39 results about "Missile attack" patented technology

The invention relates to an unmanned aerial vehicle-based guided missile attack route planning method which comprises the following steps: calculating to obtain the wind speed and the wind direction according to fight parameters of an unmanned aerial vehicle, and determining the sun illumination azimuth angle according to local time; calculating track angles of the unmanned aerial vehicle attacked by guided missiles from the left side and the right side according to the wind speed and the wind direction, and selecting the side having the relatively small absolute value of the difference value between the track angle of the unmanned aerial vehicle and the sun illumination azimuth angle to be used as the side suitable for being attacked by the guided missiles; determining the launching off-axis angles and launching axial distances of the guided missiles according to launching requirements and trajectories of the guided missiles so as to obtain the laterodeviation of the unmanned aerial vehicle; and calculating to obtain the coordinate of laterodeviation point stroke according to the track angle, at the side suitable to be attacked by the guided missiles, of the unmanned aerial vehicle, the laterodeviation of the unmanned aerial vehicle, and known impact point coordinates and further to obtain the attack route of the guided missiles, so that the unmanned aerial vehicle flies for attacking according to the attack route. According to the unmanned aerial vehicle-based guided missile attack route planning method, use requirements of all-weather attack of the unmanned aerial vehicle are met, and the automation degree, the rapidity and the real-time performance of the attack can be improved to the greatest extent.

The invention discloses a guidance method for attack time control. The guidance method comprises the following steps of establishing mathematical models of a missile and a target by considering the three-dimensional space of motion of the missile and the target; obtaining a dynamic equation of the trajectory inclination angle and the trajectory deflection angle of the missile, and obtaining a dynamic equation of the distance between the missile and the target, the angle of sight of the missile and the deflection angle of sight of the missile; on the basis, establishing a dynamic equation of the attack time error of the missile; then, separately designing the guidance law of the missile according to a pitching channel and a yaw channel, wherein the guidance law of the pitching channel is designed as an augmented proportion guidance law, the guidance law of the yaw channel is designed as a guidance law with an attack time error feedback item, and the trajectory track is adjusted to realize time control over attack on the target; and when the yaw angle is zero, adjusting the guidance law of the yaw channel to avoid singularity conditions. According to the guidance method, the attack time error is estimated, the attack time error tends to be zero through a guidance strategy, and the distance between the missile and the target tends to be zero. The guidance method for attack time control has the characteristics of clear structure and high applicability.

The invention discloses an attack angle and attack time control method based on trajectory planning. Firstly, a planned missile flying trajectory is assumed to be composed of an arc section SA and a line section AT, the arc section SA has a radius of R, and the line section AT passes across a target point T(xT, yT) and the requirement that the tail attack angle of the missile is thetaf is met; the arc section SA starts at the initial position S (x0, y0) of the missile and is tangent to the line section AT at a to-be-determined point A(xa, ya), and the point A(xa, ya) is obtained by specified missile attack time tf through an iterative algorithm. On the basis of trajectory planning, the invention provides a trajectory tracking control algorithm based on a virtual target; a feedforward and feedback composite control scheme is put forward in the arc section, and a sight line angle PD control scheme is put forward in the line section; and the method has a small calculation amount, and engineering implementation is facilitated.

The invention provides a multiple missile collaborative ballistic planning method to deal with penetration. The method comprises the specific steps that step 1, based on the radar equation, a radar threat quantification model is established to describe the threat of a radar detection area to a missile; step 2, a collaborative control model is established, the collaborative control model comprisesa collaborative time control model and a collaborative angle control model; step 3, a collaborative attack problem is converted into a nonlinear optimal control problem which is solved based on a hp-self adaptive Radau pseudospectral method, which means at one moment of the flight, the remaining flight time of each missile is determined, whether or not a collaboration is necessary, if necessary, the time for the collaborative attack is calculated and the missile to be adjusted is determined, and the collaborative ballistic planning is conducted on the missile needs to be adjusted. According tothe multiple missile collaborative ballistic planning method, multiple missiles attacking a target on the same attacking time and with the same attacking angle is ensured; meanwhile, the radar detection threat is smallest during the flight, and the comprehensive combat effectiveness is effectively improved.

