Missile Simulation Research Articles

상태변수 오차기반 스무더를 이용한 자율이동체 자세오차 보상

In this study, the navigation information of a guided missile was calculated using a smoothing algorithm and used for improving the attitude estimation accuracy of the guided missile. The state variables of the backward filter, designed in the fixed interval smoother, were set to attitude errors in the same way as the forward filter of the fixed interval smoother, which was implemented as a linearized Kalman filter algorithm. To verify the performance of the proposed algorithm, simple guided missile simulations were performed, which confirmed that the attitude error of the guided missile was reduced when the fixed interval smoother was applied.

Research on simulation model validation based on probability relational analysis

The most basic and direct method for simulation model validation is to compare the consistency of missile flight data and simulation data under the same input conditions. However, the existing dynamic data consistency analysis methods are mainly suitable for the case between 1-D missile flight data and 1-D simulation data, and do not conform to the consistency test of single sample flight data and multi-sample simulation data in equipment qualification/finalization test. To solve this problem, a simulation model validation method based on probabilistic relational analysis is proposed. The consistency of output data is measured from the two scales of probability relational coefficient and probability relational degree. The probability relational coefficient is determined by calculating the cumulative distribution probability value of real missile flight samples in the distribution function constructed by simulation data. The probability correlation degree is calculated by judging whether the probability relational coefficient satisfies the uniform distribution of[0 1]. The consistency analysis problem of a kind of dynamic data association is solved accordingly. The correlation theorem that the probability relational degree must satisfy and its property are proved. Meanwhile the operation steps of simulation model verification based on probability correlation analysis are given. This method can process all multi-dimensional simulation data at the same time, and integrate the random factors in the test process, so it can make full use of the test information under the condition of small sample flight test, and improve precision and the reliability of simulation model verification. The rationality and validity of this method are further verified by numerical tests and application examples.

Development of Infrared-Guided Missile Precision Detection Simulator

In order to carry out various detections of system indicators during the research and development phase of infrared guided missiles, the article first analyzes several main design schemes of the infrared guided missile detection simulator and finds that it has the disadvantages of difficult processing technology and low detection accuracy. The overall structure of the detection device was designed, including the design of the rotation and swing mechanism, lens mechanism, optical system and control system. The optical system error analysis is performed on the infrared guided missile detection simulator. The position of the receiving light source is obtained by analyzing the mechanism characteristics of the detection simulator and the kinematics model of the device. The phase difference analysis of the eccentricity and tilt system is obtained. The image quality was evaluated by the optical transfer function (MTF), and the system error was found to meet the requirements of imaging quality. The experiments show that the simulation of 1.7~4.9 um medium wave infrared dynamic target signals provides an accurate and reasonable experimental environment for the missile and the verification of the light source target and meets the experimental requirements.

A Comparison of Guided Missile Simulations Between EADSIM and SADM in Composite Combat Mission Planning Simulation Environments

A Comparison of Guided Missile Simulations Between EADSIM and SADM in Composite Combat Mission Planning Simulation Environments

SIMULATION OF MISSILE LAUNCH USING SUKHOI SU-35 AND VYMPEL R-73 3D MODELLING

The simulation is the operations imitating technique or processes that occur in the system and media, which can speed up the understanding of many things including missile launches. Missile launch simulation process on combat aircraft can be operated using computer simulation and application. The simulation is created using unity program and its buttons tested work fine. The results were tested with 10 questions to 10 flight department respondents. The data which is got showed 70.6% approached the process and missile launch function.

Research on Ammunition Simulation Method

This paper introduces a kind of ammunition simulation method. Based on this method, the ammunition simulation software is implemented. The software includes air to ground missile simulation model, bomb simulation model and rocket simulation model. The simulation model of air-to-ground missile simulates the ballistic model of air-to-ground missile and the process of flying, searching and finding targets, hitting targets, damaging equipment and personnel, etc. The bomb simulation model simulates the ballistic model of the bomb and the process of flying, hitting and damaging the target. The rocket simulation model simulates the rocket trajectory model and the process of flying, hitting and damaging the target. In this paper, the motion equation, coordinate transformation formula, data interface and hit damage algorithm of ammunition are introduced in detail. The method of ammunition simulation not only considers the relevant elements of the whole process of ammunition simulation, but also is convenient for software realization and rapid simulation.

