Missile System Design Research Articles

Anti-Tank Guided Missile System Design Based on an Object Detection Model and a Camera

First-generation anti-tank guided missiles (ATGMs) mainly rely on the skills of operators to guide them in hitting targets, thus making them inaccurate. However, third-generation ATGMs are affected by electronic disruption and are extremely expensive. For example, the accurate range for anti-tank RPGs is 100 m, while the range of the ATGM Javelin is just 4 km (Lightweight CLU) and the cost is US$249,700 (Lightweight CLU only). However, the range of our system depends on the camera range used, which can exceed 50 km on flat ground, and the cost is a few thousand dollars. In this paper, an object detection model was used to recognize a targeted tank, and the fundamental matrix and triangulation approaches were utilized to determine the location of the target tank. Thus, the produced control circuit is smart, autonomous, accurate, with a wide range, and quite inexpensive. The system was installed on an anti-tank missile, tested indoors, and worked correctly. Using object detection models and computer vision technologies in the weapon industry led to the production of an intelligent weapon that is smart, has more range, and is autonomous.

Research on the Integrated Design of Missile Guidance Control Considering the Angle of Attack Constraint

The integrated guidance and control design of missile considering the attack angle constraint can effectively improve the guidance accuracy and damage effect of the missile, which has become one of the hot spots in current research. In this paper, we review the problem of integrated guidance and control design of missile considering attack angle constraint. First, the steps to construct the ensemble model are described. Second, combining with the fact that modern control theory has been successfully applied to the design of missile weapon systems, the integrated design approach for missile guidance and control in recent years is summarized and summarized in this paper. Finally, the analysis and discussion of the problems and trends that need to be addressed in the integrated design of missile guidance and control can break through the constraints of traditional missile design concepts and methods and serve as a reference for the development of a new generation of missiles.

The simulation study of damage assessment of a surface-to-air missile system attacked by an anti-radiation missile and the optimization of fuze-warhead coordination

The final damage effectiveness of warhead is the most important objective in missile system design. To obtain the damage probability of a certain anti-radiation missile warhead against a typical field surface-to-air missile system and find the optimal fuze-warhead coordination strategy, the studies of modelling, simulation and optimization are carried out. First, the vulnerability of the target is analysed and the target vulnerability model is established. Secondly, the calculation models of fragments field and over-pressure field are established to realize the calculation of encounter between warhead and target. Finally, the damage assessment model is established to calculate the damage probability of the parts and the whole system. Through Monte Carlo simulation, the single-shot damage probability of the missile is obtained when the parameters of the encounter between warhead and target are randomly selected according to a certain probability distribution. And the optimal fuze control strategies of the missile at different entrance angles are obtained through optimization calculation. If the entrance angle of the missile cannot be identified, the optimal fuze initiation strategy of the anti-radiation missile in this paper is a delay of 13ms. The results show that the research method of this paper can be applied to the missile weapon system with the function of entrance angle identification to maximize the damage efficiency.

Missile Mathematical Model and System Design

Recently, aerospace (flight) engineers, having more solid mathematical backgrounds, have become familiar with the newest results in control theory and are able not only to formulate control problems but also solve them without attracting the attention of control experts. Moreover, they try to apply new results in control theory to specific aerospace and missile guidance problems. As a result, control theory is losing its biggest supplier and, to a certain degree, this slows down its progress.

Adaptive Neural Network Control for Missile Systems With Unknown Hysteresis Input

Most existing results do not take the effects of backlash hysteresis of actuators into account in a controller design of missile systems, but such hysteresis seems inevitable in practice. In this paper, a robust adaptive neural network (NN) control law for a missile system with unknown parameters and hysteresis input is proposed based on a backstepping technique. The controller is designed by introducing NN approximation, which can be adjusted by an adaptive law based on the backstepping approach. The developed NN controller does not require a priori knowledge of the unknown backlash hysteresis. In particular, unlike existing results on adaptive compensation for unknown backlash hysteresis, the sign of b is no longer needed. It is shown that the designed controller can ensure the stability and tracking performance of the closed-loop system.