The invention relates to a photoelectric warfare infield semi-physical simulation system based on a mechanical arm and belongs to the field of infield simulation and research. The system is used for realizing the full real-time dynamic semi-physical simulation, is reasonable in cost and is used for estimating the research and development on a foundation and onboard photoelectric warfare weapon system in wave bands such as visible light and medium / long wave infrared. The system comprises a guided missile guider, an interference laser emitter, a target simulation source and a launching pad, wherein the guided missile guider is hung on the mechanical arm; a linear motor is used for driving the mechanical arm to move on a cross beam; and the interference laser emitter and the target simulation source are fixed on the launching pad. A simulation interference system equivalent a laser divergence angle is used for performing real-time estimation on the tracking, the fighting time selection and the fighting performance of a laser warfare weapon after an infrared terminal guided missile attacks from a place 10km away. Meanwhile, the system provided by the invention is applied to other interference devices such as heat source and point source jammers for estimating an terminal guided section of an attacking missile.

The invention discloses an integral proportional guidance nonlinear correction method mainly applied in the guidance law adopting angle guidance. The deviation of nonlinear effects is equivalent to the corresponding guidance law angle initial value zero position, the initial angle is corrected, and therefore the overload nonlinear part in the corresponding instruction generation is eliminated. By means of the method, the ballistic overshoot influence caused when high-altitude overload response is too low and response is insufficient, and particularly nonlinearity caused by the large airspace span in a flying process and caused in the instruction switching process is overcome, and the method can be adopted when a guided missile attacks a stable moving target.

The invention provides a missile longitudinal attitude control algorithm based on reinforcement learning, belongs to the field of missile attitude control research, and relates to an Actor-Critic (AC)structure based on reinforcement learning, which is composed of an action network and an evaluation network, wherein the evaluation network is used for outputting an evaluation value for the state ofthe missile according to the state of the missile, and the action network is used for generating a corresponding elevator deflection angle according to the evaluation value output by the evaluation network, so that the longitudinal attitude of the missile is stably controlled under the condition of not depending on an internal model of the missile. The method comprises the following steps: 1) establishing and determining a missile longitudinal attitude kinetic model; (2) defining a tracking error of the missile attack angle and establishing a performance index related to the error; (3) designing an evaluation network; (4) designing an action network; (5) designing an evaluation network weight updating law; (6) designing an action network weight updating law. The algorithm is mainly applied to the missile longitudinal attitude control.

The invention discloses a bistatic forward-looking SAR imaging method in a subduction mode. The method comprises the steps: proposing an imaging model in which a reconnaissance plane cooperates with amissile, the track is vertical, and the missile performs a uniform diving attack; establishing a geometric model of an uniform diving bistatic forward-looking SAR; providing a model corresponding toslant range history; and proposing an imaging algorithm based on receiver fixed equivalent for characteristics of the slant range history. According to the method, the double missiles matching model adopts an action mechanism that a missile attack and a missile performs irradiation and imaging, and an irradiation missile is away from an imaging area.

The invention belongs to the technical field of unmanned aerial vehicle flight control, and particularly relates to an unmanned aerial vehicle flight control method. The method comprises the steps of:setting a maneuvering mode of an unmanned aerial vehicle as a shooting interception maneuvering mode during long-distance engagement; setting the maneuvering mode of the unmanned aerial vehicle as anoffset maneuvering mode after ammunition is shot; setting the maneuvering mode of the unmanned aerial vehicle as a cross-cut maneuvering mode while elude the locking of the enemy; and setting the maneuvering mode of the unmanned aerial vehicle as an escape maneuvering mode, a cocking looping maneuvering mode or a breaking S maneuvering mode when eluding the attack of a guided missile.

The invention discloses a distributed cooperative guidance law construction method based on communication time-varying delay. According to the method, guidance models are divided into a sight line direction model and a sight line normal direction model, and guidance laws of the models are constructed respectively. In the sight direction, firstly, based on the improved multi-agent consistency theory, arrival time is selected as a state variable, under the condition that time-varying delay exists in communication between missiles, it is ensured that the arrival time of the missiles is consistentthrough the effect of a consistency protocol, and finally the purpose that the missiles attack the target at the same time is achieved. In the sight line normal direction, based on the sliding mode control theory, the sight line angle error and the sight line angular rate are selected as state variables, the sight line angle error and the sight line angular rate approach to 0 by constructing a sliding mode controller, and the missile attacks a target according to a preset angle. According to the method, the maximum delay constraint does not need to be considered, the parameters in the consistency convergence protocol can be dynamically changed according to the delay, and the multi-missile cooperative strike target under the communication time-varying delay is realized.

