Generalized weighted optimal guidance laws with impact angle constraints

被引：0

作者：

Zhang, Youan ^{[1
]}

Huang, Jie ^{[1
,2
]}

Sun, Yangping ^{[1
]}

机构：

[1] Department of Control Engineering, Naval Aeronautical and Astronautical University

[2] Qingdao Branch, Naval Aeronautical and Astronautical University

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2014年 / 35卷 / 03期

关键词：

Exponential weighting; Impact angle constraint; Missiles; Optimal guidance; Schwarz's inequality; Weighted function;

D O I：

10.7527/S1000-6893.2013.0364

中图分类号：

学科分类号：

摘要：

The impact angle frame is defined which axis is in the direction of the desired impact angle, and the engagement kinematics is established in the impact angle frame. Generalized weighted optimal guidance laws with impact angle constraints are studied for first-order lag control systems and lag-free control systems respectively using Schwarz's inequality approach. For lag-free control systems and first-order lag control systems with elementary function weighting, the analytical forms of weighted optimal guidance laws can be obtained if the integrations of the inverse of the weighting functions up to triple can be analytically given. The results can be applied to guidance law designs for accomplishing different guidance objectives. For some specific weighted functions, the proposed guidance law has extended the results in references. Simulation results are given for the exponential weighting optimal guidance law with impact angle constraints.

引用

页码：848 / 856

页数：8

共 16 条

[1]

Ratnoo A., Ghose D., Impact angle constrained interception of stationary targets, Journal of Guidance, Control, and Dynamics, 31, 6, pp. 1816-1821, (2008)

[2]

Ratnoo A., Ghose D., Impact angle constrained guidance against nonstationary nonmaneuvering targets, Journal of Guidance, Control, and Dynamics, 33, 1, pp. 269-275, (2010)

[3]

Hu X., Huang X.M., Three-dimensional circular guidance law with impact angle constraints, Acta Aeronautica et Astronautica Sinica, 33, 3, pp. 508-519, (2012)

[4]

Lee C.H., Kim T.H., Tahk M.J., Et al., Polynomial guidance laws considering terminal impact angle/acceleration constraints, IEEE Transactions on Aerospace and Electronic Systems, 49, 1, pp. 74-92, (2013)

[5]

Sun S., Zhang H.M., Zhou D., Sliding mode guidance law with autopilot lag for terminal angle constrained trajectories, Journal of Astronautics, 34, 1, pp. 69-78, (2013)

[6]

Zhang Y.A., Ma P.B., Three-dimensional guidance laws with impact angle and impact time constraints, Acta Aeronautica et Astronautica Sinica, 29, 4, pp. 1020-1026, (2008)

[7]

Lee J.I., Jeon I.S., Tahk M.J., Guidance law to control impact time and angle, IEEE Transactions on Aerospace and Electronic Systems, 43, 1, pp. 301-310, (2007)

[8]

Cho H., Ryoo C.K., Tahk M.J., Implementation of optimal guidance laws using predicted velocity profiles, Journal of Guidance, Control, and Dynamics, 22, 4, pp. 579-588, (1999)

[9]

Bryson A.E., Ho Y.C., Applied Optimal Control: Optimization, Estimation and Control, pp. 1-41, (1975)

[10]

Ryoo C.K., Cho H., Tahk M.J., Optimal guidance laws with terminal impact angle constraint, Journal of Guidance, Control, and Dynamics, 28, 4, pp. 724-732, (2005)

← 1 2 →