Results 141 to 150 of about 75,283 (193)

Bank-to-Turn Guidance Law with Terminal Impact-Angle Constraint

Journal of Aerospace Engineering, 2016
AbstractTo avoid the mathematical singularity of polar converting in bank-to-turn (BTT) guidance and to provide the specified terminal impact angle, a BTT guidance law with impact-angle constraint (BTT-GL/IA) is presented. Considering the influence of the impact-angle control and target maneuver to the miss-distance, a new form zero-effort miss ...
Wen Qiuqiu, Xia Qunli, Su Weixia
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Optimal pulsed guidance law with terminal impact angle constraint

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2016
An optimal pulsed guidance law with a time-varying weighted quadratic cost function that enables imposing a predetermined intercept angle is presented. Due to the characteristic of impulse force, admissible variance of control is redefined. The optimal pulsed guidance law is deduced via extended maximum principle.
JH Liu, JY Shan, Q Liu
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Elliptical Trajectory Guidance Law with Terminal Impact Angle Constraint

AIAA Atmospheric Flight Mechanics Conference, 2015
A guidance law with terminal impact angle constraint is presented, which can guide a missile in accordance with an elliptical trajectory to adapt its maneuverability. For ballistic missiles or reentry vehicles, maneuverability is limited and varies with the flight altitude and speed.
Tingting Zhang, Haoping SHE
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Nonsingular Terminal Sliding Mode Guidance with Impact Angle Constraints

Journal of Guidance, Control, and Dynamics, 2014
Guidance laws based on a conventional sliding mode ensures only asymptotic convergence. However, convergence to the desired impact angle within a finite time is important in most practical guidance applications. These finite time convergent guidance laws suffer from singularity leading to control saturation.
Shashi Ranjan Kumar, Sachit Rao, Debasish Ghose   +2 more
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Missile Guidance Law Considering Constraints on Impact Angle and Terminal Angle of Attack

AIAA Guidance, Navigation, and Control Conference, 2015
This paper proposes a guidance law considering constraints on impact angle and terminal angle of attack for a homing missile. In the proposed structure, the guidance law generates angle of attack command and the controller tracks the generated command.
Hyeonggeun Kim, H Jin Kim
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Segmented Optimal Guidance with Constraints on Terminal Angle of Attack and Impact Angle

50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2012
Guidance law with constraint on both terminal ight path angle and terminal angle of attack was considered.Linearized missile airframe and rst order missile dynamics were taken into account to add the angle of attack as a state of the guidance equation.
Qiang Xing, Wanchun Chen
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Biased PNG With Terminal-Angle Constraint for Intercepting Nonmaneuvering Targets Under Physical Constraints

IEEE Transactions on Aerospace and Electronic Systems, 2017
A biased proportional navigation guidance law, considering the seeker's look angle and acceleration capability limits, for impact-angle-control against nonmaneuvering targets is proposed. The proposed law consists of two time-varying biases: One is to achieve the desired impact angle within the command limit; the other is to keep the look angle ...
Bong-Gyun Park, Tae-Hun Kim, Min-Jea Tahk   +2 more
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Optimal linear quadratic guidance law with terminal impact angle constraint

2017 29th Chinese Control And Decision Conference (CCDC), 2017
Traditional guidance methods ensure simple algorithm and precision, however, they may create a lower impact angle. In recent years there has been an increasing interest in guidance law in order to improve the impact angle. This paper proposes an optimal guidance law under the constraints of miss distance and impact angle.
Zhao Jianyu, Yu Jianqiao, Yang Kun
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Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints

IEEE Transactions on Aerospace and Electronic Systems, 2013
The work presented here investigates proposed impact angle control guidance laws with terminal acceleration constraints for a stationary or slowly moving target. These laws, called time-to-go polynomial guidance (TPG), assume the guidance command as a polynomial function of time-to-go and determine the coefficients of the guidance command to satisfy ...
Lee, CH Lee, Chang-Hun, Kim, TH Kim, Tae-Hun, Tahk, MJ Tahk, Min-Jea, Whang, IH Whang, Ick-Ho   +3 more
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Sliding mode guidance with terminal angle and latax constraints

2019 Sixth Indian Control Conference (ICC), 2019
An interceptor equipped with a guidance strategy that can strike a target at a specified terminal angle increases its effectiveness. Sliding mode control theory has been used to design such a guidance strategy, as it offers numerous benefits. In this paper, the role played by the interceptor’s lateral acceleration (latax) bounds in the design of a ...
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