220 results about "Missile guidance" patented technology

A missile guidance system designed to operate on GPS signals in an anti-jamming environment. The inventive system includes first, second and third airborne vehicles (20). A GPS receiver (24) is mounted on each of the three vehicles (20) to receive signals transmitted from spaceborne satellites (14). Each vehicle (20) acts as a pseudo-satellite or "pseudolite'. The received GPS signals are processed by a processor (26) to provide a first intermediate signal indicating the position of the vehicle (20). This signal is retransmitted from each vehicle and received by a GPS receiver mounted on a missile. The received intermediate signal is processed on the missile to provide an output signal indicating the position thereof. The pseudolites would be airborne in the vicinity of a target area. Because the pseudolites are relatively close to the targets compared to a satellite in high altitude orbit and because the pseudolites would be able to transmit a kilowatt or more power, the signal strength may be improved significantly. To succeed as a jammer, a jammer, successful against GPS satellites, would need considerably more power to succeed against aircraft carried pseudolites. The pseudolite system delivers GPS signals into the target area 40-70 dB stronger than signals coming directly from GPS satellites. By timing the signals for 100% time coverage, enemy C / A code receivers will be jammed because they are limited to a J / S capability of 30 dB.

A multifunction millimeter-wave system (10) that provides simultaneous and prioritized active radar protection and surveillance, high digital data rate communications, interceptor missile guidance, passive surveillance and IFF interrogation for a military vehicle. The system (10) includes a multi-function control computer (14) that provides high level control functions. The system (10) also includes a plurality of azimuth sector sub-systems (12), each including a steerable antenna (26) that directs a millimeter-wave beam to a particular location within the area covered by the sector sub-system (12). Each sector sub-system (12) also includes an FPGA-based modem (20) that performs digital signal processing for the various system operations, such as signal modulation and demodulation. Each sector sub-system (12) also includes an IF / RF transceiver (22), including a direct digital synthesizer (24), for providing signal tuning and frequency up-conversion and down-conversion.

A generalized Hough transform is used to acquire and track vehicular targets for missile guidance. This is accomplished by recognizing that most vehicles have silhouettes that may be described as a “rounded rectangle”. The position and shape of such rounded rectangles is described in terms of 5 parameters (xc, yc, a, b, θ) where xc, yc are the center coordinates, a,b are the major and minor axis and Θ is the orientation. The computation of a five dimensional Hough transform on an image including such a target will produce the five parameters that provide the “best fit” rounded rectangle to the target. These parameters are then passed to a missile tracker. This capability can be used to improve track gate handoff from the automatic target recognizer (ATR) to the missile tracker, changing aspect ratios of maneuvering targets, limited lock-on after launch (LOAL), aimpoint designation and fire control system to missile seeker handover.

The invention discloses a guidance and control integrated design method considering all-strapdown seeker view field constraint, and aims at solving the technical problem that an existing guidance and control integrated design method is poor in practicability. According to the technical scheme, the guidance and control integrated design method comprises the steps that a missile longitudinal channel attitude control system model, a longitudinal plane missile-target relative motion model and an all-strapdown seeker longitudinal channel sight decoupling model are built; the state variable and the system output variable are selected, and a guidance and control integrated state space mathematical model considering view field angle constraint is built; a control method combining an obstacle Lyapunov function, an expansion state observer and dynamic surface control is adopted. The control method combining the obstacle Lyapunov function, the expansion state observer and dynamic surface control is adopted, and meanwhile the guidance precision and the all-strapdown seeker view field angle constraint conditions are met, so that it is guaranteed that the body sight angle detected by an all-strapdown seeker in the missile guidance and control process meets the seeker view field constraint.

A method for engaging a hostile missile with an interceptor missile includes mathematically dividing an estimated target trajectory into portions, the junction of each portion with the next defining a possible intercept point. The engagement for each possible intercept point is modeled, to generate a probability of lethal object discrimination which is processed to generate a probability of intercept for each of the possible intercept points. The intercept point having the largest probability of intercept defines a selected intercept point from which intercept missile launch time is calculated, interceptor missile guidance is initialized, and the interceptor is launched at the calculated launch time and under the control of the interceptor missile guidance. Also, a method for estimating discrimination performance of a system of sensors includes generating sensor data signal-to-noise ratio and an aspect angle between the sensor and a lethal object. A table of probability of lethal object discrimination is generated as a function of the signal-to-noise ratio and aspect angle. The signal-to-noise ratio and the aspect angle are quantized into bins and the table with at least the signal-to-noise ratio and the aspect angle is entered to determine the probability of lethal object discrimination.

