36 results about "Missile system" patented technology

The invention belongs to the technical field of missile system testing and data processing, and particularly relates to a steering engine testing method and device, and the method comprises the steps: respectively testing a controller, a driver, an actuator, a cable and all parts of accessories which form a steering engine system; all the component units are assembled; carrying out matching test on each composition unit; the steering engine is assembled, and system electrical communication is completed; performing function test and performance test on the steering engine in a normal temperature state; performing performance test on the steering engine under various environment test conditions; testing the limits of the steering engine under various boundary conditions; carrying out local abnormal value detection and elimination on all test data; and analyzing the test data to obtain a steering engine test result, and generating a test report. By improving the testing method, coverage of ground testing content of the steering engine is guaranteed, and the reliability of the steering engine is improved; by designing a data processing and data analysis method, steering engine test data are processed, and the test efficiency is improved.

The invention discloses a plane symmetry aircraft BTT control method based on lateral SAR imaging seeker visibility, and the method comprises the steps: firstly overturning a projectile body by 180 degrees, enabling the available view field of a seeker to face downwards, and facilitating the finding of a target below; then designing a guidance instruction according to a lateral SAR imaging preposition angle requirement, carrying out amplitude limiting on a pitching guidance instruction, projecting the guidance instruction to a missile system, obtaining a roll angle increment instruction, and obtaining a roll angle instruction and a pitching overload control instruction by combining the roll angle increment instruction with a current roll angle; finally, after lateral SAR imaging is completed, a guidance instruction is calculated according to the requirement for hitting the target, and a roll angle instruction and a pitching overload control instruction are calculated according to the guidance instruction. According to the control method and the design method, the structure is universal, the engineering practice ability is high, and the method can be widely applied to various plane symmetry aircraft guidance control systems carrying lateral SAR imaging seekers in the future.

A mounting system and method that provides simplified mounting points and attachment interfaces for associated components. Specifically, the system and method generally comprise a mounting system, including a new support chassis, which allows for a Forward Looking Infrared (FLIR) aiming system which was built to be placed in an infantry system for a TOW missile, to be used in a vehicle mounted ISU system.

The present invention relates to a semi-active laser seeker head for miniature, laser-guided missile systems comprising a housing (20) limiting an inner chamber (23); a lens element (40) that is seated in a gap (26) of the housing (20) reaching the inner chamber (23) so as to receive electromagnetic radiation. The laser seeker head comprises; a body (44) that has a convex surface (42) on which the lens element (40) gets completely seated in a gap (26) on one hand and that extends into the inner chamber (23) on the other hand; and a filter (52) that directly receives the electromagnetic radiation, which is focused by the convex surface (42), from the body (44) that lies before and selectively transfers it to a multi-channel sensor (56) arranged at the rear portion thereof based on a predetermined wavelength threshold.

The present application belongs to the field of elastic motion modeling of air defense missiles, and particularly relates to an elastic motion modeling method for air defense missiles with trajectory control and direct-gas combined control, aiming at solving the problem that the traditional modeling method is insufficient in covering trajectory control force, thus being difficult to realize accurate modeling of the elastic motion of air defense missiles with trajectory control and direct-gas combined control. The present application comprises: calculating the kinetic energy T of the missile system caused by the bending deformation of the elastic missile body, the elastic potential energy U of the missile system, and the damping energy D of the missile system caused by the bending deformation of the elastic missile body; calculating the generalized force Q acting on the missile body corresponding to the virtual work through the virtual work principle i ; based on the kinetic energy T of the missile system, the elastic potential energy U of the missile system, the damping energy D of the missile system, and the generalized force Q i , constructing the dynamic equation of the elastic missile body through the Lagrange equation. The present application corrects and improves the problem of insufficient coverage of trajectory control force in the traditional modeling method, and has high accuracy and precision in the elastic motion modeling of air defense missiles with trajectory control and direct-gas combined control.

This invention discloses a method for interceptor deployment and deorbiting decision-making in a space-based anti-missile scenario. It includes modeling the time interception window, establishing a model of the time window during the interception process; establishing a model of the space interception window, obtaining a space interception window model for the opposing ballistic missile; and calculating and analyzing the single-orbit distribution density of on-orbit interceptors. This enables the space-based interceptor weapon system to allocate the optimal number of on-orbit interceptors to intercept the opposing missile under different interception requirements. This invention provides a reference for solving the interceptor deployment and corresponding weapon deorbiting decisions in space-based anti-missile systems, enhancing the rationality and accuracy of space-based anti-missile interception systems, and has excellent application prospects in the aerospace field.