Temperature Field Simulation of Launcher and Missile under Fire Condition

In order to figure out the temperature field distribution of the launcher and the missile under fire conditions, the geometric model of the launcher and the missile was established. The temperature field of a typical pool fire flame was simulated, and the temperature field distribution of the launcher and internal missile under the typical pool fire flame was calculated. The results show that the maximum temperature of the outer surface of the launcher after firing 3600s is 1238K, the highest temperature of the missile surface can reach 690K, the maximum temperature of the missile center is 333K. The heat transfer by radiation plays a major role in the whole heat transfer process, which accounts for 88.35%.

Design and Implementation of Simulation Training System Based on MVC Architecture

With the development of technology of computer, the missile force has been developing towards informatization. A new training method based on simulation training is launched. This article mainly introduced missile simulation training system and the MVC architecture, and proposed the structure of MVC architecture design simulation training system, in the last, implementing the simulation training system for a missile weapon. The usage of MVC frame design achieved a good structure, loosely coupled and high cohesive simulation training system, which effectively improves the development and late maintenance cost of the simulation training system, and realizes that one system can meet the requirements of multiple batches of missile weapons.

Research and Implementation of Key Technology for Calculation of Acquiring Simulation Training System

For a missile acquiring system, there are problems such as high system failure rate, poor acquiring computer maintainability and loopholes in the calculation program during the training process of the troops. For this purpose, the acquiring professional training can get rid of the dependence on the actual equipment, and provide good hardware conditions for the training of the troops and the teaching of the college, a missile acquiring simulation training system is designed and constructed. The key to acquiring simulation training system software design is acquiring calculation, and the two technical difficulties in acquiring calculation are data format conversion and data output precision control. This paper focuses on the basic algorithms and implementation methods of self-test calculation, data format conversion and data output precision control, and solves the key technical problems of acquiring calculation in the acquiring training software.

Systems Theoretic Accident Model and Process (STAMP) applied to a Royal Navy Hawk jet missile simulation exercise

The Royal Navy uses Hawk jets to simulate sea-skimming missile attacks against vessels as part of their training regulations. To best achieve these goals, pilots of the Hawk are required to fly at approximately 50 feet above sea level to accurately mimic the flight path of a missile. Despite this need the Hawk is not equipped with a radar altimeter and instead relies upon pilot skill to ensure the safe completion of the operation. Incidents whereby the Hawk jets have struck the water are however recorded, risking pilot safety. This paper explores the Hawk missile simulation task using a Systems Theoretic Accident Model and Process (STAMP) and its corresponding hazard analysis Systems-Theoretic Process Analysis (STPA) methodology to map the key stakeholders within this operation. In doing so, the method explores areas of potential risk in the system and recommends how overall systemic safety of the operation can be improved.

Real Time Control of Hardware In-the-Loop Simulation Based on CAN Bus and RTX

In Hardware In-the-Loop Simulation(HILS) of missile, real time is the main consideration. Due to the poor real time performance of the Windows system, a real time solution scheme for HILS of missile based on the RTX system is proposed, and the design of the RTX hardware driver and the reflective memory technology are introduced. Aiming at the problem of precise timing and data synchronization in real time system, the timer of RTX is studied and a hardware solution for data synchronization is proposed. For the CAN bus to long distance transmission in high baud rate conditions, the CAN relay station is designed. The HILS platform has been built, and the result of simulation is correct without missing frames and wrong frames, meeting the requirements of stability and reliability.

Analyzing and Designing Control System for an Inverted Pendulum on a Cart

It is a collection of MATLAB functions and scripts, and SIMULINK models, useful for analyzing Inverted Pendulum System and designing Control System for it. Automatic control is a growing field of study in the field of Mechanical Engineering. This covers the proportional, integral and derivative (PID). The principal reason for its popularity is its nonlinear and unstable control. The reports begin with an outline of research into inverted pendulum design system and along with mathematical model formation. This will present introduction and review of the system. Here one dimensional inverted pendulum is analyzed for simulating in MATLAB environment. Control of Inverted Pendulum is a Control Engineering project based on the flight simulation of rocket or missile during the initial stages of flight. The aim of this study is to stabilize the Inverted Pendulum such that the position of the carriage on the track is controlled quickly and accurately so that the pendulum is always erected in its inverted position during such movements.

Study on Simulation Model of Fire Strike

In this paper, a simulation model of firepower strike is proposed based on some assumptions, including firepower strike equipment simulation component, reconnaissance radar simulation module, gun simulation model and tactical missile simulation model. The model is simple and feasible.