A system, processing structure and method for performing vehicle intercept includes target acceleration estimation or blocking via a filter prior to deriving an interceptor acceleration time history via a guidance law. In the processing structure where the unknown target accelerations are blocked from affecting estimates, a guidance law is generated, stored and retrieved accounting for worst case target acceleration. In the processing structure where the target acceleration is presumed constant with a constant bank angle, the guidance law is closed form, exploiting constant heading angular velocity, and thus generated online.

The invention discloses a semi-physical real-time simulation system of a laser guided missile. The system is used for carrying out simulation test on a missile laser guide head, an electric steering engine and a missile guidance control algorithm. The system comprises a signal simulation part used for generating the laser received by a simulation guide head, a motion simulation part used for simulating the relative motion relation between a missile and a target; a test main control part used for running the missile motion simulation software in real time, driving the whole simulation system, monitoring and recording data in the whole test process, and analyzing the data. The method aims to provide an auxiliary design tool for missile designers, so that designers can know problems possiblyexisting in the missile performance and design. The development period of missiles is shortened, and the number of external field flight tests is reduced. The system has better practicability and higher economic benefits.

A system and method for determining a 3-dimensional target position and velocity using 2-dimensional IR sensor angular measurements for objects travelling in a ballistic manner within an IR sensor's field of view (FOV). Resulting 3-dimensional states may be used to generate updated inputs for correlation and object selection to drive missile guidance and intercept operations.

The invention relates to a method for constructing missile guidance information, in particular to a method for constructing seeker guidance information of half-strapdown seeking, and belongs to the technical field of missile guidance system design. The invention provides a new method for constructing the seeker guidance information of half-strapdown seeking; and the method carries out frame angular rate evaluation based on Unscented Kalman filter (UKF), then carries out guidance information construction, effectively improves the construction precision of the guidance information, prevents error amplification caused by the method for acquiring angular rate by directly carrying out angular differentiation for a frame, has high guidance information precision compared with the method adoptingEKF filter construction, and can control the missile to fly to a target according to the proportional guidance under disturbance condition. The method can be widely applied to various guidance weapons of half-strapdown seeking, and has important military application prospect.

An accurate and rapid method for characterizing the performance of an APD and setting its operating voltage Vop to an optimal value uses an on-board LED or other pulsed light source to measure APD responses at different operating voltages Vop. An estimated breakdown voltage Vb is determined by comparing the measured responses, and the Vop is adjusted to a new value at a fixed offset from the estimated Vb. The fixed offset is selected according to ambient light conditions, including the presence or absence of light background noise, and whether the sun is partially or fully in the field of view. The method is iterated until convergence, or until a maximum number of iterations is reached. In embodiments, a plurality of APD's having a common Vop can be adjusted, and the Vop is never set below a minimum value VopBW necessary to meet timing requirements for a missile guidance system.

An optically-aided, inertially guided missile. The inventive missile includes a receiver for accepting guidance commands from a source located on an independent frame of reference relative to the missile and providing a first signal in response thereto. A filter is mounted on the missile for processing the first signal and providing a second signal in response thereto. The filter outputs commands to a navigation system which provides missile guidance commands in a conventional manner. In the illustrative implementation, the filter is a Kalman filter configured to eliminate the effects of gunner jitter and optical guidance system noise thereby significantly improving missile terminal performance at long ranges. In the illustrative implementation, the navigation system includes an inertial sensor assembly. The navigation system outputs a signal representative of missile-to-target cross track position and velocity in response to outputs from the sensor assembly and the filter. A guidance law is used by the system to compute missile acceleration commands in response to the missile-to-target cross track position and velocity. Thereafter, fin control commands are generated by an autopilot in response to the missile acceleration commands in a conventional manner.

The invention relates to a double-rotary table semi-physical simulation system and method for a full strapdown missile guidance control system. A guide head, body sight simulation rotary tables, a target simulator, an inertia group, a missile-borne computer, a posture simulation rotary table, a steering gear, a steering gear loading system, a real-time master control simulation machine, a data acquisition computer and a reflective memory network are included; one rotary table is used for simulating the attitude motion, and the other rotary table is used for simulating motion of a missile relative to the body sight. By means of the system, two three-axis rotary tables are used for replacing five-axis rotary tables required during semi-physical simulation of a traditional full strapdown missile guidance control system, and the complexity and cost of the simulation platform are effectively reduced.