The invention provides an early warning aircraft tactical behavior simulation method and system under condition of no-escorted formation. The method comprises the following steps: detecting air, seaborne and ground threat targets and attack ranges of the threat targets in real time based on the early warning aircraft executing an early warning detection task; calculating the shortest path selected by the early warning aircraft to avoid all the threat targets to reach the detection area by using an early warning aircraft detection patrol path planning algorithm. Compared with a conventional early warning aircraft tactical behavior simulation method, the early warning aircraft adopts a self-survival combat mode without combat aircraft escorting, the function of actively avoiding air, seaborne and ground threats of an enemy is added, and if aiming by an enemy missile is found, the air, ship-to-air missiles and ground-to-air missiles of the enemy can be preferentially avoided. Based on the enhanced behavior tree, the functions of early warning aircraft detection patrol path planning, enemy target detection and identification, enemy threat avoidance, enemy missile attack avoidance and the like are designed in a layered manner, and the self-survival rate and intelligence acquisition capability of the early warning aircraft are improved.

The invention discloses a separation type defensive armor for a naval vessel and a ship. The defensive armor is characterized in that the defensive armor is made of a metal material and fixedly formed by a retractable mechanical arm or a mounting buoyancy chamber and the vessel; when the vessel is attacked by a surface weapon and a missile, the defective armor blocks and detonates the attacking weapon in a water area away from the vessel, so that harm caused by a reason that the vessel directly explodes when attacked by the heavy weapons is reduced; and the defensive armor for the civil ship is a light single-layer defensive armor and dragged by a locomotive at a ship deck, so that a phenomenon that pirates boards the ship and robs passengers at a pirate boarding point is avoided. The defensive armor has the advantages that self-fixed armor protection of the conventional vessel is changed; the last defender type shield defense effect is achieved at the periphery of the vessel; and a nonmilitary technological defense effect is achieved to guarantee the ocean shipping safety of the civil ships.

The invention discloses a semi-physical simulation system for missile attack and defense confrontation of semi-physical simulation system and implementation method thereof. The system is placed in a darkroom environment and comprises an interceptor simulation system, a bullet target simulation system, a simulation host and a visual display screen. The system can be independently used for testing and developing an interceptor or an attacking bullet, and can also be used for simulating two parties to carry out anti-guide and anti-interception combat, so that simultaneous development of an attacking party weapon system and a defending party weapon system is realized; in testing the advantages and disadvantages of the confrontation strategies of the two game parties, mutual learning of the two parties in confrontation is realized so as to continuously improve respective strategies, and compared with numerical calculation of game confrontation, the test result is more reliable; the system and method not only can be used for testing and development of an anti-missile interception weapon system, but also particularly refers to missile interception and anti-interception, and can be used for semi-physical simulation of military confrontation such as ground chariot confrontation and aerial fighter combat confrontation after modification.

The invention provides a method for avoiding an attack of a large aircraft. The method comprises the following steps: detecting whether there is no missile in a predetermined area; when there is a missile, judging whether a missile section target is a large aircraft or not; when no missile exists in the area or the target of the missile does not point to the large aircraft, the large aircraft normally executes a predetermined task; when the target of the guided missile section is a large aircraft, judging the coming direction of the guided missile, constructing a fuzzy inference rule according to the coming direction of the guided missile and the aircraft speed, and controlling the large aircraft to perform corresponding maneuvering actions by the aircraft according to the constructed fuzzy inference rule, or accelerating the flight of the large aircraft and getting rid of the guided missile by adopting an acceleration mode; then, whether the missile distance is smaller than a first preset value or not is judged, if yes, the large aircraft conducts diving S maneuver to avoid attacks, and if not, the original flight state is kept; then, whether the missile distance is smaller than a second preset value or not is judged, if yes, the large aircraft adopts tail-section avoidance, and if not, the large aircraft keeps the original flight state.