Design of Real-Time Hardware-in-the-Loop TV Guidance System Simulation Platform

This paper presents a novel design of a real-time hardware-in-the-loop (HIL) missile TV guidance system simulation platform, which consists of a development computer, a target computer, a turntable, a control cabin, and a joystick. The guidance system simulation model is created on the development computer by Simulink® and then downloaded to the target computer. Afterwards, Simulink Real-Time™ runs the model in real-time. Meanwhile, the target computer uploads the real-time simulation data back to the development computer. The hardware in the simulation loop is TV camera, encoders, control cabin, servomotors, and target simulator. In terms of hardware and software, the system has been simplified compared with the existing works. The volume of the turntable integrating the target simulator and the seeker simulator is about 0.036 cubic meters compared to the original 8 cubic meters, so it has a compact structure. The platform can perform the closed-loop control, so the simulation has high precision. Taking the TV guidance simulation as an example, in the case of target maneuvering, the final miss distance of the TV guidance missile is 0.11812 m, while the miss distance of the original system is 13 m. The trajectories obtained from the HIL and mathematical simulations substantially coincide. So the simulation results show that the proposed HIL simulation platform is effective.

BOM-based design knowledge representation and reasoning for collaborative product development

Modern product development becomes increasingly collaborative and integrated, which raises the need for effectively and efficiently sharing and re-using design knowledge in a distributed and collaborative environment. To address this need, a framework is developed in this research to support design knowledge representation, retrieval, reasoning and fusion, which takes account of structural, functional and behavioral data, various design attributes and knowledge reasoning cases. Specifically, a multi-level knowledge representation based on the Base Object Model (BOM) is proposed to enable knowledge sharing using Web services technologies. On this basis, a multi-level knowledge reuse method is developed to support the retrieval, matching and assembly of knowledge records. Due to the tree structure of BOM, both depth-first and breadth-first searching strategies are employed in the retrieval algorithm while a novel measure is proposed to evaluate similarity. Moreover, a method based on the D-S evidence theory is developed to enable knowledge fusion and thus support effective decision-making. The framework has been implemented and integrated into an HLA-based simulation platform on which the development of a missile simulation example is conducted. It is demonstrated in the case study that the proposed framework and methods are useful and effective for design knowledge representation and reuse.

Guidance Law and Neural Control for Hypersonic Missile to Track Targets

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

Application of an Improved Colored Petri Net Modeling Method in Certain Missile Training System

In allusion to the need of analyzing complex system, we have proposed a method named multi-grade color Petri net. We for the first time use this new method to analyze a missile training simulator system. This model can accurately reflect the complex environments of the system and avoid the difficulty occurring often in developing accurate mathematics model by using classical research approach.

Review of the Spalart-Allmaras turbulence model and its modifications to three-dimensional supersonic configurations

The Spalart-Allmaras (SA) model is a turbulence model for modeling different types of turbulent flows, especially in aerodynamics. Until 1992, when it was published by Spalart and Allmaras, there had been modified different terms of the governing equation of this model (prediction, diffusion and destruction). In this literature review, one can go through the details of the governing equation of this model and the role of each term and reasoning behind it. The model is implemented in three-dimensional compressible supersonic flows, and validated for two different configurations: a ballistic missile and a cruciform missile simulations show the ability of the method to snap the interaction between the fuselage vortices and the winglets.

Anti-Ship Missile Capture Capability Modeling and Simulation Evaluation

On the basis of analyzing anti-ship missile operational process, this paper expounds the factors set affecting the capture capability of anti-ship missile, systematically set up anti-ship missile capture capability evaluation model; By means of large-sample simulation experiment, this paper analyzes the effects of target designation accuracy on target speed capture probability. Simulation practice shows that the detailed simulation model establishment, large sample space design, and many times simulation experiments can realize missile searching probability simulation analysis under the condition of many factors interwoven impact, and can effectively support capture capability assessment under given conditions.

Anti-Ship Missile Attack-Defense Confrontation Ability Verification Technology Based on Simulation

A detailed study on modeling and simulation of anti-ship missile terminal guidance radar whole work process, such as target echo, environmental clutter, electronic jamming ,signal processing and data processing etc, is made in this paper.On this basis, an anti-ship missile attack-defense confrontation simulation system is developed to realize the verification of anti-ship missile attack-defense confrontation ability. The application of this simulation system proves that the efficiency of the military training is improved and the cost of training is cut down.