The invention discloses an undirected topology-based cluster naval vessel air defense and anti-navigation system capability change analysis method, which comprises the following steps of: firstly, considering input attribute information of each naval vessel in a cluster, and constructing a corresponding cluster naval vessel undirected topological graph by taking each naval vessel as a node and taking a support relationship between the naval vessels as an edge; all nodes are traversed based on the undirected topological graph of the clustered naval vessel, node association information is obtained, the ability change of the air defense and anti-navigation system of the clustered naval vessel is analyzed, and the node association information comprises a node closed neighborhood, a node attack probability, a node weapon resource quantity and the like; based on the undirected topological graph of the clustered naval vessels, the most important node in the undirected topology is calculated in combination with a Roman control algorithm, the probability that each naval vessel is possibly attacked is calculated, and finally the air defense and anti-guide system capacity change of the clustered naval vessels is analyzed; results show that the method can effectively analyze the ability change of the air defense and anti-missile system of the cluster naval vessel.

The present invention discloses a method and system for avoiding conical obstacles of a cruise missile formation based on a two-hop network, and relates to the field of collaborative guidance and control algorithms for multiple aircraft. The method includes constructing a cruise missile model, determining the state variables of the cruise missile model, and the communication topology of the cruise missile formation; constructing a cruise missile cone obstacle model, and a β agent is constructed on the obstacle surface in the cruise missile cone obstacle model; constructing a cruise missile formation sub-control law algorithm, and the cruise missile formation sub-control law includes a formation keeping control law, a navigation feedback control law, and a formation obstacle avoidance control law; updating the state of the β agent, and updating the position and position speed of the β agent; constructing a cruise missile formation cone obstacle avoidance algorithm, and setting the initial state of the cruise missile formation. The present invention can achieve the purpose of multiple cruise missile systems flying in formation at a desired speed and formation.

1. The name of the design product: motorized target. 2. The use of the design product: used for simulating enemy aircraft or incoming missiles to provide opportunities for various types of artillery or missile systems to shoot at imaginary targets. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

The invention relates to the production of a semi-active laser seeker that has a low volume and weight budget, can be used in miniature ammunition and has a laser proximity sensor.

The utility model discloses a percussion type current generating device based on magnetoelectric induction. Comprising a shell, a magnetoelectric igniter in threaded connection with the interior of the shell, a push rod body in sliding connection with the interior of the shell, a button in threaded connection with the push rod body, a button cover in threaded connection with the shell, a first cylinder in clearance fit connection with one end in the push rod body, and a second cylinder in clearance fit connection with the other end in the push rod body, the push rod body comprises a first cylinder and a second cylinder, the two ends of the release spring are fixedly connected to the first cylinder and the second cylinder respectively, the return spring is clamped outside the push rod body, the lever is connected with the push rod body through a riveting structure, the magnetoelectric igniter comprises an iron core, the lever is connected with the iron core in an interference fit mode, and the iron core is located in the center of the magnetoelectric igniter. The push rod body is pushed to slide in the shell, the lever is pushed to move, the iron core is driven to swing, and current is generated. The device is small in size and light in weight, can be efficiently integrated in a missile system with limited space, and meets the requirements of modern military equipment for space and weight.

The invention relates to a missile system (100) that consists of a missile (120) that is charged before launch and instead of a thermal battery, has an optimised energy source (130) with a voltage boost circuit (132) and voltage buck circuit (133), and launcher (110) containing power unit (113) to charge / discharge energy source (130) in order to reduce costs and increase efficiency.

The application provides a multi-agent system DFS pseudo-tree communication method, structure and application thereof. The multi-agent system DFS pseudo-tree communication method is as follows: constructing a multi-agent system DFS pseudo-tree; determining the best cut point and root node of the DFS pseudo-tree, and determining the best neighbor node; initializing local data of the multi-agent, triggering a message-driven search process by the root node, selecting a node when the number of nodes to be searched is less than 2, and selecting the best cut point as the next search node when the number of nodes to be searched is greater than or equal to 2, and if there is no cut point, selecting the best neighbor node as the next search node, until the search is completed, and terminating the operation of the root node. The application can effectively solve the multi-agent cooperation problem in a complex environment, has high efficiency and good expansibility, and has a significant advantage in the application of large-scale missile system cooperative path planning.

