rocket engine; it is powered by the tow rope of the carrier aircraft; it relies on the carrier aircraft to detect the target and receives the position and attitude information uploaded by this weapon through the tow rope, and generates control instructions on the fire control system of the carrier aircraft or a special fire control box. The towed hard-kill active protection weapon of the present invention has high interception efficiency and low cost, can utilize the existing towed decoy launching device of the carrier aircraft, and with minor modifications, can greatly improve the success probability of intercepting targets, and finally endows the carrier aircraft with the brand-new hard-kill target ability from scratch. Brief Description of the Drawings

[0031] Figure 1 It is a schematic diagram of the composition of the towed hard-kill active protection weapon of the present invention.

[0032] Figure 2 It is a schematic diagram of the principle of the towed hard-kill active protection weapon of the present invention. Detailed Embodiment

[0033] The following combines the drawings and gives embodiments to describe the present invention in detail.

[0034] As Figure 1 shown, a towed hard-kill active protection weapon includes a tow rope and a weapon projectile. The weapon projectile includes a directional warhead, a proximity fuse, a strapdown inertial navigation device, an electric servo, fins, and a structural member.

[0035] Among them:

[0036] The proximity fuse is used for daily operation insurance and post-launch insurance release, and to complete target detection. When the target approaches to a certain extent and the attitude of the weapon projectile complies with the regulations and does not pose a threat to the safety of the carrier aircraft, it detonates the directional warhead (the warhead detonates forward and circumferentially, and the angle between the fragment dispersion angle and the axis of the projectile body is no more than 90 degrees under static conditions);

[0037] The directional warhead is used to generate fragments by explosion to destroy the incoming target;

[0038] The strapdown inertial navigation device is used for measuring and calculating the attitude and position of the weapon projectile and, in cooperation with the carrier aircraft, to complete the initial transfer alignment;

[0039] The tow rope is used to provide traction force from the carrier aircraft to the weapon projectile, and is also responsible for power supply from the carrier aircraft to the weapon projectile and transmission of various signals (the signals include the information required for transfer alignment of the strapdown inertial navigation device sent from the carrier aircraft to the weapon projectile, self-check instructions, servo control instructions, self-check return information of the weapon projectile, transfer alignment return information, start-up and navigation information of the strapdown inertial navigation device, proximity fuse status information, etc.);

[0040] The servo is an electric servo or a gas cylinder servo, which includes control surfaces and can act according to the control instructions transmitted from the carrier aircraft to generate a control force to change the attitude of the weapon projectile (the control surfaces will generate the aerodynamic force required for the maneuver of the weapon projectile accordingly);

[0041] The control surfaces are used to provide the aerodynamic force required for the flight and maneuver of the weapon projectile;

[0042] The structural parts are used to complete the physical connection between the various components of this weapon;

[0043] As Figure 2 shown, the launch method of a towed hard-kill active protection weapon is as follows:

[0044] Normally, the control surfaces and fins of the weapon projectile are folded and placed in the towed launcher of the carrier aircraft;

[0045] When the carrier aircraft flies to the danger zone, the carrier aircraft powers on the weapon projectile, and the weapon projectile completes self-check (the self-check information includes the servo communication feedback information, proximity fuse communication feedback information, and strapdown inertial navigation device communication and initial information of the gyroscope and accelerometer);

[0046] Subsequently, the carrier aircraft conducts transfer alignment with the strapdown inertial navigation device in the maneuver control cabin and maintains the aligned state to make preparations for launch;

[0047] When the carrier aircraft flies into the danger zone and detects an incoming target, the transfer alignment is terminated, the strapdown inertial navigation device is started, the launch parameters are set, and then the weapon projectile is launched;

[0048] The weapon projectile uploads its own position and attitude information to the carrier aircraft in real time through the tow rope;

[0049] The carrier aircraft tracks the incoming target in real time, and calculates the maneuvering command of the weapon projectile in real time based on the information of the incoming target, the position and speed information of the carrier aircraft itself, and the position, speed, and attitude information of the weapon projectile;

[0050] When the weapon projectile is at a certain distance from the carrier aircraft, the carrier aircraft starts to send control instructions to it through the tow rope, so that the weapon projectile can move to the middle position between the incoming target and the carrier aircraft according to the maneuvering command, and controls the weapon

[0051] projectile to block the incoming target;

[0052] When the weapon projectile is far from the safe distance of the carrier aircraft and its attitude and control are normal, the proximity fuse is armed and starts to detect the incoming target; during the process of the proximity fuse detecting the incoming target, the weapon projectile moves according to the maneuvering command of the carrier aircraft and always stays at the middle position between the incoming target and the carrier aircraft;

[0053] 0 When the incoming target is detected by the proximity fuse in the weapon projectile and approaches the effective damage distance of the directional warhead of the weapon projectile, and it is judged that the attitude and control of the weapon projectile are normal and will not pose a threat to the carrier aircraft, the proximity fuse detonates the directional warhead;

[0054] The directional warhead of the weapon projectile explodes, generating high-speed fragments to damage the incoming target and complete the operation;

[0055] If the weapon projectile gets out of control or other accidents occur during the process, the carrier aircraft can cut off the tow rope and release the weapon projectile to ensure the safety of the carrier aircraft.

