It is difficult to display the diagnosis processes in a fault diagnosis software of the missile control systems because of its complicated structure and multifarious signal lines. A new method based on custom components is given for developing fault diagnosis softwares of the missile control systems.
Lastly,a fault diagnosis software of the missile control systems is deveoped with Borland C++ Builder 6.0 as development tools. The engneering practice show that the method is very efficient in fault diagnosis softwares developing of the missile control systems.
With the severe threat of electromagnetic pulse weapon to ballistic missile control systems,the primary ways how control system counteract HEMP are discussed.
Optical fiber technology is used in missile control system,which can resolve the electromagnetic interfere,the electric isolation,anti-jamming and so on in control system effectively. The capability and reliability of the missile control system can be improved greatly.
This paper first analyzed the ground test and control system architecture and its characteristics of the missile control system based on the bus. Then it made an explanation to the structure and BIT technique of a single component.
FUSE is not targeted at applications that require strong consistency on replicated data, such as stock exchanges and missile control systems.
In recent years Monte Carlo method has been more and more widely used in solving a variety of engineering problems which are difficult to solve with other mathematical methods. In Refs. [1] [2] the principles of Monte Carlo method generation of random variables, test of random variables, and applica- tion of the Monte Carlo method in some areas are discussed. In Ref. [3] Monte Carlo method is used to study system reliability in frequency domain, but not all nonlinear effects were considered; as a result this...
In recent years Monte Carlo method has been more and more widely used in solving a variety of engineering problems which are difficult to solve with other mathematical methods. In Refs. [1] [2] the principles of Monte Carlo method generation of random variables, test of random variables, and applica- tion of the Monte Carlo method in some areas are discussed. In Ref. [3] Monte Carlo method is used to study system reliability in frequency domain, but not all nonlinear effects were considered; as a result this approximate method would very likely introduce big errors. When we consider the nonlinear effects in a nonlinear system, how to analyse system reliability in frequency domain is a problem. The classical method which is used to study the nonlinear system is the describing-function method. This method is a graphical method which fails to analyse systems in which there are several nonlinear elements. In order to analyse the stability of tactical missile control system, in this paper we use a new method which combines Monte Carlo method with functions describing the characteristics of nonlinear elements. In the method the amplitude, X, of the input signal, Χsinωt, in the describing function is simulated by uniformly distributed random variables in the interal (a,b) which is so chosen that the value of amplitude may occur in both the linear range and the nonlinear range. In the course of missile flight, the control system is influenced by a variety of random disturbances. The disturbances often cause random variations of system parameters. Real values always deviate from normal values either computed or obtained from tests. Therefore, we use random variables for simulating these parameters. When there are not enough data for determining the statiscal characteristics of the random deviations, we can in most cases consider that these deviations belong to the standard normal distribution, N(0,σ). In this paper, we take an early tactical missile guidance system as an example. The calculated results show that Monte Carlo method combined with the describing functions of nonlinear element is a very powerful method in the stability analysis of missile control systems with significant nonlinearties. Because in the method not only nonlinearities of control system but also random variations of system parameters are considered, results obtained are more reliable than those obtained by using traditional methods.
This paper presents an identification algorithm with auto-regulation forgetting factor for fast time-varying systems. This algorithm is based on Ref[l,2] and perfectly improves the method for choosing forgetting factor, and in the algorithm the auto-regulation factor is introduced so as to cope with parameter estimation of fast time varying systems such as missile control system, etc., Digital simulation results show that this algorithm is satisfactory for identifying the parameters which change in the form...
This paper presents an identification algorithm with auto-regulation forgetting factor for fast time-varying systems. This algorithm is based on Ref[l,2] and perfectly improves the method for choosing forgetting factor, and in the algorithm the auto-regulation factor is introduced so as to cope with parameter estimation of fast time varying systems such as missile control system, etc., Digital simulation results show that this algorithm is satisfactory for identifying the parameters which change in the form of some typical functions (e.g., exponential, slide, step, sine, square or their combination).
The generalized predictive contrller ( GPC) appears to be more robust than conventional adaptive controller in dealing with systems having varying and / or mismodelled dynamics. In this paper, a robust GPC law is combined with a robust parameter estimator to provide a practical adaptive control algorithm, which is applied to a ground air missile autopilot control system having fast time-varying dynamics. The influence of design and tuning parameters on the controller performance is analysed for setpoint tracking...
The generalized predictive contrller ( GPC) appears to be more robust than conventional adaptive controller in dealing with systems having varying and / or mismodelled dynamics. In this paper, a robust GPC law is combined with a robust parameter estimator to provide a practical adaptive control algorithm, which is applied to a ground air missile autopilot control system having fast time-varying dynamics. The influence of design and tuning parameters on the controller performance is analysed for setpoint tracking and disturbance rejestion, Aband-pass estimator filter and a controller filter are introduced into the GPC strategy for the purpose of improving the reliability of parameter estimation, providing robustness to model-plant mismatch and tailoring the rejection of disturbances, thus reducing the possibility of input oscillations and indeed saturation. Simulation results illustrate the good performance and the excellent properties of the presented control scheme, particularly its ability to cope with varying and mismodelled dynamics, variations of model order and high level disturbances.
导弹控制系统
missile control system
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