14 results about "Missile guidance" patented technology

The application discloses a laser beam riding guidance missile roll angle de-rotation measurement system and method based on polarized light, and belongs to the technical field of missile guidance control. The system comprises a laser irradiator for emitting polarized laser to generate a polarized laser field; a polarized detector assembly is arranged on one side of a target missile body close to the laser irradiator and is located in the polarized laser field together with the target missile body; wherein the polarized detector assembly comprises a four-quadrant detector, an accelerometer, a detection circuit and a signal processing module; a rectangular coordinate system is established in the polarized laser field, and a target missile body coordinate system is established. The application can not only measure the real-time roll angle parameter of the missile relative to the laser information field coordinate system, but also saves the loading process of the missile body reference information, simplifies the system complexity and is highly applicable.

The application provides a missile body and seeker installation error compensation method and system, comprising: obtaining a first angle value between a missile body and a target source by using a satellite navigation receiver and a strapdown inertial navigation system, the target source being at a preset distance from a launching frame on which the missile is placed and being within a field of view range of the seeker; obtaining an installation error angle value between the missile body and the seeker according to a rotation angle value of a frame of the seeker and the first angle value; and performing error compensation on an installation error of the missile body and the seeker according to the installation error angle value. Compared with the prior art, the first angle value between the missile body and the target source is obtained, the rotation angle value of the frame of the seeker is compared with the first angle value to obtain the installation error angle value, the installation error is reduced by software compensation according to the obtained installation error angle value, the precision of a line-of-sight angle measured by the seeker is effectively improved, and the precision of a missile guidance control system is improved.

Embodiments of the present application disclose a virtual object control method and device, electronic equipment and a storage medium; the method comprises: acquiring a direction of a sight line and a starting point of the sight line, and displacement and speed of a virtual object; calculating a deviation vector between the virtual object and the starting point of the sight line according to the starting point of the sight line and the displacement of the virtual object; decomposing the speed into speed components in a plurality of specified directions according to the deviation vector; calculating acceleration in the specified directions; fusing the acceleration in all the specified directions to obtain a target acceleration of the virtual object; and controlling the virtual object to move along the direction of the sight line based on the target acceleration. Based on simple speed decomposition and acceleration calculation, the control process of missile guidance is simplified, and the calculation amount in control is reduced, so that the missile guidance can be efficiently applied in games to realize control of the virtual object.

The invention discloses a high-speed maneuvering target interception collaborative surrounding guidance method based on a coverage theory. The method can ensure that the high-speed maneuvering target cannot escape after being surrounded by the intercepted projectile group, and the success rate of multi-projectile cooperative interception of the maneuvering target is greatly improved. According to the method, the maneuvering characteristics of the missile and the target are considered, the surrounding area is analyzed in combination with the concept of the Aboronius circle, and then the surrounding formation is designed to achieve redundant coverage of the target escape area. And then under the angle constraint, the time constraint and the limitation of missile acceleration of the missile encircling formation, a cooperative guidance optimization problem is constructed and solved, an optimal multi-missile guidance instruction is obtained, all missiles can reach the preset encircling formation at the same time in the flight stage, encircling of the target is completed, and the aim that the multi-missile multi-missile guidance instruction is obtained is achieved. Then, the maneuvering target is intercepted and hit in the terminal guidance stage, it is ensured that the target cannot escape after being surrounded by the interception bullet group, and cooperative surrounding, interception and hit of the high-speed maneuvering target are achieved.

The application discloses an interception guidance method and related device considering speed time variation and target maneuvering, relates to the technical field of missile guidance, and comprises the following steps: acquiring missile maneuvering parameters and target maneuvering parameters; establishing a three-dimensional guidance model under the condition of speed time variation and target maneuvering according to the missile maneuvering parameters and the target maneuvering parameters; constructing a time-varying navigation ratio proportional guidance law based on the three-dimensional guidance model; increasing a vertical acceleration component on the basis of the time-varying navigation ratio proportional guidance law to generate an improved augmented proportional guidance law; decomposing a missile normal acceleration vector in a missile total acceleration vector to a pitch plane and a yaw plane, and generating an attitude control instruction based on the conversion between an inertial coordinate system and a speed coordinate system; and adjusting the attitude control instruction based on the real-time updated missile time-varying navigation ratio, the missile normal acceleration vector and the target maneuvering parameters to intercept the target. The application can effectively improve the interception precision and stability of the missile in a complex maneuvering environment.