The invention discloses a gyroplane guided missile attack system. The gyroplane guided missile attack system comprises a gyroplane, a fire control computer, a weapon hanging frame, a guided missile, adata link, a reconnaissance pod, an attitude and heading instrument and a power distribution box. According to the gyroplane guided missile attack system, the gyroplane platform is utilized, and thefire control computer, the weapon hanging frame, the guided missile, the data link, the reconnaissance pod, the attitude and heading instrument and the power distribution box are hung, so that the determination, aiming and attack efficiency of a ground static target, a ground moving target and a low-altitude moving target is achieved. The gyroplane guided missile attack system is suitable for mounting guided missiles for autonomous guidance, homing guidance, remote control guidance, composite guidance and the like. The gyroplane guided missile attack system achieve pilot launching, remote command and control center launching and program launching, and the launching attack task of a guided missile is completed. The gyroplane guided missile attack system has the advantages of being low in cost, long in distance, high in precision and flexible in launching.

The invention provides an automatic program management device and method for an ion implantation machine table. The device comprises a receiving unit, a downloading unit, a parameter collection unit and a program correctness checking unit, wherein the receiving unit is used for providing an input selection command for a user; the downloading unit is used for downloading a corresponding to-be-checked program file after a target machine table is selected; the parameter collection unit is used for collecting to-be-checked parameters for each program in the to-be-checked program file according toa preset missile attack strategy and generating a to-be-checked parameter report, wherein the missile attack strategy is to traverse the to-be-checked file line by line according to a file format of the to-be-checked file to acquire the to-be-checked parameters; and the program correctness checking unit is used for performing correctness checking on the to-be-checked parameter report to obtain a checking result corresponding to the to-be-checked program file. The automatic program management device and method have the advantages that correctness checking can be automatically performed on the ion implantation programs of the VARIAN ion implantation machine table, manpower of manual checking is saved, furthermore it can be 100-percent guaranteed that program errors are checked out, and losscaused by the program errors is avoided.

The invention discloses a missile guidance law for simultaneously attacking a maneuvering target by multiple missiles, and aims to provide a guidance law for the missiles when the multiple missiles attack the maneuvering target, wherein the stabilization time of the guidance law does not depend on initial conditions of a system. In order to realize rapid response and robustness of the system, a non-singular rapid terminal sliding mode surface with fixed time convergence is designed, and the sliding mode surface has the characteristic of rapid convergence of a traditional terminal sliding mode and also has non-singular property. According to the designed sliding mode surface, the guidance laws which converge in the fixed time direction and the direction perpendicular to the missile visual line direction are constructed, two guide law design parameters are mutually independent, the parameters can be matched according to system performance requirements, a saturation function is introduced into the guidance law to avoid system buffeting, and the guidance law is simple in structure and easy to achieve.

The invention discloses an automated program correctness management method and apparatus for an ion implantation machine. The method comprises the steps of receiving selection operation of a user, and selecting a target machine server; after the selection operation of the user is received, downloading to-be-checked programs from the target machine server according to the selection operation of the user; collecting to-be-checked parameters for the programs by adopting a missile attack method for traversing program file title lines column by column first and then traversing program files line by line; performing correctness check on the programs and the to-be-checked parameters, and outputting check results. Through the method and the apparatus, the programs of the NISSIN ion implantation machine can be automatically subjected to correctness check, so that the manpower of manual check is reduced, 100% checkout of program errors can be ensured better, and the loss caused by the program errors is avoided.

The invention discloses an unmanned aerial vehicle guided missile attack system which comprises an unmanned aerial vehicle and a ground command and control center. A fire control subsystem, a weapon hanger, a guided missile, a data chain, a reconnaissance pod and a distribution box are arranged on the unmanned aerial vehicle; the fire control subsystem calculates the attack attitude and time according to the target information acquired by the reconnaissance pod, the carrier platform information of the unmanned aerial vehicle and the command and control information of the ground command and control center, and controls the guided missile to launch; the guided missile is mounted on the weapon hanger, so that the information interaction between the fire control subsystem and the guided missile is realized; the guided missile realizes a target attack; the data chain realizes the remote wireless information interaction between the unmanned aerial vehicle and the ground command and control center; the reconnaissance pod obtains the target information in real time; the distribution box is used for power supply management; and the ground command and control center is used for remote control. According to the present invention, the remote command and control and program launching can be achieved, a helicopter, a bomber and a fighter do not need to be used when an attack task is executed, and the system has the advantages of being low in cost, free of casualties, long in distance, high in precision and flexible in launching.

