Study on Missile Intelligent Fault Diagnosis System Based on Fuzzy NN Expert System

In order to study intelligent fault diagnosis methods based on fuzzy neural network (NN) expert system and build up intelligent fault diagnosis for a type of missile weapon system, the concrete implementation of a fuzzy NN fault diagnosis expert system is given in this paper. Based on thorough research of knowledge presentation, the intelligent fault diagnosis system is implemented with artificial intelligence for a large-scale missile weapon equipment. The method is an effective way to perform fuzzy fault diagnosis. Moreover, it provides a new way of the fault diagnosis for large-scale missile weapon equipment.

Multi-agent decision support system for missile defense based on improved PSO algorithm

Ballistic missile defense system (BMDS) is important for its special role in ensuring national security and maintaining strategic balance. Research on modeling and simulation of the BMDS beforehand is essential as developing a real one requires lots of manpower and resources. BMDS is a typical complex system for its nonlinear, adaptive and uncertainty characteristics. The agent-based modeling method is well suited for the complex system whose overall behaviors are determined by interactions among individual elements. A multi-agent decision support system (DSS), which includes missile agent, radar agent and command center agent, is established based on the studies of structure and function of BMDS. Considering the constraints brought by radar, intercept missile, offensive missile and commander, the objective function of DSS is established. In order to dynamically generate the optimal interception plan, the variable neighborhood negative selection particle swarm optimization (VNNSPSO) algorithm is proposed to support the decision making of DSS. The proposed algorithm is compared with the standard PSO, constriction factor PSO (CFPSO), inertia weight linear decrease PSO (LDPSO), variable neighborhood PSO (VNPSO) algorithm from the aspects of convergence rate, iteration number, average fitness value and standard deviation. The simulation results verify the efficiency of the proposed algorithm. The multi-agent DSS is developed through the Repast simulation platform and the constructed DSS can generate intercept plans automatically and support three-dimensional dynamic display of missile defense process.

Steady Fault Characteristic Analysis of a Missile Power System Based on a Differential Evolution Algorithm

The differential evolution (DE) algorithm is applied to solving themodels''equations of a whole missile power system, and the steady fault characteristics of the wholesystem are analyzed. The DE algorithm is robust, requires few control variables, is easy to use andlends itself very well to parallel computation. Calculation results indicate that the DE algorithmsimulates faults of a missile power system very well.

Intelligent Design and Implementation of Missile Fire Control System

Missile fire control system is the core of ship-based missile weapon system, whose safeguard level has direct relation with the attack ability of naval vessels. After a long period of deep investigation and research, it was found that, in one missile fire control system, there are such problems as single safeguard system, low ratio of cost to efficiency, etc. By adopting intelligent control techniques and many measures to multiple securities, the new type of assistant system is designed, some difficult problems are solved, such as fixed project channel and unitary means of missiles, which can make the equipment carry out combat mission reliably and continuously.

Modelling missile motion system using neural networks

The models of noallnear systems are idendried by recmeive pedctive ermrs(RPE) methed based on thelayered neural networks. To improve the identification precision, gain callcient and arentUm factor are itheucedinto the algorithm for the data are dids by noses and vny suddnly. this lerthm is applied to the twcmedeiling of rolling and pitchng angles of ndssiles. Simulation results shoW tha the proposed algurithm is sultable forthe modelling of nodrinear systems.

Simulation of Control and Guidance System for the Spinning Missile

Adopted for some small-size short range surface-to-air missiles and antitank guided missiles is a single-channel control method of making missile rotating around its longitudinal axis. In hardware-in-the-loop simulations of the guidance and control system for these kinds of spinning missiles, improper use of special simulation equipment and test method will cause significant errors, even lead to failure of the simulation. In this article, the author gives an analysis of the causes of significant errors and failure of the simulation, and puts forward a solution, which is improved workable in making the hardward-in-the-loop simulation successful.

Dynamic Simulation for Missile Erection System

In order to study the dynamic characteristics of the missile erection system,it can be considered as a rigid-flexible coupling multi-body system.Firstly,the actual system is abstracted as an equal and simplified one and then the forces applied to it are analyzed.Secondly,the rigid-flexible coupling dynamic simulation for erection system is accomplished by use of the system simulation software,for example Pro/E,ADAMS,ANSYS,MATLAB/Simulink,etc.Finally,having the aid of simulation results,the kinetic and dynamic characteristics of the flexible bodies in erection system are analyzed.The simulation considering the erection system as a rigid-flexible coupling system can provide valuable results to the research of its kinetic,dynamic and vibrational characteristics.

