11 results about "Missile attack" patented technology

The invention relates to the technical field of intelligent ammunition, and discloses a coaxial multi-rotor patrol ammunition which comprises an integrated control part, an ammunition body part and an integrated power part, a plurality of first propeller blades and second propeller blades are connected to the integrated power part, and a seeker is connected to the outer wall of the integrated control part; the adjustable shielding mechanism is connected to the other end of the projectile body part in a sliding manner; the elastic energy releasing mechanism is connected between the adjustable shielding mechanism and the projectile body part; the shape of the adjustable shielding and preventing mechanism can be adjusted according to the flight attitude, and when entering an attack state, the adjustable shielding and preventing mechanism is in an unfolded state, so that a conical protective cover is formed, the whole projectile body part and the flight structure can be effectively covered for protection, wind resistance is reduced, and the service life of the projectile body part is prolonged. And meanwhile, the elastic energy release mechanism can be used for partially converting the resistance generated by the attack on the conical shield into reverse jet power, so that the kinetic energy loss during the attack of the flying projectile is effectively reduced.

The presently disclosed subject matter includes an active protection system and a method, dedicated for detecting, locating, and incapacitating beam-riding missiles and in that way protecting an asset from being targeted by the missile. According to some examples following receipt of a threat-indication, the active protection system estimates a location of a beam used for directing a threat (e.g., ATGM) to the target and launches an aerial platform that flies in the opposite direction along the beam until it meets and incapacitates the incoming threat.

The invention relates to a launching device (10) for deploying active agents (12) for protecting an object (O) and / or vehicle from missiles (P), wherein the launching device (10) has a launcher unit (16) for deploying fireable active agents (12), wherein the launcher unit (12) has a plurality of launcher segments (30) arranged adjacent to one another and pivotable relative to one another, wherein the launcher segments (30) each have a receiving space (38) extending along a deployment axis (36) for receiving and firing at least one active agent (12), wherein the launcher unit (16) has an actuator (46) by means of which the launcher segments (30) can be pivoted relative to one another, such that the angle (α) that the deployment axes (36) of adjacent launcher segments (30) enclose with one another can be adjusted. A method for deploying active agents (12) to protect an object (O) and / or vehicle from missiles (P) is specified.

FIELD: radar technology.SUBSTANCE: invention relates to passive methods of protecting radar stations (RLS) from homing high-precision weapons (HPW) with a passive homing head (PHH), which include anti-radar missiles (ARM). The radar station and an additional radiation source (ARS) synchronized with it emit coherent signals in the direction of the spatial position of the ARM. These devices represent a source of spatially diverse interference to the passive homing head of a missile. The normal to the phase front of the resulting electromagnetic wave differs from the normal to the phase front of the radar. As a result, the missile's passive homing head is oriented in the direction of the false target, which is different from the direction of the protected radar. The condition for the interference impact is the provision at the input of the receiving antenna of the PGSN of an inversion zone of the total wave front of the resulting signal of the radiation sources with certain amplitude-phase relationships, as well as the provision of a change in the angular velocity of rotation of the missile-target line of sight.EFFECT: increased radar's protection against anti-missile missile attacks by diverting its guidance trajectory to a false point from the protected radar.1 cl, 2 dwg

The application provides a rigid-flexible coupling arrow attack angle controller design method constituted by a parafoil and an arrow, the parafoil is combined with a traditional arrow to form a rigid-flexible coupling arrow, and the parafoil attack angle is quickly adjusted to the vicinity of a target attack angle by controlling a flap deflection angle Φ of the parafoil to track a desired attack angle instruction of the parafoil, so that the response speed of the parafoil attack angle is greatly improved, and then the aerodynamic performance of the parafoil can be fully exerted, and the arrow can realize rapid, small-radius and large-angle agile turning.