[0056] In summary, the above is only the preferred embodiment of the present invention and is not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0057] The parts not detailed in the present invention belong to the well-known technologies in the art.

[0058] The parts not detailed in the present invention belong to the well-known technologies in the art.

Claims

1. A launching method for a towed hard-kill active protection weapon, characterized in that Including: In the initial state, the weapon projectile's wings and control fins are folded and placed inside the carrier aircraft's towed launcher. When the carrier aircraft flies to before the dangerous area, the carrier aircraft powers on the weapon projectile, and the weapon projectile completes self-check. The carrier aircraft conducts transfer alignment with the strapdown inertial navigation device in the maneuver control cabin and maintains the alignment state for pre-launch preparation. When the carrier aircraft flies into the dangerous area and detects an incoming target, the transfer alignment ends, the strapdown inertial navigation device starts, the firing data is inputted, and the weapon projectile is launched. The weapon projectile real-time uploads its own position and attitude information to the carrier aircraft through the tow rope. The carrier aircraft real-time tracks the incoming target and calculates the maneuver command of the weapon projectile in real time according to the incoming target information, the carrier aircraft's own position and speed information, and the weapon projectile's position, speed, and attitude information. When the distance between the weapon projectile and the carrier aircraft reaches the set distance a, the carrier aircraft starts to send control commands to the weapon projectile through the tow rope, making the weapon projectile move to the middle position between the incoming target and the carrier aircraft according to the maneuver command, and controlling the weapon projectile to block the incoming target. When the weapon projectile is at a safe distance from the carrier aircraft and its attitude and control are normal, the proximity fuse is armed and starts to detect the incoming target; during the process of the proximity fuse detecting the incoming target, the weapon projectile moves according to the carrier aircraft's maneuver command and always stays at the middle position between the incoming target and the carrier aircraft. When the incoming target is detected by the proximity fuse inside the weapon projectile and is close to the effective damage distance of the directional warhead of the weapon projectile, and it is judged that the weapon projectile's attitude and control are normal and will not threaten the carrier aircraft, the proximity fuse detonates the directional warhead. The directional warhead of the weapon projectile explodes, generating fragments to damage the incoming target and complete the operation. The said towed hard-kill active protection weapon includes a tow rope and a weapon projectile. The weapon projectile includes a directional warhead, a proximity fuse, a strapdown inertial navigation device, an electric servo and wings. The said proximity fuse is used for arming and disarming after launch and completing target detection. The said directional warhead is used for generating fragments by explosion to destroy the incoming target. The said strapdown inertial navigation device is used for measuring and calculating the weapon projectile's attitude and position and cooperating with the carrier aircraft to complete the initial transfer alignment. The said tow rope is used to provide the traction force of the carrier aircraft to the weapon projectile, and at the same time is used for the carrier aircraft to supply power to the weapon projectile and transmit various signals. The said servo moves according to the control command sent down by the carrier aircraft, generating a control force to change the attitude of the weapon projectile. The wings are used to provide the aerodynamic force required for the weapon projectile to fly and maneuver.

2. The emission method according to claim 1, characterized in that, The self-check information of the said weapon projectile includes the servo communication feedback information, the proximity fuse communication feedback information, and the strapdown inertial navigation device communication and the initial information of the gyroscope and accelerometer.

3. The emission method according to claim 1, wherein Also including: If the weapon projectile gets out of control or other accidents occur during the launch process, the carrier aircraft cuts off the tow rope and releases the weapon projectile.

4. The emission method according to claim 1, characterized in that, The said proximity fuse detonates the directional warhead when the target approaches the set distance and the weapon projectile's attitude is compliant and will not threaten the safety of the carrier aircraft.

5. The emission method according to claim 1, wherein The said directional warhead detonates forward and circumferentially, and the included angle between the fragment scattering angle and the projectile axis is not more than 90 degrees under static conditions.

6. The emission method according to claim 1, characterized in that, The various signals transmitted by the drag rope include the information required for strapdown inertial navigation device transfer alignment sent by the carrier aircraft to the weapon projectile, self-check instructions, servo control instructions, weapon projectile self-check return information, transfer alignment return information, strapdown inertial navigation device startup and navigation information, and proximity fuse status information.

7. The emission method according to claim 1, wherein The servo is an electric servo or a gas cylinder servo and includes a rudder flap.

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