Integrate Fuzzy Logic Stable Control System of Bank-to-Turn Missiles

The question of stable control system of bank-to-turn (BTT) missiles is a bottleneckin BTT technology. Integrate fuzzy logic stable control system of BTT missiles is designed in whichthree main problems are resolved. How to select input variables Of the fuzzy logic controller and howto guarantee completeness of the output control are two of them. The last one is how to coordinatethe fuzzy logic controllers in integrate fuzzy logic stable control system. Simulating results prov that integrate fuzzy logic stable coatrol system of BTT missiles is sueccessful, and it can be widelyused in future.

Fire Distribution of Integrated Missile-gun Air Defense System Based on Earlier Damage Criterion

The fire distribution can be divided into weapon assignment and firing time scheduling. The criterion of weapon allocation is that a target with greater threat has higher priority. And the criterion of firing time scheduling is that a target can be damaged with the expected probability before a specific time. A fire distribution scheme and a program for the integrated missile-gun air defense system based on a criterion of earlier damage were presented. An example was taken to illustrate its effectiveness.

Distributed Air &Missile Defense with Spatial Grasp Technology

A high-level technology is revealed that can effectively convert any distributed system into a globally programmable machine capable of operating without central resources and self-recovering from indiscriminate damages. Integral mission scenarios in Distributed Scenario Language (DSL) can be injected from any point, runtime covering & grasping the whole system or its parts, setting operational infrastructures, and orienting local and global behavior in the way needed. Many operational scenarios can be simultaneously injected into this spatial machine from different points, cooperating or competing over the shared distributed knowledge as overlapping fields of solutions. Distributed DSL interpreter organization and benefits of using this technology for integrated air and missile defense are discussed along with programming examples in this and other fields.

Analysis and improvement of missile three-loop autopilots

The non-minimum phase feature of tail-controlled missile airframes is analyzed. Three selection strategies for desired performance indexes are presented. An acceleration autopilot design methodology based on output feedback and optimization is proposed. Performance and robustness comparisons between the two-loop and classical three-loop topologies are made. Attempts to improve the classical three-loop topology are discussed. Despite the same open-loop structure, the classical three-loop autopilot shows distinct characteristics from a two-loop autopilot with PI compensator. Both the two-loop and three-loop topologies can stabilize a static unstable missile. However, the finite actuator resource is the crucial factor dominating autopilot function.

A framework for equipment systems-of-systems effectiveness evaluation using parallel experiments approach

Equipment systems-of-systems （SOS） effectiveness evaluation can provide important reference for construction and optimization of the equipment SoS. After discussing the basic theory and methods of parallel experiments, we depict an SoS effectiveness analysis and evaluation method using parallel expe- riments theory in detail. A case study is carried out which takes the missile defense system as an example. An artificial system of the missile defense system is constructed with the multi-agent modeling method. Then, single factor, multiple factors and defense position deployment computational experiments are carried out and evaluated with the statistical analysis method. Experiment re- sults show that the altitude of the secondary interception missile is not the key factor which affects SoS effectiveness and putting the defense position ahead will increase defense effectiveness. The case study demonstrates the feasibility of the proposed method.

Output-feedback based partial integrated missile guidance and control law design

An output-feedback based partial integrated guidance and control (IGC) law for missile interceptor is proposed with the smooth finite time convergence property. Firstly, a novel outputfeedback based smooth sliding mode control is proposed for a class of nonlinear systems in the presence of immeasurable state and disturbance. The finite time convergence property of this control scheme is proved based on the Lyapunov stability and homogeneous principle. Then, the proposed control method is applied to the design of partial IGC law. A kind of scaling methods is also developed to reach the rapid convergence of the system. An important dominance of this control scheme is the smooth characteristic, which may result in chattering free convergence. The simulation results indicate the high precision and smooth elevator deflection of the proposed output feedback base partial IGC law. © 2016 Beijing Institute of Aerospace Information.