The invention relates to a design method of a fast convergence Kalman filter for estimating the missile and target line-of-sight rate, and belongs to the technical field of missile guidance control. The method is provided to improve the convergence speed of present target-missile line-of-sight rate estimating Kalman filtering methods. The method comprises the following steps: setting an initial filter estimate; measuring and calculating the relative distance and the relative rate between a target and a missile at present; measuring and calculating the components of the acceleration of the missile in o' y4 and o' z4 axis directions of a line-of-sight coordinate system; constructing a pitching channel fast-convergence by suing a missile pitching channel line-of-sight motion state equation and a pitching channel line-of-sight angle measurement equation, constructing a yaw channel fast-convergence Kalman filter by using a missile yaw channel line-of-sight motion state equation and a yaw channel line-of-sight angle measurement equation, and respectively finding the line-of-sight pitch angle rate and the line-of-sight yam angle rate between the target and the missile. The method improves the convergence speed of the Kalman filter to obtain high-precision line-of-sight rate estimation.

The invention discloses a semi-strapdown air-to-air missile guidance method based on a sliding mode variable structural theory. The semi-strapdown air-to-air missile guidance method comprises the following steps of 1, acquiring a missile-target line-of-sight turn rate differential model under a line-of-sight coordinate system; 2, acquiring a motion tracking sliding mode guidance rule; and 3, acquiring an expected line-of-sight turn rate xd. According to the method, a sigmoid function is applied to the sliding mode surface design of the motion tracking sliding mode guidance rule, the missile-target line-of-sight angular rate is improved at the initial guidance stage, the estimation to the target motion state is improved, the missile-target line-of-sight angular rate is made to be zero at the last guidance stage, the miss distance is lowered, and the missile hit precision is improved.

The invention relates to a method for determining laser beam rider guidance information field initial fixed focus parameters. The method comprises the following steps of: (1) determining an entire missile guidance control system chart; (2) determining a mathematical model of each pane of the control system chart; (3) stringing the mathematical model of a lead compensation network to the control system chart; (4) designing a lead compensation network according to the requirements of the system on convergence rate of an introduction section trajectory; and (5) designing laser link transfer coefficients so that a step response curve of the laser link transfer coefficients is closest to the step response curve of the lead compensation network. The design results of the laser link transfer coefficients obtained from the step (5) are the laser beam rider guidance information field initial fixed focus parameters determined by the invention. The method provided by the invention can be used for fast and accurately designing the laser beam rider guidance information field initial fixed focus parameters and meets the requirements of the system on convergence rate of an introduction section trajectory.

The invention discloses an H-plane waveguide power divider. The H-plane waveguide power divider comprises a coupling cavity, an input port, an isolation port B, an isolation port C, an isolation port A, an output port A and an output port B, wherein the input port, the isolation port B, the isolation port C, the isolation port A, the output port A and the output port B are communicated with the coupling cavity; and the input port is located at a front end face of the coupling cavity, the isolation port A is located at a rear end face of the coupling cavity, the front end face and the rear end face are two mutually-symmetrical opposite faces of the coupling cavity, the isolation port B and the isolation port C are respectively located at the two sides of the input port, and the output port A and the output port B are respectively located at the two sides of the isolation port A. The H-plane waveguide power divider further has the characteristics of simple structure, small volume and low processing difficulty. The H-plane waveguide power divider can be widely applied to the military and civilian fields of antenna arrays, phased-array radar, power synthesis, missile guidance, communications and the like.

The invention discloses a multi-missile time cooperative missile guidance method and system. The method comprises the following steps that (1) a guidance kinematics model of each missile in a missile group is established; (2) for the established guidance kinematics model of each missile, CPN guidance laws for a stationary target and a maneuvering target are given respectively, and missile guidance based on the CPN guidance laws is completed; wherein when the CPN guidance laws are determined, the missile group consistency expected remaining flight time is calculated based on a weighted average consistency method; and based on a multi-agent depth deterministic strategy gradient algorithm, the missiles learn and decide CPN guidance law correlation coefficients. According to the method, the multi-agent DRL is applied on the basis of the existing time cooperative guidance law CPN to endow the missile group with the intelligent sensing and decision-making ability, the guidance precision can be improved, the cooperative time error can be reduced, and effective attacks can be achieved for static and maneuvering targets respectively.

A method and apparatus for guiding a vehicle to intercept a target is described. The method iteratively estimates a time-to-go until target intercept and modifies an acceleration command based upon the revised time-to-go estimate. The time-to-go estimate depends upon the position, the velocity, and the actual or real time acceleration of both the vehicle and the target. By more accurately estimating the time-to-go, the method is especially useful for applications employing a warhead designed to detonate in close proximity to the target. The method may also be used in vehicle accident avoidance and vehicle guidance applications.

