Results 261 to 270 of about 539,000 (325)

Optimal Guidance Laws with Terminal Impact Angle Constraint

Journal of Guidance, Control, and Dynamics, 2005
Optimal guidance laws providing the specified impact angle as well as zero terminal miss distance are generalized for arbitrary missile dynamics. The optimal guidance command is represented by a linear combination of the ramp and the step responses of the missile’s lateral acceleration.
Ryoo, CK, Cho, HJ, Tahk, MJ Tahk, Min-Jea   +2 more
openaire   +2 more sources

A Parameterized Solution to Optimal Guidance Law Against Stationary Target With Impact Angle Constraint

IEEE Transactions on Aerospace and Electronic Systems
A 3-D parameterized guidance law against stationary target with impact angle constraint is proposed in this article. In particular, we perform a dimension reduction on the relative motion in the rotating line-of-sight frame, and proceed to formulate the ...
Yiji Zhu, Cong Zhou, Sai Chen, Xun Song, Kebo Li, Chaoyong Li   +5 more
semanticscholar   +1 more source

Optimal sliding mode guidance law against maneuvering target with impact angle constraint

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
In this paper, an optimal sliding mode guidance law with impact angle constraint is proposed against maneuvering targets. Firstly, the impact angle frame for a static target is extended to a maneuvering target.
Mian Gong, Siteng Zhou, Di Zhou
semanticscholar   +1 more source

Novel second-order sliding mode guidance law with an impact angle constraint that considers autopilot lag for intercepting manoeuvering targets

Aeronautical Journal, 2020
A novel second-order sliding-mode-based impact angle and autopilot lag guidance law for engaging manoeuvering targets with unknown acceleration is presented in this study. A backstepping technique is applied to the design of the sliding surface.
W.J. Zhang, Q. Xia, W. Li
semanticscholar   +1 more source

Design of Guidance Law with Impact Angle and Impact Time Constraints

Advanced Materials Research, 2014
In order to achieve the tactical mission of cooperative attack for multi-missiles, in a predetermined direction at a predetermined time, this paper studies the design of guidance law with impact angle and impact time constraints. Firstly, using the optimal control theory, the optimal guidance law is designed to control the impact angle, based the ...
Lin Ping Feng, Zuo E Fan, You Gen Zhang
openaire   +1 more source

A novel non-singular terminal sliding mode control-based integrated missile guidance and control with impact angle constraint

Aerospace Science and Technology, 2019
A novel impact angle constrained integrated guidance and control (IGC) scheme is proposed with non-singular terminal sliding mode control (NTSMC) technique for missile to intercept a maneuverable target.
Chao Ming, Xiaoming Wang, Ruisheng Sun
semanticscholar   +1 more source

Partial Integrated Guidance and Control with Impact Angle Constraints

Journal of Guidance, Control, and Dynamics, 2015
Novel sliding-mode control laws are proposed in this paper to stabilize a class of uncertain nonlinear systems. Considering that the sign function, which is often used in the sliding-mode control can cause chattering of control input, the saturation function is used to take its place in proposed controllers.
Xianghua Wang, Jinzhi Wang
openaire   +1 more source

Adaptive PPN guidance law with impact angle constraint

2013 American Control Conference, 2013
In this work, two adaptive guidance law which achieve the specified impact angle are proposed. The first one is based on the conventional PPN guidance law, while the second one is inspired by controlling the turn rate of relative velocity. Since in both cases the analytical solutions of relative angles between target and missile velocity vectors are ...
openaire   +1 more source

Three-dimensional guidance law with terminal impact angle constraint

2009 International Conference on Mechatronics and Automation, 2009
Based on the dynamics and kinematics of the relative motion between missile and target for missile guidance, under the assumptions that the target is stationary, and the velocity of missile is a constant, and according to the error between the real impact angle and the designated impact angle, the desired kinematics of LOS (line of sight) is analyzed ...
null Ma Pei-bei, null Zhang You-an, null Ji Jun, null Zhang Xiao-jie   +3 more
openaire   +1 more source

Integrated guidance and control of interceptors with impact angle constraint against a high-speed maneuvering target

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2019
An integrated guidance and control method is investigated for interceptors with impact angle constraint against a high-speed maneuvering target. Firstly, a new control-oriented model with impact angle constraint of the integrated guidance and control ...
Guanjie Hu, Jianguo Guo, Jun Zhou
semanticscholar   +1 more source