The invention discloses a multi-machine multi-missile collaborative air combat decision-making method based on SM-HAPPO deep reinforcement learning, and relates to the technical field of air combat intelligent decision-making. Starting from a multi-aircraft multi-missile collaborative air combat decision-making method, a dynamic model of an aircraft, a missile guidance model and an air combat situation model are established, and simulation of a complex environment is achieved. For collaborative decision-making of isomorphic or heterogeneous aircrafts, a PPO algorithm is expanded to the field of heterogeneous agents, a GRU-based state memory module is introduced, and an SM-HAPPO algorithm suitable for deep reinforcement learning of the heterogeneous agents is provided. In the strategy network, a loss function with a mask mechanism and a strategy entropy regular term is introduced, and the stability and exploratory performance of the algorithm are improved. Finally, a simulation experiment of aircraft collaborative air combat decision making is completed in a python environment, and it is proved that compared with a traditional intelligent algorithm, the collaborative decision making capacity and the air combat winning rate of the unmanned aerial vehicle can be further improved.

The application discloses a high-precision micro gyroscope based on noise compression effect and a working method thereof, mainly relates to a noise compression light source applied to a micro gyroscope based on a silicon-based photonic crystal microcavity, and can be applied to high-precision inertial navigation, missile guidance and other military fields. The application comprises (1) a noise compression light source generation structure; (2) a micro gyroscope structure based on a silicon-based photonic crystal microcavity; (3) a coupling structure of the noise compression light source and the micro gyroscope based on the silicon-based photonic crystal microcavity; and (4) a micro gyroscope test structure based on the silicon-based photonic crystal microcavity. The application has the advantages that the optical scattering noise and other noise sources of a cavity optical force structure in the micro gyroscope based on the silicon-based photonic crystal microcavity can be reduced, and super-high-precision angular velocity detection can be realized.

The application discloses a missile guidance control integration method based on a neural network mechanism modeling, which comprises the following steps: in a continuous time system, a vertical plane missile guidance control integration model is established; according to the dynamic equation of the vertical plane missile guidance control integration, a state transition equation in a discrete time system is established; a data set for fitting the dynamic model of a neural network is established, and a neural network parameter model obtained through neural network regression calculation is used as a non-mechanism fitting model of a missile control system; and according to the neural network parameter model, a guidance control integration mechanism model used in a control cycle is obtained. The method uses the input and output data of a control process to perform self-modeling of a time-varying control system, meanwhile, the model is equivalent to a mechanism method, and the modeling result can be used for the control of a discrete time system, and the modeling principle has interpretability and reliability.

The invention relates to a complementary training method for improving the robustness of a reinforcement learning interception strategy, and the method comprises the steps: obtaining an average confrontation combat scene, describing the average confrontation combat scene through a first-order delay dynamics model, and defining a defense missile guidance process in the average confrontation combat scene as a Markov decision process; on the basis of a Markov decision process, a strategy is updated step by step by using a PPO algorithm based on a course learning mode, a basic interception strategy is obtained, full-scene performance evaluation is performed on the basic interception strategy, failure scenes with miss distance exceeding standards are screened out to construct a failure scene list, and mixed initial state distribution is established by using the failure scene list. And difference compensation training is carried out through a PPO algorithm to obtain an optimal interception strategy. Aiming at the problem that a specific scene is easy to fail in a complex air combat interception scene, the robustness and reliability of an interception strategy are improved by introducing a failure scene compensation training mechanism, and the task success rate in a diversified combat environment is ensured.

