20 results about "Missile system" patented technology

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 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.

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 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 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.

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.

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 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.

The application discloses a guidance instruction analysis method based on control stiffness analysis, relates to the field of aircraft control and comprises the following steps: S1, acquiring a leading head signal, an input signal of a filter, an output signal of the filter and time before and after a unit step of a autopilot; S2, analyzing an equivalent time constant of a missile dynamics system; S3, calculating a normal demand overload n yc and a lateral demand overload n zc of a non-rolling missile system; S4, analyzing a normal overload instruction in a pitching channel in a guidance process; and S5, analyzing a rolling angle instruction of the missile. The control stiffness is a ratio of total guidance time and the equivalent time constant of the missile dynamics system, and necessary control stiffness is a prerequisite for ensuring the hitting precision of the missile. When the guidance time is greater than the equivalent time constant of the missile dynamics system by a set multiple, a trajectory is basically converged, the sign of the lateral demand overload can be used to finely adjust the rolling angle instruction, the effect of reducing the oscillation of the rolling angle instruction is achieved, and the quality of the guidance instruction is improved.

The present invention discloses an adaptive designated attack time guidance method, device, medium, and product for attacking maneuvering targets, belonging to the field of missile interception guidance. This method first establishes a dynamic model for a single missile intercepting a single maneuvering target and an expression for estimating the remaining flight time. It then develops an attack time error sliding mode surface and an adaptive nonlinear designated time guidance law. This model is then applied to a multi-missile system intercepting a single maneuvering target. After setting a desired attack time for each missile in the multi-missile system, the adaptive nonlinear designated time guidance law ensures that the attack time error for each missile converges to zero within a finite time, ensuring that each missile hits the maneuvering target at the desired attack time. This method enables a multi-missile system to intercept a maneuvering target at a designated attack time.