Saturation attack based route planning and threat avoidance algorithm for cruise missiles

According to the characteristic of cruise missiles,navigation point setting is simplified,and the principle of route planning for saturation attack and a concept of reference route are put forward.With the help of the shortest-tangent idea in route-planning and the algorithm of back reasoning from targets,a reference route algorithm is built on the shortest range and threat avoidance.Then a route-flight-time algorithm is built on navigation points.Based on the conditions of multi-direction saturation attack,a route planning algorithm of multi-direction saturation attack is built on reference route,route-flight-time,and impact azimuth.Simulation results show that the algorithm can realize missiles fired in a salvo launch reaching the target simultaneously from different directions while avoiding threat.

Study on Anti-ship Missile Saturation Attack Model

Based on the analysis for the interception process of ship-to-air missile system to the anti-ship missile stream, the antagonism of ship-to-air missile and anti-ship missile stream was modeled by Monte Carlo method. This model containing the probability of acquiring anti-ship missile, threat estimation, firepower distribution, interception, effectiveness evaluation and firepower turning, can dynamically simulate the antagonism process of anti-ship missile attack stream and anti-air missile weapon system. The anti-ship missile's saturation attack stream for different ship-to-air missile systems can be calculated quantitatively. The simulated results reveal the relations among the anti-ship missile saturation attack and the attack intensity of anti-ship missile, interception mode and the main parameters of anti-air missile weapon system. It provides a theoretical basis for the effective operation of anti-ship missile.

Functionality evaluation of system of systems architecture based on extended influence diagrams

System of systems architecture（SoSA） has received increasing emphasis by scholars since Zachman ignited its flame in 1987. Given its complexity and abstractness, it is critical to validate and evaluate SoSA to ensure requirements have been met.Multiple qualities are discussed in the literature of SoSA evaluation, while research on functionality is scarce. In order to assess SoSA functionality, an extended influence diagram（EID） is developed in this paper. Meanwhile, a simulation method is proposed to elicit the conditional probabilities in EID through designing and executing SoSA. An illustrative anti-missile architecture case is introduced for EID development, architecture design, and simulation.

Air and Missile Defense Under Spatial Grasp Technology

A novel control ideology and technology for solving tasks in large distributed networked systems will be briefed. Based on active scenarios self-navigating and self-matching distributed spaces in a highly organized super-virus mode, it can effectively establish global control over large systems of any natures. The technology can use numerous scattered and dissimilar facilities in an integral and holistic way, allowing them to work together in goal-driven supercomputer mode. The approach can be useful for advanced air and missile defense in a variety of ways which is described and explained in this paper.

Three-Dimensional Discrete Observability Analysis for Air-to-Air Missile Target Tracking

The interception information of infrared（ IR）-guided air-to-air missiles（ AAM） is mainly estimated only using the basic bearing measurements. In order to intercept highly maneuverable targets,it is essential to study the system observability to improve the target tracking system performance.The uniqueness of this paper is that the observability analysis is derived based on a discrete three-dimensional （3D） system model. During the maneuvering scenario,the system is approximated by a segment-by-segment system. The relationship between missile-target motion and observability is given by direct and dual approaches. Meanwhile sufficient observability conditions are derived. Moreover,a numerical simulation is conducted and an alternate method is provided to reinforce the proposed observability analysis results.

Penetration Capability Comparison of the Same Anti-ship Missiles Between Millimeter and Centimeter Wave Seekers

This paper compares the penetration capabilities of the same type anti-ship missiles with millimeter wave(MMW)seeker and centimeter wave seeker,and constructs mathematical models of penetration probability and saturation attack number for all anti-ship missiles used in the countermeasure system,according to the rule which makes the ship-borne air defence system oppase as far as possible and equally,and combining the actual combat situation.It can be seen,from analysis of the countermeasure process between anti-ship missile and surface naval ship,that for the same type of anti-ship missile with different seekers,the main influence on the penetration capability is from electronic jamming system.Based on the built model,the penetration capabilities of the same type anti-ship missiles with MMW and centimeter wave seekers are simulated.The simulated results show that the penetration capability of MMW seeker is slightly better than that of the centimeter wave seeker and its saturation attack number is also influenced by the discovering probability greatly.Finally,some suggestions to get superior penetration effect are given for a commander to choose seeker type suitably.

Research on Optimization Strategy of Missile Preliminary Design

Two system optimization architectures are proposed for missile system preliminary design, taking into account aerodynamics, weights and sizing, propulsion and trajectory. Approximation methods are investigated in order to reduce problem dimensionality and to improve the efficiency of optimization process.