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作 者:张晨欣 王宁宇 王小刚[2] ZHANG Chenxin;WANG Ningyu;WANG Xiaogang(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)
机构地区:[1]国防科技大学空天科学学院,长沙410073 [2]哈尔滨工业大学航天学院,哈尔滨150001
出 处:《宇航学报》2023年第10期1544-1554,共11页Journal of Astronautics
基 金:国家自然科学基金项目(U20B2005)。
摘 要:针对空空导弹期望时间拦截强机动目标问题,提出了一种不依赖剩余时间估计的新型攻击时间约束滑模制导律。设计了一种以弹目距离和攻击时间误差加权求和的滑模面,通过分析制导收敛条件,推导得到自适应非奇异权重函数,通过引入有限时间收敛条件,得到了一种有限时间收敛滑模制导律。该制导律在不依赖剩余时间估计条件下保证了终端打击精度和攻击时间约束。通过设计包含滑模变量的附加制导项,显著提升了攻击时间的收敛精度。针对未知加速度机动目标,分析并证明了该制导律对于拦截强机动目标具有良好的适用性。最后通过数学仿真验证了所提出的制导律在不同约束条件下的有效性,并通过对比仿真验证了算法的优越性。This paper presents a new impact time control guidance law of air-to-air missiles independent of time-to-go prediction for intercepting maneuvering targets.Firstly,a novel sliding mode surface weighted by the sum of missile-target distance and impact time errors is designed.By analyzing the guidance law convergence conditions,the adaptive nonsingular weight functions are derived.Secondly,by introducing the finite-time convergence condition,a finite-time convergence time-constrained sliding mode guidance law is obtained.The proposed guidance law guarantees the terminal strike accuracy and impact time constraint independent of time-to-go prediction.And then,the convergence accuracy of impact time is significantly improved by designing the additional guidance term including sliding mode variable.After that,the proposed guidance law is analyzed and proved to have good applicability for intercepting the strong maneuvering target with unknown acceleration.Finally,the effectiveness of the proposed guidance law under different constraints conditions are verified by mathematical simulations,and the superiority of the guidance law is verified by comparative simulations.
关 键 词:空空导弹 强机动目标 攻击时间约束 有限时间收敛 滑模制导律
分 类 号:V249.32[航空宇航科学与技术—飞行器设计]
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