A computer implementation processor is provided for directing a missile from a radar towards an interception point of a moving target. The processor includes a missile simulator module; a pre-launch module; a trajectory curvature module; and a guidance module. The missile simulator module determines look angle time to the interception point from the radar. This module determines the look angle time remaining to intercept, at which the angular difference between the line-of-sight to the interceptor and the target are below a threshold value. The pre-launch module provides an initial curvature gain value. The trajectory curvature module updates the curvature gain value from the look angle time. The simulator module receives the gain value in feedback. The guidance module receives the gain value and physical characteristic information for the missile and provides acceleration command to the missile to intercept the target.

The application discloses a multi-missile time-space cooperative guidance method, which comprises the following steps: 1) establishing a guidance motion dynamics model of a missile intercepting a target in a three-dimensional space; 2) calculating a guidance time consistency error through information interaction among the missiles, and designing a line-of-sight direction acceleration control input as a control quantity for coordinating the attack time of the missiles; and 3) designing a bottom-layer missile guidance law, i.e. a line-of-sight normal control input, for controlling the missiles to intercept a maneuvering target at an expected line-of-sight angle. The application establishes a time-space cooperative guidance control of multiple missiles intercepting the same maneuvering target in the three-dimensional space based on a guidance time estimation method and a line-of-sight angle constraint, and can truly reflect the relative motion relationship among the multiple missiles and the target and the remaining time of the terminal guidance of the missiles.

The invention provides an intersection vehicle risk avoiding trajectory planning method based on a proportional guidance method, and aims to solve the problems of collision risk caused by dynamic interaction between a vehicle and a straight vehicle when the vehicle turns right and insufficient real-time performance and adaptability of a traditional trajectory planning method. According to the method, a proportional guidance method in missile guidance is introduced, a virtual target vehicle is dynamically generated to serve as an interception target, and trajectory planning is converted into a target tracking process. The method specifically comprises the following steps: establishing an intersection coordinate system and acquiring vehicle state information in real time; generating a virtual target vehicle according to the speed and position of the conflicting vehicle, and processing a multi-conflicting vehicle scene in combination with a safety distance model; calculating the acceleration of the main vehicle by using a proportional guidance method, and cooperatively adjusting the track through the change rate of the sight angle and the speed direction angle; intercepting conditions are pre-judged, and the vehicle speed is dynamically adjusted to optimize the track feasibility; a Bezier curve is introduced into the tail section to correct the course angle, and it is ensured that the posture is smoothly aligned with the target lane during vehicle confluence. According to the method, the path and speed collaborative planning is realized, the traffic efficiency and the driving comfort are improved while the driving safety is guaranteed, and the method is suitable for the real-time obstacle avoidance requirement in the complex scene of the urban intersection.

The application discloses a kind of attack bomb dive section guidance method and system based on sliding mode control, it is related to missile guidance and control technical field, first establish the sliding mode guidance law with impact point angle constraint, then using the sliding mode guidance law with impact point angle constraint to control attack bomb, realize attack bomb dive section guidance, by designing the sliding mode guidance law with impact point angle constraint to control attack bomb, it can make up the loss of maneuverability, can obtain greater maneuverability when attack bomb is converted into dive section from horizontal flight section, so as to realize successful guidance, complete the established technical index, satisfy the guidance demand under complex environment.

The invention relates to the technical field of image processing and information fusion, and discloses a missile-borne infrared-visible light multi-modal image fusion method, which comprises the following steps: S1, carrying out image preprocessing on an infrared image and a visible light image by adopting different algorithms; s2, performing multi-scale decomposition and feature extraction on the infrared image and the visible light image; s3, performing low-frequency fusion and high-frequency fusion on the infrared image and the visible light image by adopting a self-adaptive fusion rule; s4, performing image reconstruction and post-optimization on the fused low-frequency information and high-frequency information; s5, realizing missile-borne real-time optimization by adopting hardware acceleration strategies such as FPGA (Field Programmable Gate Array) parallel design and memory optimization; the method can adapt to various missile guidance systems, the target locking precision and the real-time response capability in a complex battlefield environment are remarkably enhanced, and the method is expanded to the national defense application fields such as unmanned aerial vehicle reconnaissance and armored vehicle multispectral sensing and has great military value.