The invention discloses an attack angle constrained high-speed interception guidance method. The attack angle constrained high-speed interception guidance method comprises the following steps of establishing the relative motion relation between a guided missile and a target with the longitudinal plane where the guided missile and the target are located as an attack plane to obtain an expression ofrelative motion parameters; deducing expressions of the zero effort miss and zero effort speed according to the missile-target relative motion parameters; making the zero effort miss and zero effortspeed as first-layer sliding mode variables according to the hierarchical sliding mode theory and combining a first-layer sliding mode into a second-layer mode; and selecting an exponential reaching law, making the exponential reaching law equal to the second-layer mode about the time derivative and then solving the falling angle constraint missile guidance law of a high-speed flight missile. Through the attack angle constrained high-speed interception guidance method, the missile hits on the target at the preset angle of sight to improve the destroy effect. When the missile intercepts the target at high speed, the missile hits on the target with small zero effort miss. Thus, the attack angle constrained high-speed interception guidance method has good reliability.

The invention discloses a strip-line high-pass filter. The strip-line high-pass filter comprises a transmission line and at least two shorting stubs which are connected with the transmission line, wherein the transmission line is mainly formed by a metal cavity and an inner conductor arranged inside the metal cavity; each shorting stub is mainly formed by a stub cavity and a stub inner conductor arranged inside the stub cavity; the adjacent shorting stubs are located at one side or two sides of the metal cavity. The strip-line high-pass filter disclosed by the invention has the advantages of simplicity in machining, convenience in debugging and compact structure. The strip-line high-pass filter disclosed by the invention is hopeful to be widely applied to an electronic system of each microwave waveband, and is particularly suitable for military and civil fields of radars, missile guidance, communication and the like.

A missile guidance system semi-physical simulation method of the invention includes the following steps: (1) a missile-target engagement mathematical model, a target simulator motor speed control model and a CCD camera motor speed control model are established in a host machine; (2) TCP / IP communication between the host machine and a target machine is established, and the TCP / IP communication is compiled to the target machine; (3) a CCD camera is powered on, and an image of an area where a target simulator is located is taken; (4) the image is transmitted to a target tracking experimental turntable control box; (5) a target is identified; (6) an operator uses a rocker to lock the target, and outputs the misalignment angle of a missile seeker to the target machine; (7) the process in whichthe missile seeker tracks the target is simulated; (8) the angular position and angular velocity information of the motor and the line-of-sight angular velocity are obtained; (9) key data in the simulation process is monitored in real time through the display of the target machine; and (10) the target machine feeds back the calculation result through a TCP / IP mode to the host machine for subsequent data analysis.

The present invention discloses a modular wave filter which belongs to the filed of microwave communication and mainly settles the problems of high machining cost and long period in the prior art. Themodular wave filter comprises an input / output structure, a coupling metal sheet, a waveguide metal sheet, a resonant metal sheet, and a coupling turning screw positioned on the coupling metal sheet and a resonant turning screw positioned on the resonant metal sheet, wherein, the coupling metal sheet, the waveguide metal sheet and the resonant turning metal sheet are modular membranes which are designed beforehand. The modular wave filter has advantages of simple structure and convenient fabrication, can complete the designing and fabrication of the wave filter requested by the user, and is mainly used for the systems of microwave communication, radar, missile guidance, etc.

The invention discloses a method for controlling the decoupling guidance of a rotary missile. The method comprises the following steps that 1) a racemization cabin section is arranged between the front cabin section and the rear cabin section of the rotary missile; 2) an inertia measuring element is installed in the front cabin section, so that an accelerometer of the inertial measurement elementand the sensitive axis of a gyroscope are parallel to each axis of the front cabin section of the rotary missile; 3) the three-axis angular velocity data and the acceleration data output by the inertia measuring element are collected and calculated through a control plate, and a rolling angle value coupled to the front cabin end is obtained; and 4) a motor in the racemization cabin section is controlled by calculating the difference between the rolling angle of the front cabin section and the set rolling angle, so that coupling among three channels namely, the yaw, pitching and rolling-rotation is reduced to the minimum, wherein the racemization cabin comprises a shell, a motor and a bearing are arranged inside the shell, shafts are arranged inside the motor and the bearing, slip rings arearranged inside the shafts, and one ends of the shafts are provided with structural connecting ports of the rear cabin section. And therefore, the problems that coupling of the yaw and pitching channels is strong in the existing rotary missile guidance, and the control is difficult are solved.