The invention discloses an online intelligent self-adaptive parameter adjustment method for a missile stability controller. The method comprises the following steps: S1, constructing a numerical simulation model of a missile nonlinear dynamic model; the parameters influencing the stability of the system are subjected to pulling deviation of different combinations, and state output of the missile dynamics system under different pulling deviation combinations is obtained; s2, constructing a training data label by quantifying the stable state of the missile stability control system; s3, performing frequency domain feature extraction on the training input data; s4, performing correlation mapping on the stability of the missile system and a rudder instruction time sequence signal, and constructing a neural network for steady-state sensing; and S5, designing a controller parameter adaptive adjustment strategy. Real-time stability perception of missile flight is realized, and the defect that stability judgment cannot be performed on a missile when a traditional missile flies is overcome; under the condition that the stability margin of the preset controller is insufficient, the margin boundary of the system is expanded, and the robustness of the controller is improved.

The present invention discloses a method for designing a curved range-increasing trajectory in the mid-course guidance section, belonging to the field of guidance technology, and is applicable to a simple, highly versatile, and engineering-applicable method for designing a curved range-increasing trajectory of a medium- and long-range anti-tank missile using inertial guidance in the mid-course guidance section. Based on the information output by inertial navigation and combined with target information, this method determines the desired altitude trajectory in the mid-course guidance section. A method for solving the desired altitude trajectory in the mid-course guidance section that takes into account both range increase and terminal velocity requirements is provided. This method is characterized by simplicity, strong versatility, and suitability for engineering applications, and has broad application value in similar medium- and long-range anti-tank missile systems. The present invention has been applied in the development process of a certain domestic missile weapon system.

The application discloses a method for constructing and evaluating an air defense anti-missile killing net model based on a granularity super network, and belongs to the technical field of combat systems.The method for constructing the air defense anti-missile killing net model based on the granularity super network comprises task analysis, function component modeling, connection edge modeling and an air defense anti-missile killing net architecture model based on the granularity super network.The application abstracts four types of nodes, i.e., targets, early warning, decision and attack, from an air defense anti-missile combat system based on a combat loop theory, and establishes an air defense anti-missile killing net model based on the granularity super network.The energy reduction degree, energy recovery rate, recovery degree and structural elasticity of the air defense anti-missile killing net based on the granularity super network are all superior to those of an air defense anti-missile system based on a traditional network.Meanwhile, a combat capability evaluation method based on Pythagorean binary semantic fuzziness is proposed, the membership degree of node attribute indexes is accurately determined, and the combat loop capability of the air defense anti-missile killing net and the overall combat capability are quantitatively evaluated.

The invention relates to a missile guidance method, device and equipment based on a digital main line and a storage medium. A missile mechanism model is constructed by using development and production stage data on a digital main line, a missile error compensator is constructed by using test verification stage data on the digital main line, and a missile system hybrid model is constructed based on the missile mechanism model and the missile error compensator. And guided missiles are guided through the guided missile system hybrid model. Compared with the prior art, a large amount of missile flight test data can be provided for training through the data link integrated by the digital main line, the complexity of data fusion is reduced, error compensation is carried out on the missile mechanism model through the missile error compensator of the missile system hybrid model, and the problem of missile guidance error deviation is solved.

Disclosed is a method and system to provide protection for maritime vessels from multiple threat types including shoulder launched rocket propelled threats, ballistic (howitzer), and larger scale missile systems. According to an exemplary embodiment, the protection system is based on the ballistic launch (from the protected vessel) of an explosive charge(s) aimed ˜5 meters away from the vessel and ˜1 meter beneath the waterline followed by detonation to enable the formation of a water wall. Through the formation of a water wall, incident threats can be initiated (piezo fuze) and passivated through dynamic interaction with the water formation. In addition, the upward velocity of the water wall can enable an upwards rotation of the incident threat changing the orientation of the warhead jet formation (for shape charge warheads) above the vessel.

