Missile Control System Research Articles

System Software Abstraction Layer - much more than Operating System Abstraction Layer

Current and future aircraft systems require real-time embedded software with greater flexibility compared to what was previously available due to the continuous advancements in the technology leading to large and complex systems. Portability of software as one of the aspects of this flexibility is a major concern in application development for avionics domain for fast development and integration of systems. Abstractions of the hardware platform which have been already introduced by the operating system community allow the software modules to be reused on different hardware and with different physical resources. Now operating system community has come up with an abstraction layer called operating system abstraction layer (OSAL) which along with the hardware abstraction unifies the OS architecture too. It provides a common set of primitives independent of the underlying operating system and its particular architecture. Factors such as reliability, scalability and determinism of any application largely depend on the design and architecture of the application. This is the most important and critical factor of real time systems such as mission computers of avionics systems, missile control system or control computers of space shuttle. It demands developer to perform feasibility of different software architecture to select the best alternative. Authors’ analysis shows that to make any real time application more secure, scalable, deterministic, and highly portable, OSAL has to be extended to more than just operating system abstraction. This new view of OSAL will be called as system software abstraction layer (SSAL). In this paper, authors attempt to highlight the efficiency of SSAL as well as detailed description of its main features and design considerations. Authors have implemented the SSAL on top of two well known OS (WinCE and Vxworks) and performed extensive evaluations, which shows that it effectively reduces portability efforts while achieving simplicity, predictability, security and determinism. This paper presents in brief, the API functionalities, its components, implementation, interfaces, advantages and overheads along with a case study. Defence Science Journal, 2013, 63(2), pp.214 -222 , DOI:http://dx.doi.org/10.14429/dsj. 63.4267

The Design of Rolling Bearing Testing for some Missile Control System Based on C8051F021

C8051F021 is a fully integrated mixed-signal System-on-a-Chip MCU. It is applied to rolling bearing testing, and portable rolling bearing testing machine is realized. Performance and integrated level of the system are improved greatly for C8051F021 application. The hardware structure of the system is discussed in this paper, and the key codes of information acquire is also given.

Application of a Complex Lead Compensator for a Laser Guided Missile

This paper discusses the application of a lead compensator with complex pole and complex zero for a missile. It is compared with a lead compensator with real pole and real zero. A typical laser guided missile control system is considered for the performance comparison of both the compensators. Simulation studies carried out with MATLAB brings out the scope of using complex compensator in missile guided systems.

Hardware-in-the-Loop Simulation of Missile Control System Based on Windows Operation System

A hardware-in-the-loop (HIL) simulation platform in use of windows operation system was successfully established based on general industrial PC combined with an external timer. The following HIL simulation process of missile control system indicated that the novel platform could not only satisfied the real-time requirement of HIL simulation, but also is low-cost and universal, which could provide a convenient new choice in the similar applications.

Dynamic Anti-Windup Design for Missile Overload Control System

The former research on the overload control system of a supersonic missile didn’t consider actuator saturation. In order to reduce the windup effect caused by actuator saturation, we developed a dynamic anti-windup compensator. The overload control system design adopted a two-step approach. Firstly a sliding mode controller was designed ignoring the saturation. Secondly a dynamic anti-windup compensator was designed. It added to the control system to reduce the windup effect. It disengaged the actuator fast from saturation phase after the actuator entered saturation. Simulation results showed that the dynamic anti-windup compensator reduced 52% of saturation time of the control system. Hence the performance of the overload control system is improved effectively.

The effective evaluation of the guidance method which has the changed interception quantity that adaps to movement of target.

In this paper, the author assessed the effect of guidance law with minimum normal accelerator trajectory in the whole of guidance process and at the impact point by destructive range parameters. Base on real parameters of intermediate-range missile ammunition and typical properties of x93+x94 scan missile control system control observatory combining Matlab simulation of authors proved the effect of the new law.

The Design of High Attack-angle Flying Missile Control System Based on Feedback Linearization

The Design of High Attack-angle Flying Missile Control System Based on Feedback Linearization

PID Control Based Missile Sub-Channel Simulation

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

Intelligent Control Method of Ground to Air Missile Based on FCMAC

Intelligent control methods of missile guidance and control system (GACS) are studied in this paper. Secondly, the component and principle of GACS is introduced. Based on the fuzzy neural network, this paper constructs a basic structure of the intelligent control method of missile. Meanwhile, a new intelligent control method of rolling channel of missile based on Fuzzy Cerebella Model Articulation Controller (FCMAC) is designed. Under complicated environmental conditions, the missile can be accurately controlled with this method. Finally, the application value is illustrated. It’s very meaningful to improve the combat capability.

Research on the Relationship between Stabilization Problem and Tracking Problem of Missile Control System

The stabilization problem of a system without parameter uncertainties can always be transferred to a tracking problem if it is no need to consider the robustness requirement of a system. But those two questions are not the same for a missile control systems. In this paper, the uncertainties of parameters are considered, and we found that the stabilization problem can not be transferred to a tracking problem.

A Simple Differential Sliding Mode Design for the Overload Control of Missile System

A simple differential sliding mode control law was designed for the missile overload control system without considering the uncertainties of air-dynamic coefficients. The sliding mode was composed of overload error and the differential error of overload. Finally, a numerical simulation was down and it testified that it is unable to make the system stable with only pure overload control strategy. Although the sliding mode was arrived , Oscillation phenomenon was caused by the poles in imaginary axis.

