| In modern battlefield, air-to-ground tactical missile, which can perform the task of battlefield suppress, breaking and attacking the enemy targets in depth,has been a kind of very effective guided weapon. Attitude control system is significant in the whole design of the missile, it is a part of the guidance system,and affects the accuracy of missile directly.The missile guidance system is divided into two sections:One is steering system,and the other is control system. Steering system send out the command of tracking target or correction error to the control system of missile. Control system control the centroid and attitude for the operation and stabilization of missile according to the instruction. At present,most missile control centroid indirectly by control of attitude. This paper focuses on design method of air-to-grond tactical missile attitude control loop.This paper includes the following several aspects:first, the missile of this paper is a kand of small tactical misiles, its aerodynamic shape is axisymmetric model. Establishing mathematical model through hypothesis and simplified of small disturbance linearization and freezing theory, then select the characteristic points which could represent the quality of arbitrary point on all possible trajectory of this missile; Second, using the frequency response correction classic method which is belong to the classic method to design attitude controller of pitch channel and roll channel, then analyse the advantage and disadvantage of the theory on attitude control system of missile; Third, about the slope channel of this missile in paper, design the attitude controller with sliding mode variable structure control, then analyse its advantages and diszavantages. forth, about the slope channel of this missile in paper, design the attitude controller with model reference adapting control, then analyse its advantages and diszavantages. Fifth, summarizes the full paper, and put forward its further research direction. |
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