7 results about "Cruise missile" patented technology

This invention discloses an anti-cruise missile interception system, relating to the field of national defense and military technology. The anti-cruise missile interception system includes a blocking net, a towing device, and a high-voltage power supply. The blocking net is attached to the towing device and electrically connected to the high-voltage power supply. The blocking net is woven from chemical fiber or carbon fiber filaments and mounted on a tower or strip-shaped balloon. The high-voltage power supply employs a high-voltage arc radiation device or a high-voltage electromagnetic pulse device. The immense energy released by the high-voltage power supply can disrupt the guidance and control systems of cruise missiles, causing them to deviate from their targets or even triggering an explosion. This invention has significant advantages such as rapid response, high energy, large interception range, automatic interception, ability to counter continuous cruise missile attacks, low cost, and ease of manufacturing. Through dense, carpet-like deployment, it can effectively intercept enemy cruise missiles and loitering munitions, protecting important military bases and targets.

A multi-cruise missile penetration control method based on multi-head attention mechanism belongs to the interdisciplinary field of artificial intelligence and autonomous systems. It constructs a multi-cruise missile adversarial game simulation environment to collect raw high-dimensional situational observation data; designs a multi-head attention autoencoder to model the dynamic correlation of battlefield units using the multi-head attention mechanism, unsupervisedly compressing the high-dimensional heterogeneous observation data into a low-dimensional essential situational representation; constructs a centralized multi-agent flexible actor-commentator reinforcement learning agent based on the dimensionality reduction features, and completes cooperative strategy training by combining a multi-objective composite reward function to output the globally optimal penetration decision; adopts centralized perception and decision-making, and deploys the model to the actual system to form a closed-loop control. This method alleviates the curse of dimensionality, improves situational awareness efficiency, enhances the convergence speed of reinforcement learning training and the robustness of cooperative strategies, adapts to dynamic adversarial battlefield environments, and improves the success rate of multi-cruise missile swarm penetration. It is applicable to scenarios such as military swarm operations and UAV collaborative mission planning.

The application provides a low-subsonic to high-subsonic wide-speed-range deformable aerodynamic layout of a cruise missile, comprising double-axis variable sweep wing mechanisms arranged at the bottom of a fuselage, capable of arbitrarily changing and locking a sweep angle in a range of 0-90 degrees, each double-axis variable sweep wing mechanism comprising an inner wing segment and an outer wing segment, the inner wing segment being pivotally connected with the fuselage at a wing root, and the inner wing segment being adjusted at a front sweep angle in a range of 0-90 degrees; the outer wing segment being pivotally connected with the inner wing segment at a wing tip, and the outer wing segment being adjusted at a rear sweep angle in a range of 0-90 degrees; and the nose being blunt. In the embodiment, the double-axis variable sweep wing mechanism has opposite influence trends of the inner wing segment and the outer wing segment on the center of pressure of the cruise missile during stretching, folding and flying, so as to control the change range of the center of pressure of the cruise missile in a very small interval, and make the wing sweep process have good maneuvering and stability characteristics and flight stability. In addition, the double-axis variable sweep wing mechanism is parallel to the fuselage when being folded, so that the cruise missile is convenient to store and transport, and the storage and deployment capability is improved.

The application discloses a high-altitude long-endurance target aircraft combined navigation method and system applicable to satellite denial conditions, relates to the high-altitude target aircraft, general unmanned aerial vehicle and navigation guidance field of cruise missile, and the high-altitude long-endurance target aircraft combined navigation method applicable to satellite denial conditions comprises the following steps: in a take-off preparation stage, a combined navigation unit receives navigation basic information set through a data link; in a take-off stage, the combined navigation unit completes self-alignment based on a current attitude angle of the target aircraft, a current speed of the target aircraft and current position coordinate information of the target aircraft, and then the target aircraft is launched; in a target aircraft flight stage, the combined navigation unit analyzes a PDOP value by using a preset threshold value, determines a current navigation mode, calculates target aircraft navigation state information and transmits the target aircraft navigation state information to a flight control unit, and the flight control unit generates flight control instructions based on the target aircraft navigation state information. The application can realize accurate positioning and navigation of a flight vehicle (such as a target aircraft) in a normal satellite signal environment and a satellite denial environment.