The invention relates to an underground ultra-safe nuclear power station which is arranged under the ground. The underground ultra-safe nuclear power station sequentially comprises a power generation layer, an isolation layer, a reactor layer, a cooling layer, a nuclear waste recycling layer and a storing layer from top to bottom, wherein the power generation layer provides power for a whole system and a power network on the ground; an isolation water pond is arranged in the isolation layer; a nuclear fuel box is arranged in the isolation water pond; a reactor is arranged in the reactor layer; a feeding tube of the reactor extends upwards and is connected with the nuclear fuel box; a cooling water pond is arranged in the cooling layer; a nuclear waste box is arranged in the cooling water pond; a totally closed nuclear waste regeneration cycle system is arranged in the nuclear waste recycling layer; a nuclear waste conveying channel is formed between the regeneration cycle system and the nuclear waste box; and a nuclear fuel storage warehouse is arranged in the storage layer and is used for storing nuclear wastes and nuclear fuel balls. The underground ultra-safe nuclear power station has quite high seismic capacity; requirements on geology are low; and when accidents occur, the reactor cannot in a dry burning state. The underground ultra-safe nuclear power station has the advantages of terrorist attack prevention, air investigation prevention, missile attack prevention and nuclear radiation leakage prevention.

The invention relates to an unmanned aerial vehicle guided missile attacking system based on big data. The unmanned aerial vehicle guided missile attacking system comprises an investigation unmanned aerial vehicle, a positioning unmanned aerial vehicle and an attacking unmanned aerial vehicle. The investigation unmanned aerial vehicle is used for taking sharp images of a target in all directions,and the sharp images are used as target images; the positioning unmanned aerial vehicle is loaded with a positioning navigator, the investigation unmanned aerial vehicle transmits the target images tothe positioning navigator, and a guided missile is loaded in the attacking unmanned aerial vehicle; the positioning navigator is internally provided with an image collector and an image dissector, the target images are stored in the image dissector, and when the target images are fit with the images in the image collector, the positioning navigator flies to the target and is automatically fixed to the target; the positioning navigator is further internally provided with a self driving mechanism, a positioner and a signal emission source which is used for emitting optical signals; a sound wavegenerator is installed on the positioning navigator, a sound wave receiver is installed on the guided missile and used for emitting inaudible waves. The unmanned aerial vehicle guided missile attacking system based on the big data has the beneficial effects of being precise in positioning, capable of adapting to visible severe environments and good in attacking effect.

The present invention provides a method and system for simulating the tactical behavior of an early warning aircraft under the condition of no escort formation. The patrol path planning algorithm calculates the shortest path selected by the early warning aircraft to avoid all threatening targets and reach the detection area; compared with the conventional early warning aircraft tactical behavior simulation method, the early warning aircraft adopts the "self-survival" combat mode without fighter escort, which increases the ability to actively avoid the enemy The function of air, sea and ground threats, if found to be targeted by enemy missiles, can preferentially avoid enemy air-to-air, ship-to-air and surface-to-air missiles. Based on the enhanced behavior tree, the functions of early warning aircraft detection and patrol path planning, detection and identification of enemy targets, avoidance of enemy threats, and avoidance of enemy missile attacks are designed in layers, which improves the "self-survival" rate and intelligence acquisition ability of early warning aircraft.