The invention discloses a loaded power divider. The loaded power divider comprises a coupling cavity, an input terminal, an output terminal, a coupling terminal and an isolation terminal, wherein the input terminal, the output terminal, the coupling terminal and the isolation terminal are communicated with the coupling cavity; the input terminal and the isolation terminal are located at a front end face of the coupling cavity, the coupling terminal and the output terminal are located at a rear end face of the coupling cavity, the isolation terminal is located at the right side of the input terminal, and the coupling terminal is located at the right side of the output terminal; and columnar bodies are arranged in the coupling cavity, are arranged into at least three rows along the direction of the front-rear axis of the input terminal, are arranged into at least two columns along the direction vertical to the front-rear axis of the input terminal, and are connected with an upper internal wall or lower internal wall of the coupling cavity. The power divider disclosed by the invention has over 59% relative operating bandwidth and has the characteristics of simple structure, small volume and low processing difficulty. The loaded power divider can be widely applied to the military and civilian fields of antenna arrays, phased-array radar, power synthesis, missile guidance, communications and the like.

The invention discloses a guided missile track and posture coordinated control system under side window detection conditions. The system comprises an initial roll angle command calculation module, an initial index angle calculation module, a roll angle command deviation calculation module with feedback items, an index angle calculation module under the condition providing the feedback items and a final roll angle command calculation module. A guided missile track and posture coordinated control method under the side window detection conditions is provided; and the problem about control commands of a roll angle controller is solved, a guided missile provided with a side window guide head can meet the side window detection posture control requirement and the guided missile guidance accuracy requirement at the same time.

The invention discloses a RapidIO-based high-speed communication method between SoC chips of an on-board system. Six transfer rates are included, based on a RapidIO 3.1 communication protocol, according to market demands, the RapidIO interface of SoC chips is configured with four transfer modes: an AXI bus mode, a DMA transfer mode, a DME transfer mode, and a doorbell mode. The communication method designs an automatic transmission method, according to the amount of data to be transmitted and destination address basic information, the most efficient transfer mode is selected from four transfermodes automatically, that transmission bandwidth is fully utilized, the problem of high speed communication between SoC chips and other connected chip-to-terminal equipment in missile guidance systemis solved, and the requirements of large data volume and small data volume are met. The transmission rate can reach 10.3125 Gbps, and the utilization ratio of transmission bandwidth can be increasedfrom 30% to 52%. The method is suitable for most hardware transmission interfaces on the market.

The invention discloses a method for suppressing ultra-low-altitude target mirror image interference using the Brewster effect. The method comprises the steps of setting up, according to an ultra-low-altitude target-environment coupling scattering mechanism, a four-path electromagnetic simulation model, obtaining the mirror image interference scattering intensity of an ultra-low-altitude guided missile target under different battlefield environments, and finding an optimal Brewster's angle of attack under each corresponding environment. Simulation of target-environment composite scattering characteristics under various conditions is performed by using the electromagnetic calculation model, the Brewster's angle in each different environment is found and the signal-to-interference ratio characteristics under the Brewster's angles are compared. According to different target parameters, guidance parameters of a guided missile and the guided missile tracking law are subjected to guided missile guidance rate constraint and optimization design, the grazing angle is enabled to be as close to the Brewster's angle as possible according to a certain optimization method, and the Brewster ballistic optimization design is completed. According to the invention, the suppression performance of the ultra-low-altitude target mirror image interference can be improved with low signal processing cost.

The embodiment of the invention provides a missile guidance method and device. The missile guidance method comprises the steps that according to the spatial position of an attack target and the spatial positions of all to-be-guided missiles, the coordinated attack time of all the to-be-guided missiles is obtained based on a proportional guidance method; according to the coordinated attack time andpreset terminal acceleration of all the to-be-guided missiles, a model prediction and static planning algorithm is used for the first time to obtain a set of control variables; according to the coordinated attack time, all the preset terminal acceleration and preset attack angles of all the to-be-guided missiles, the model prediction and static planning algorithm is used for the second time to guide all the to-be-guided missiles; and the control variables serve as initial control variables for using the model prediction and static planning algorithm for the second time. According to the missile guidance method and device, attack time and attack angle coordinated guidance of the multiple missiles is achieved, meanwhile, the model prediction and static planning algorithm can be rapidly converged, and the guidance efficiency and precision are improved.