A launch canister comprises a housing in which a 9M96E (2) ground-to-air missile, an upper fixing strap, a lower fixing strap and an external connector are arranged, the structure, the size and the position of the housing are the same as those of straps and connectors of transport launch containers (TLC) of 5B55E, 48H6E and 40H6E missiles, and a base, transport launch containers for supporting a load on the ground during launch of a missile from a launch canister. The external connector of the 9M96E (2) missile is coupled with the external connector of the launch canister through a switching device, and the switching device comprises a multiplexing channel splitter used for transmitting information to the missiles in the launch canister and a distribution board used for setting identification numbers of the missiles in the 35P6E and 40P6E missile systems through jumpers. According to the launch canister, at most four transportation launch containers of ground-to-air missiles with 9M96E (2) can be integrated into a box, and the box is installed for a single installation module of the transportation launch containers of 5E55E, 48H6E and 40H6E missiles. The method has the technical effect that the ammunition cardinal number of 35P6E and 40P6E missile systems is increased by four times.

The invention relates to a multiple missile system that enables the destruction of multiple targets using a single missile in military operations that require extensive damage over a wide range, thereby saving both time and cost.

This application discloses a wind-interference-considered, designated-time, three-dimensional coordinated guidance method, device, and medium. The method relates to the field of guidance technology. The method comprises: establishing a dynamic model for a three-dimensional multi-missile interception of a stationary target; establishing a wind interference model; determining a wind-interference-considered three-dimensional guidance model based on the wind-interference-considered dynamic model and the wind interference model; determining an estimated remaining flight time of the missile system against the stationary target based on the wind-interference-considered three-dimensional guidance model; determining a sliding mode surface of the missile system's attack time error based on the total flight time of the designated missiles and the estimated remaining flight time of the missile system against the stationary target; determining a wind-interference-overcoming designated-time coordinated guidance law based on the missile system's wind-interference-overcoming sliding mode surface based on the adaptive theory and Lyapunov theory; and guiding the missile system based on the wind-interference-considered designated-time coordinated guidance law. This application can improve the accuracy and stability of missiles.

The invention provides an inertial control all-in-one machine and a navigation control method thereof.The inertial control all-in-one machine comprises an inertial navigation assembly, and the inertial navigation assembly collects inertial measurement signals of a carrier, obtains motion parameters of the carrier and sends the motion parameters to a missile-borne computer; the missile-borne computer receives the motion parameters of the inertial navigation assembly, communicates with a carrier and other subsystems on the carrier, and sends control signals to the electric comprehensive control combination and other subsystems; and the electric comprehensive control combination receives a control signal of the missile-borne computer and executes a corresponding control action. Through the integrated design of the inertial navigation system and the control system, the overall miniaturization of the missile system is realized, and the time period and the economic cost of the design of the missile system are reduced.

The invention relates to a high-performance microstrip conformal data link antenna which comprises a first data link PCB, a second data link PCB, a third data link PCB and a fourth data link PCB, and the four data link PCBs are connected and fixed through screws. Radiation patches are arranged on the front side and the back side of the first data link PCB, first through holes are formed in the peripheries of the radiation patches, and a power divider assembly is arranged on the third data link PCB; the second data link PCB and the fourth data link PCB are both metal grounds. According to the invention, the anti-interference capability and the signal receiving quality of the antenna in a complex electromagnetic environment are improved, and reliable communication between a missile and a control system is ensured; the performance stability of the antenna in an extreme environment is enhanced, and the requirements of a missile system for high reliability and long service life are met; by optimizing indexes such as antenna size, weight and power consumption, the overall performance and combat effectiveness of a missile system are improved.

The invention relates to a missile-borne inertial measurement unit self-calibration method based on an orientation transfer mode, and belongs to the technical field of navigation guidance and control. After a missile is delivered out of a warehouse, an initial orientation is transferred to a missile-borne inertial measurement unit in an optical aiming mode, an orientation reference error transfer equation is established, and the self-calibration of the missile-borne inertial measurement unit is realized in a zero-speed and orientation matching mode; the observability of the zero error of the fiber-optic gyroscope is improved, the zero error of the fiber-optic gyroscope is estimated by using a Kalman filter, the observable precision of the error is judged, and the transmission redundancy self-calibration based on the azimuth reference is realized; according to the method, the high-precision light aiming system is used as a truth value reference, so that the attitude precision of the missile-borne inertial measurement unit is improved; the self-calibration capability of a missile system is improved, and the navigation precision and reliability of a missile in a complex environment are enhanced.