The invention belongs to the technical field of vertical launching, and particularly relates to an airborne embedded vertical launching device. The device comprises a mounting frame, a fuel gas exhaust pipeline, a heat insulation box body and an emission controller. A plurality of vertical launching wells arrayed in a matrix mode are arranged on the mounting frame, missiles are mounted in the vertical launching wells, and missile launching opening covers are arranged at the ends of the vertical launching wells. One end of the fuel gas exhaust pipeline is connected with the mounting frame, an internal channel of the fuel gas exhaust pipeline is communicated with the vertical launching wells, and a machine body flame exhaust opening cover is arranged at the other end of the fuel gas exhaustpipeline. The heat insulation box body is installed in a machine body and used for containing the mounting frame, the vertical launching wells and the fuel gas exhaust pipeline. The emission controller is used for controlling the launching of the missiles. After being assembled to an aircraft, the aircraft not only reserves the forward missile attacking capacity, but also has the attacking capacity towards the upper portion and the lower portion of the aircraft body, and the attacking and defending capacity of the combat aircraft in short-distance air combats is improved.

The invention discloses an automation program correctness management device and an automation program correctness management method for a SEN ion-implantation machine table. The method comprises the steps of: receiving a selection operation of a user and selecting a target machine table server; after receiving the selection operation of the user, downloading to-be-checked programs from the target machine table server according to the selection operation of the user; collecting the to-be-checked parameters for each program by using a missile attack method and generating a to-be-checked parameter report; and carrying out correctness checking on the programs and the to-be-checked parameters and outputting a checking result. According to the device and the method, the correctness checking can be automatically carried out on the programs of the SEN machine table, not only the manpower for manual checking is saved but also a program error can be absolutely checked and the loss caused by the program error is avoided.

The invention discloses an automated program correctness management method and apparatus for an ion implantation machine. The method comprises the steps of receiving selection operation of a user, and selecting a target machine server; after the selection operation of the user is received, downloading to-be-checked programs from the target machine server according to the selection operation of the user; collecting to-be-checked parameters for the programs by adopting a missile attack method for traversing program file title lines column by column first and then traversing program files line by line; performing correctness check on the programs and the to-be-checked parameters, and outputting check results. Through the method and the apparatus, the programs of the NISSIN ion implantation machine can be automatically subjected to correctness check, so that the manpower of manual check is reduced, 100% checkout of program errors can be ensured better, and the loss caused by the program errors is avoided.

The invention provides a target non-escape area reliable prediction method adapting to cooperative task planning. The target non-escape area reliable prediction method is characterized by comprising the following steps: 1, selecting at least two feature points in a missile flight envelope; 2, setting the spatial distribution of a target in the airspace according to the position and speed of the target; 3, establishing a target non-escape area by taking the feature point in the missile flight envelope as a starting point and the aim as an end point, and establishing a mapping relationship between the current state of a missile, namely the initial state of the feature point, and the target non-escape area; and 4, obtaining the target non-escape area according to the mapping relationship between the current state of the missile and the target non-escape area, establishing a target escape cost model, calculating the current target escape cost, and predicting the missile interception capability. According to the target non-escape area reliable prediction method adapting to cooperative task planning, a non-escape area model of the missile attack target is established according to the flight state information of the missile and the target, the target escape cost is effectively predicted, and support is provided for missile cooperative task planning.

The invention discloses a missile guidance law for multiple missiles attacking maneuvering targets simultaneously, aiming at providing missiles with a guidance law whose stable time does not depend on system initial conditions when multiple missiles attack maneuvering targets. In order to achieve fast response and robustness of the system, a non-singular fast terminal sliding mode surface with fixed time convergence is designed. This sliding mode surface has the characteristics of traditional terminal sliding mode fast convergence and non-singularity. Based on the designed sliding mode surface, a guidance law that converges at a fixed time along and perpendicular to the line of sight of the projectile is constructed. The design parameters of the two guidance laws are independent of each other, and the parameters can be matched according to the system performance requirements, and the saturation function is introduced in the guidance law To avoid system chatter, the guidance law has a simple structure and is easy to implement.

According to the terminal guidance control method and system of the unmanned aerial vehicle, the terminal guidance control system is constructed based on a homing guidance mode according to the guidance characteristics of the electronic warfare unmanned aerial vehicle, the corresponding terminal guidance control method is provided, the diagonal constraint and guidance precision requirements are met through a passive radar guidance method, and the terminal guidance control system and the terminal guidance control method are applied to the electronic warfare unmanned aerial vehicle. And meanwhile, tail end maneuvering and simulated attack control are realized, targets are accurately intercepted, missile attacks are defended, and the defense penetration capability is improved.