The application discloses an air-to-air missile evading method based on drum maneuvering, and the aircraft performs drum maneuvering, the speed direction of the aircraft is opposite to that of the missile, and the missile attack is evaded; in the process of evading the missile, the aircraft obtains a guidance law of the aircraft according to current position and a desired motion trajectory, in the desired motion trajectory, the aircraft performs circular motion in a vertical plane and uniform motion in a forward direction. The air-to-air missile evading method based on drum maneuvering can realize drum evading action of the aircraft on the missile, and the evading effect is good.

The invention discloses a super real-time simulation and cooperative control integration method based on track segmentation calculation. The method comprises the following steps: for a plurality of missiles which the same target arrives at at the same time, acquiring real-time positions of the missiles in a flying process; performing super-real-time simulation according to the real-time position, and determining the remaining flight time of each missile; determining expected time according to the remaining flight time; and the time constraint guidance rate of each missile is determined according to the expected time, and then the path of the corresponding missile is adjusted. According to the invention, accurate prediction of the residual flight time is realized, closed-loop control of flight time error and lateral overload is established, and thus high-precision cooperation of multi-missile attack time is realized.

The invention relates to a launch device (10) for discharging active elements (12) for protecting an object (O) and / or vehicle from missiles (P), wherein the launch device (10) has a launcher unit (16) for discharging fireable active elements (12), wherein the launcher unit (12) has multiple launcher segments (30) arranged adjacent to one another and pivotable relative to one another, wherein the launcher segments (30) each have a receiving space (38) extending along a discharge axis (36) for receiving and firing in each case at least one active element (12), wherein the launcher unit (16) has an actuating drive (46) by means of which the launcher segments (30) can be pivoted relative to one another such that the angle (α) enclosed by the discharge axes (36) of in each case adjacent launcher segments (30) can be set. The invention also relates to a method for discharging active elements (12) for protecting an object (O) and / or vehicle from missiles (P).

The application discloses a kind of anti-ship missile attack time interval evaluation method based on BP neural network, comprising the following steps: S1, establish simulation model, obtain neural network training sample according to simulation model;S2, training sample is used to train BP neural network, and obtain guidance time prediction model;S3, desired range, maximum overload capacity, target field of view angle, target field of view angle maximum value are input into guidance time prediction model, and the guidance time range is obtained.The anti-ship missile attack time interval evaluation method based on BP neural network disclosed in the application does not need complicated calculation, can conveniently know the feasible guidance time of multiple missiles at this time, and the guidance time range obtained has high accuracy and short time consumption.

The present application belongs to the field of unmanned aerial vehicle maneuver decision technology, and discloses a kind of unmanned aerial vehicle short-range air combat maneuver autonomous decision method, system, equipment and terminal, establish short-range air combat situation, missile attack area and the expression of missile allowed launch condition is achieved, construct unmanned aerial vehicle movement dynamics model and carry out action representation in reinforcement learning;According to node and fuzzy clustering method, similar experience in experience pool is clustered and excluded, to ensure that the experience retained is typical;Design air combat maneuver autonomous learning, autonomous decision algorithm based on node clustering and DDPG, realize the autonomous decision of short-range air combat maneuver.The present application is used to exclude similar experience, and retain the most typical experience.The present application effectively solves the problem of large amount of experience pool data and low algorithm efficiency when making decision on complex tasks.The present application improves the short-range air combat problem description model, changes the state expression method according to the characteristics of short-range air combat, and better reflects the characteristics of short-range air combat.

A device (800) for protecting an aircraft against missiles, includes a Short-Wave InfraRed based (SWIR-based) Missile Tracking Unit, having a SWIR-based optical imager that associated with an optical SWIR band filter. The device (800) further includes a SWIR signals processor; it analyzes the captured SWIR optical signals; and it performs a SWIR-based missile acquisition process, which is also based on raw angular position data of a missile as received from a Missile Approach Warning System (MAWS); and it performs a SWIR-based missile tracking process, which continuously and dynamically determines a precise angular position of the missile based on the captured SWIR optical signals. The device (800) includes a laser-based missile-jamming unit, having an internal laser emitter; and optionally also being operably associated with an external high-power laser emitter; to disrupt the missile, or to disrupt a guiding station of the missile.