MODIFIED GUIDANCE LAW BASED ON A SLIDING MODE CONTROLLER FOR A MISSILE GUIDANCE SYSTEM
MODIFIED GUIDANCE LAW BASED ON A SLIDING MODE CONTROLLER FOR A MISSILE GUIDANCE SYSTEM
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基于滑模控制器的导弹制导系统改进制导律
DOI：
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发表时间：
2016
期刊：
影响因子：
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通讯作者：
Md. Mijanur Rahman
中科院分区：
文献类型：
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作者：
A. Alrawi;S. Graovac;R. Ahmad;Md. Mijanur Rahman
在科技论文的基础上，针对某型导弹系统提出了一种改进的制导与控制滑模控制器(MGCSMC)方法。采用改进的滑模控制器(MSMC)算法，使导弹在短时间内到达预定目标。当导弹靠近目标时，目标总是进行高机动。在制导与控制(G&C)中，用MSMC代替传统的比例导引方法，对SMC中的脱靶量和抖振现象进行了理论分析。仿真结果表明，与PN方法相比，MGCSMC在抖振、脱靶量和有限时间方面分别改善了约80%、47%和20%。此外，对于高空目标，MGCSMC使导弹的加速度和飞行角度提高了约65%，并且达到了100%的精度，而在相同条件下，PN方法只达到了60%的精度。
Original scientific paper In this paper, a modified guidance and control sliding mode controller (MGCSMC) method is proposed in a guided missile system. The modified sliding mode controller (MSMC) algorithm is adopted to enable the missile to reach the desired target within a short period of time. The target always makes high manoeuvres when the missile is close to it. This issue has been treated in guidance and control (G&C) by using a MSMC instead of the traditional method such as proportional navigation method (PN).Theoretical analysis is conducted to reduce the miss-distance and chattering phenomenon in SMC. Simulation of MGCSMC compared with PN method shows an improvement of about 80 %, 47 % and 20 % for the chattering, miss-distance and finite time, respectively. Furthermore, for the high-altitude target, the MGCSMC improves the acceleration and flight angle of the missile by approximately 65 %, and achieves 100 % accuracy, whereas in PN method only 60 % accuracy is achieved under the same conditions.