A robust impact angle constraint guidance law with seeker’s field-of-view limit

A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.

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Time-Varying Biased Proportional Guidance with Seeker’s Field-of-View Limit

International Journal of Aerospace Engineering ◽

10.1155/2016/9272019 ◽

2016 ◽

Vol 2016 ◽

pp. 1-11 ◽

Cited By ~ 6

Author(s):

Zhe Yang ◽

Hui Wang ◽

Defu Lin

Keyword(s):

Impact Angle ◽

Field Of View ◽

Line Of Sight ◽

Terminal Phase ◽

Time Varying ◽

Guidance Law ◽

Homing Missiles ◽

Guidance Laws ◽

Bias Terms ◽

Impact Angle Constraint

Traditional guidance laws with range-to-go information or time-to-go estimation may not be implemented in passive homing missiles since passive seekers cannot measure relative range directly. A time-varying biased proportional guidance law, which only uses line-of-sight (LOS) rate and look angle information, is proposed to satisfy both impact angle constraint and seeker’s field-of-view (FOV) limit. In the proposed guidance law, two time-varying bias terms are applied to divide the trajectory into initial phase and terminal phase. The initial bias is designed as a function of LOS rate and look angle to maintain the seeker’s lock-on while the final bias eliminates the deviation between the integral value of angle control bias and the expected bias amount. A switching logic is adopted to change the biases continuously so that there is no abrupt acceleration change during the engagement. Extensive simulations considering both kinematic and realistic missile models are performed to illustrate the efficiency of the proposed method.

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Trajectory shaping guidance law design using constraint-combining multiplier

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410020986371 ◽

2021 ◽

pp. 095441002098637

Author(s):

Min-Guk Seo ◽

Chang-Hun Lee ◽

Tae-Hun Kim

Keyword(s):

Design Method ◽

Impact Angle ◽

State Variables ◽

Flight Trajectory ◽

Potential Significance ◽

Guidance Law ◽

Terminal Constraints ◽

The Impact ◽

Guidance Laws ◽

Impact Angle Constraint

A new design method for trajectory shaping guidance laws with the impact angle constraint is proposed in this study. The basic idea is that the multiplier introduced to combine the equations for the terminal constraints is used to shape a flight trajectory as desired. To this end, the general form of impact angle control guidance (IACG) is first derived as a function of an arbitrary constraint-combining multiplier using the optimal control. We reveal that the constraint-combining multiplier satisfying the kinematics can be expressed as a function of state variables. From this result, the constraint-combining multiplier to achieve a desired trajectory can be obtained. Accordingly, when the desired trajectory is designed to satisfy the terminal constraints, the proposed method directly can provide a closed form of IACG laws that can achieve the desired trajectory. The potential significance of the proposed result is that various trajectory shaping IACG laws that can cope with various guidance goals can be readily determined compared to existing approaches. In this study, several examples are shown to validate the proposed method. The results also indicate that previous IACG laws belong to the subset of the proposed result. Finally, the characteristics of the proposed guidance laws are analyzed through numerical simulations.

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Three-Dimensional Fixed-Time Cooperative Guidance Law With Impact Angle Constraint and Prespecified Impact Time

IEEE Access ◽

10.1109/access.2021.3057428 ◽

2021 ◽

Vol 9 ◽

pp. 29755-29763

Author(s):

Mu Lin ◽

Xiangjun Ding ◽

Chunyan Wang ◽

Li Liang ◽

Jianan Wang

Keyword(s):

Three Dimensional ◽

Fixed Time ◽

Impact Angle ◽

Impact Time ◽

Guidance Law ◽

Cooperative Guidance ◽

Impact Angle Constraint

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Fractional-order sliding mode control based guidance law with impact angle constraint

Nonlinear Dynamics ◽

10.1007/s11071-021-06820-6 ◽

2021 ◽

Author(s):

Yongzhi Sheng ◽

Zhuo Zhang ◽

Lei Xia

Keyword(s):

Sliding Mode Control ◽

Fractional Order ◽

Sliding Mode ◽

Impact Angle ◽

Mode Control ◽

Guidance Law ◽

Impact Angle Constraint

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FOV constrained guidance law for nonstationary nonmaneuvering target interception with any impact angle

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/09544100211046867 ◽

2021 ◽

pp. 095441002110468

Author(s):

Nikhil Kumar Singh ◽

Sikha Hota

Keyword(s):

Kinematic Model ◽

Angular Spectrum ◽

Impact Angle ◽

Field Of View ◽

Two Dimensional ◽

Proportional Navigation ◽

Guidance Law ◽

Real World Applications ◽

Target Interception ◽

Impact Angles

This paper presents the nonstationary nonmaneuvering target interception with all possible desired impact angles in a two-dimensional (2D) aerial engagement scenario, where the target can move in any direction. The paper also considers the field-of-view (FOV) constraint for designing the guidance law so that the target is always visible while following the missile trajectory in the entire engagement time, which makes it feasible for real world applications. The guidance law is based on the pure proportional navigation (PPN) to achieve any impact angle of the entire angular spectrum. The proposed guidance law is then simulated for intercepting a nonstationary nonmaneuvering target using a kinematic model of a missile to demonstrate the efficacy of the presented scheme. A comparison with the related work existing in the literature has also been added to establish the superiority of the present work.

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