Predictor Observers for Proportional Navigation Systems Subjected to Seeker Delay

We propose predictor observers as viable tools to compensate for pure time delays in the seeker subsystem of missile guidance systems employing proportional navigation guidance (PNG). With the intention of use in terminal guidance in which the missile is already on a near-collision course with a target, we demonstrate that a classical predictor observer for linear time-delay systems is input-to-state stable (ISS) with respect to bounded target maneuver and measurement disturbances. We then show how the classical predictor observer can be implemented as a Kalman filter for the delayed state augmented with a predictor. Finally, we illustrate the practicality of the approach in missile guidance system design through two examples that exhibit seeker delay and random target maneuvers. For both examples, numerical simulations show that predictor observer guidance laws are able to substantially reduce miss distance versus baseline PNG laws that have no delay compensation, inviting further studies of the approach for designing real missile guidance systems in practice.

The Application of Parameter Dependency Diagrams in System Design. A missile system design example

AbstractThe traditional approach to the design of systems with interrelated elements is an iterative approach. In this paper the author explores the parameter dependence diagram as developed by Eisner to reduce the number of iterations. PDDs are also used to define the functional areas and physical elements in the system. Finally, the approach is demonstrated with a missile system design example. It is recommended that parameter dependency diagrams be used more frequently in the design of highly interrelated systems.

Two-channel pitch/yaw missile autopilot design using arbitrary order sliding modes based pole placement

AbstractThe paper presents a new missile autopilot system design. The design is achieved through the pole-placement in quasi-continuous high-order sliding mode gains adjustment. Enhanced performance, strong robustness and smooth control are obtained through arbitrary increase of the number of non-oscillatory stable poles. The target application of this technique the two-channel pitch/yaw missile autopilot system is considered. Numerical simulations indicate that the arbitrary-order sliding modes based pole placement’s performance compares favourably against recently proposed high-order pole placement schemes.The proposed arbitrary-order pole placement scheme presents a promising design tool for finite-time stabilisation and control of uncertain multivariable systems.

레이돔 굴절 오차 보상을 위한 적응 파티클 필터 설계

Radome aberration error causes degradation of miss distance as well as stability of high maneuver missile system with RF seeker. A study about radome compensation method is important in this kind of missile system design. Several kinds of methods showed good compensation performance in their paper. Proposed adaptive Particle filter estimates line of sight rate excluding the radome induced error. This paper shows effectiveness of adaptive Particle filter as compensation method of radome aberration error. Robust performance of this filter depends on external aiding measurement, target acceleration. Tuning of system error covariance can make this filter unsensitive against the error of target acceleration information. This paper demonstrates practical usage of adaptive Particle filter for reducing miss distance and increasing stability against disturbance of radome aberration error through performance analysis.

A Fast Algorithm for the Inverse of a Tridiagonal Period Matrices in Signal Processing

The theory and method of matrix computation, as an important tool, have much important applications such as in computational mathematics, physics, image processing and recognition, missile system design, rotor bearing system, nonlinear kinetics, economics and biology etc. In this paper, Motivated by the references, especially [2], we give the estimates for the lower bounds on the inverse elements of strictly diagonally dominant tridiagonal period matrices.

Estimates for the Lower Bounds on the Inverse Elements of Strictly Diagonally Dominant Tridiagonal Period Matrices in Signal Processing

The theory and method of matrix computation, as an important tool, have much important applications such as in computational mathematics, physics, image processing and recognition, missile system design, rotor bearing system, nonlinear kinetics, economics and biology etc. In this paper, Motivated by the references, especially [2], we give the estimates for the lower bounds on the inverse elements of strictly diagonally dominant tridiagonal period matrices.

A Fast Algorithm for the Inverse of a Class of Tridiagonal Period Matrices in Signal Processing

The Tridiagonal period Matrices, as an important tool, have much important applications ( such as in computational mathematics, physics, image processing and recognition, missile system design, nonlinear kinetics, economics and biology etc). In this paper, we give a fast algorithm for the inverse of the class of tridiagonal period matrices .

A new methodology for fuzzy multi-attribute group decision making with multi-granularity and non-homogeneous information

The aim of this paper is to develop a new methodology for solving fuzzy multi-attribute group decision making problems with non-homogeneous information, including multi-granular linguistic term sets, fuzzy numbers, interval values and real numbers. In this methodology, different distances are defined to measure differences between alternatives and the ideal solution as well as the negative ideal solution. A relative closeness method is developed by introducing the multi-attribute ranking index based on the particular measure of closeness to the IS. The proposed method determines a compromise solution for the group, providing a maximum "group utility" for the "majority" and a minimum of an individual regret for the "opponent". The implementation process, effectiveness and feasibility of the method proposed in this paper are illustrated with a real example of the missile weapon system design project selection.