Circuit Fault Diagnosis Interface Software Design

On the basis of research on digital circuit fault diagnosis system for missile launch and control system – one research project recently completed by the author ,and through analysis for the first and foremost problem of interface circuit, this paper makes a detailed description of digital circuit fault diagnosis interface circuit software design based on LabWindows/CVI, and gives major steps of the development for interface circuit software.

Research on Accessibility of Integral Sliding Mode Contorl of Missile System

Considering the no uncertain air-dynamic coefficients situation, a kind of sliding mode control law, which was composed of the angle velocity and overload error, was designed for the overload control system of missile. And the accessibility of sliding mode was analyzed. What worthy pointing out is that a transfer- function-type backstepping algorithm was adopted to solve the derivative item of actuator and a novel type of control was proposed.

Modeling of dynamics, guidance, and control systems of air-to-surface missiles

In this study, the generic dynamic models of air-to-surface missiles are given in addition to the related guidance and control schemes. In this extent, two-part missile configurations are considered as well as the traditional single-part missile geometries. The dynamic modelling part consists of the general equations of motion for both of the mentioned types of missile configurations, aerodynamic modelling and corresponding transfer functions, which are used in the design of missile autopilots. Further, the notable guidance laws applicable to such missiles are given along with the relevant autopilot, or missile control system, models. Regarding the mission profile of these munitions, the target is modelled as a surface vehicle moving on the ground. After conducting some computer simulations based on the proposed models, the study is concluded by a general evaluation section.

Proportional Guidance and CDM Control Synthesis for a Short-Range Homing Surface-to-Air Missile

This paper presents a high-performance and simple guidance method for a short-range missile. Missile control systems are designed along the estimated flight envelope of the missile based on coefficient diagram method. The linear time invariant (LTI) models are obtained by linearizing missile nonlinear model at specific operating points. The governing equations of motion are accurately modeled by taking into account the effect of the mass rate and the center of gravity shift. A novel algebraic approach called coefficient diagram method (CDM) is used to design normal acceleration and roll angle control systems. The proportional navigation law is considered as the guidance law. One case of engagement scenarios is studied and the missile performance is evaluated. The robustness of the proposed controller is tested against parameter uncertainties and wind disturbance.

Hierarchical anti-disturbance adaptive control for non-linear systems with composite disturbances and applications to missile systems

In this paper, a new anti-disturbance controller is presented for a class of non-linear systems with multiple disturbances. The first part of the disturbance is described by an exogenous model and the second part represents an uncertain variable bounded by a given function. A new non-linear disturbance observer is designed to estimate the composite disturbances. Then, a hierarchical control strategy consisting of disturbance-observer-based control and a robust adaptive controller is presented to achieve the anti-disturbance performance. A stability analysis for both the error estimation systems and the composite closed-loop system is provided. Finally, the approach is applied to a missile control system to show the efficiency of the approach.

Demonstration of a Wire Suspension for Wind-Tunnel Virtual Flight Testing

This paper describes the development of a wire suspension system for dynamic testing of missiles in a wind tunnel. The system restrains the missile, permits motion in 3 rotational degrees of freedom, and measures forces on the model. The apparatus allows testing of missile control systems in the wind tunnel, reducing the cost and risk of a flight-test program. Hydraulic actuators control cable tension and model position. Bearings provide free roll and pitch, whereas yaw motion is created by the cable actuation system and a repetitive-learning controller. The paper describes the cable arrangement, force balance, bearings, closed-loop hydraulic control, and the repetitive-learning controller. Two sets of tests were conducted with the broad ocean area missile (a sidewinder variant) in the HighVelocity Air Stream facility at the China Lake Naval Weapons Center. The tests, conducted at M 0:4–0:6, demonstrate functionality of the system in a series of missile pitch and yaw maneuvers. The learning controller is shown to learn an s maneuver in the yaw plane.

RBF neural network-based sliding mode control for a ballistic missile

In this paper, the non-linear models for the three channels of a ballistic missile are analysed. The coupled terms are taken as additional disturbances for every single channel, in order to realise the independent design for every channel and to simplify the structure of the control system. An RBF neural network-based sliding mode controller is designed for every channel's thrust vector control system of the ballistic missile. For the controller, the RBF neural network modifies the parameter of the sliding mode controller to approximate the lumped uncertainty. The performance of the designed RBF neural network-based sliding mode controller is compared with that of the conventional PID controller in the numerical simulation, and its effectiveness is demonstrated by the simulation results.

백스텝핑 방법과 외란관측기법에 의한 미사일 제어시스템의 동역학을 고려한 미사일 유도법칙의 설계

In this paper, a design method of a missile guidance command is presented considering the dynamics of missile control systems. The design of a new guidance command is based on the well-known PNG(propotional navigation guidance) laws. The missile control system dynamics cause the time-delays of the PN guidance command and degrade the performance of original guidance laws which are designed under the assumption of the ideal missile control systems. Using a backstepping method, these time-delay effects can be compensated. In order to implement the guidance command developed by the backstepping procedure, it is required to measure or calculate the successive time-derivatives of the original guidance command, PNG and other kinematic variables such as the relative distance. Instead of directly using the measurements of these variables and their successive derivatives, a simple disturbance observer technique is employed to estimate a guidance command described by them. Using Lyapunov method, the performance of a newly developed guidance command is analyzed against a target maneuvering with a bounded and time-varying acceleration.

Automatic Control System of Homing Missile with Scanning On-Board Device

Automatic Control System of Homing Missile with Scanning On-Board Device