The invention discloses a portable laser anti-interference system and a working method. The laser anti-interference system comprises a detection tracking unit used for searching, finding, tracking and identifying a'low, slow and small 'target; the laser damage unit is used for generating high-energy laser beams and damaging a target, the laser damage unit comprises an air-cooled laser light source, a beam space energy synthesis module and a beam positioning module, and the laser beams emitted by the air-cooled laser light source are subjected to beam energy convergence through the beam space energy synthesis module; the light beam orientation module emits a high-energy laser beam sent by the light beam space energy synthesis module at the same angle according to target angle information provided by the detection tracking unit, and realizes laser damage of a target according to an attack target distance and a matching light spot focusing distance; the control unit is used for guiding the detection tracking unit to track the target and controlling the laser damage unit to damage the target; and the guarantee unit is used for supplying power to the detection tracking unit, the laser damage unit and the control unit and performing time service positioning.

The application relates to a wireless transmission energy control device and a wireless transmission energy control method, and solves the problems of multiple missile cable transmission, large weight and large occupied space of the energy control device. The device comprises an energy control management module and an energy control execution module, the energy control execution module comprises a sending end and at least one receiving end, the sending end comprises a first coupling coil and a first wireless transceiver module, and the receiving end comprises a second coupling coil and a second wireless transceiver module; the energy control management module is used for receiving a missile instruction and sending the instruction to the sending end; the sending end is used for receiving an external current and transmitting electric energy to the corresponding receiving end through the coupling effect of the first / second coupling coil, and transmitting the missile instruction to the corresponding receiving end through wireless communication between the first / second transceiver modules; and the receiving end is used for controlling the corresponding missile system according to the missile instruction. The number of cables and the occupied space are reduced, and the maintenance difficulty of the weapon equipment is reduced.

The invention provides a metal-cover-free elastic wall cable and an individual guided missile and guided missile system thereof, and the elastic wall cable is of a flat strip-shaped structure, and comprises a conductive core wire layer which is formed by arranging a plurality of insulated wires side by side or in a twisting manner from inside to outside in sequence; the insulating coating layer partially or completely coats the conductive core wire layer; the electromagnetic shielding and protecting outer layer completely coats the outer part of the insulating coating layer; and the elastic wall cable is directly fixed on the outer surface of the engine compartment through a bonding layer. According to the invention, a raised metal protective cover is abandoned, and the flat cable is directly attached to the wire passing groove preset in the surface of the projectile body, so that the outer surface of the cable is basically flush with the engine compartment shell. The fairness of the aerodynamic shape of the missile body is greatly guaranteed, the flight resistance is reduced, an asymmetric flow field caused by sudden change of the shape is avoided, and therefore the flight stability and the control precision of the missile are improved.

The application provides a heterogeneous network air defense and anti-missile system coordination method, device and equipment, the method comprises the following steps: selecting coordination equipment based on coordination rules in at least reconnaissance equipment and striking equipment; forming multiple air defense and anti-missile coordination networks based on the coordination equipment and other category equipment different from the coordination equipment; evaluating the multiple air defense and anti-missile coordination networks based on evaluation indexes to determine a target air defense and anti-missile coordination network with a coordination effect meeting requirements; wherein the evaluation indexes comprise a flexibility index about whether the network structure can be quickly adjusted to respond to different requirements, an economy index about whether the communication and maintenance cost is too high, and an attack and defense index about the size of the enemy killing and defense capability. The method provided by the application is used for quickly forming multiple air defense and anti-missile coordination networks, and can objectively and comprehensively evaluate the multiple networks to determine a target air defense and anti-missile coordination network with a coordination effect meeting requirements.

The present invention relates to a missile-borne inertial system self-calibration method based on an azimuth transfer mode, belonging to the technical field of navigation, guidance and control. After a missile is released from a warehouse, the present invention uses optical aiming to transfer the initial azimuth to the missile-borne inertial system, establishes an azimuth reference error transfer equation, improves the observability of the fiber optic gyroscope zero-position error through a zero-speed and azimuth matching method, and uses a Kalman filter to estimate the fiber optic gyroscope zero-position error, judge the error observable accuracy, and realize redundant self-calibration based on azimuth reference transfer. The present invention uses a high-precision optical aiming system as a true value reference to improve the attitude accuracy of the missile-borne inertial system. The present invention improves the self-calibration capability of the missile system and enhances the navigation accuracy and reliability of the missile in complex environments.

A hypersonic self-guided missile system is described. Particularly, embodiments describe missiles whose trajectories are controlled by an on-board control unit that decrease the effect of damaging heat to sensitive internal components by employing one or more annular windows, internal mirrors, lenses, and / or cameras. Embodiments may have an internal camera oriented substantially toward or away from the nose of the missile.