Study of damping in layered and jointed welded structures

Vibration and noise reduction are crucial in maintaining high performance level and prolonging the useful life of machinery, automobiles, aerodynamic and spacecraft structures. It is observed that damping is caused by energy dissipation due to micro-slip along frictional interfaces. In this paper, a layered and jointed welded cantilever beam model has been considered for examining the vibration energy dissipation due to interfacial friction of jointed structures. Experiments are performed on mild steel specimens with a number of layers under different initial conditions of vibration to validate the theory developed. It is found that the interface pressure distribution characteristics, number of contacting layers, amplitude and frequency of vibration, length and thickness of specimen govern the damping capacity of jointed layered structures with welded joints. These results can be positively exploited in the design of machine tools, aircrafts, spacecrafts, satellites, automobiles and missile systems effectively to maximise their damping capacity.

GUIDANCE LAW EVALUATION FOR MISSILE GUIDANCE SYSTEMS

In missile guidance system, to reduce the interception “miss distance,” it is important to choose a suitable guidance law and navigation constant. This paper investigates and compares the system behavior of guidance laws under different navigation constants. Based on use of the adjoint technique, miss distance sensitivity analyses which consider the system noise, target step maneuver, initial heading error and system parameters for different guidance laws and navigation constants are presented. Based on these analyses, some suggestions for choosing a suitable guidance law and navigation constant are given for the design of missile guidance systems. Also, a suggestion for the optimal escape time for pilots of fighter planes is given.

Frequency domain approach to guidance system design

The frequency domain approach to guidance system design is presented. The model of the guidance control system reflects the most important characteristics of the flight control system that combines airframe and autopilot dynamics (damping, natural frequency, time constant, and airframe zero frequency). The analytical expressions for frequency response and related expressions for missile system performance are given. The analytical results obtained can be utilized for missile system design.

The Methods of Guided Missile Control System Design and Simulations

The Methods of Guided Missile Control System Design and Simulations

Engineering Applications of Jet Impingement Associated with Vertical Launching System Design

In the course of missile system design, jet plume impingement is encountered in designing airframe as well as launchers, requiring careful investigation of its effect on the system. In the present paper, recent works on such topic are presented to demonstrate usefulness of CFD results in helping design the hardware. The jet impinging flow structure exhibits such complex nature as shock shell, plate shock and Mach disk depending on the flow parameters. The main parameters are the ratio of the jet pressure to the ambient pressure and the distance between the nozzle and the wall. In the current application, the nozzle contour and the pressure ratio are held fixed, but the jet impinging distance is varied to illuminate the characteristics of the jet plume with the distance. The same methodology is then applied to a complex vertical launcher system (VLS), capturing its flow structure and major design parameter. These applications involving jets are thus hoped to demonstrate the usefulness and value of CFD in designing a complex structure in the real engineering environment.

3-루프 가속도 오토파일롯 구조를 갖는 유도탄의 공력특성 연구

We study how the missile autopilot with three loop acceleration structure is related to the aerodynamic characteristics. First, the relationships between the response characteristics of wingless-tail controlled missile and aerodynamics are derived. Next the maximum allowable performance limit of autopilot and the design direction for a missile shape are indicated using the property of zero. The method proposed in this paper may give a help to the missile autopilot system design and determination of the shape of aerodynamic. Also, the validity of proposed method is demonstrated via numerical example.

Missile Control Using Fuzzy Cerebellar Model Arithmetic Computer Neural Networks

Anovel fuzzyneuralnetworkcontrolsystem architecture,calledthefuzzycerebellarmodelarithmeticcomputer (fuzzy CMAC) neural network, is proposed. This fuzzy neural network architecture exploits a synergism between the original CMAC neural network and the theory of fuzzy logic controller. The fuzzy CMAC is able to perform arbitrary function approximation and can achieve a higher learning speed and greater accuracy than the original CMAC. It also has the capability of conveniently incorporating human knowledge into the system and processing information based on fuzzy inference rules. We evaluated the use of fuzzy CMAC in the design of advanced missile control systems. The method is demonstrated by missile interception simulations, and promising results are obtained.