A Field-of-view Constrained Switched-Phase Two-Stage Adaptive Integrated Guidance Law

This article proposes an impact-time-control guidance law that can keep a non-maneuvering moving target in the seeker’s field of view (FOV). For a moving target, the missile calculates a predicted intercept point (PIP), designates the PIP as a new virtual stationary target, and flies to the PIP at the desired impact time. The main contribution of the article is that the guidance law is designed to always lock onto the moving target by adjusting the guidance gain. The guidance law for the purpose is based on the backstepping control technique and designed to regulate the defined impact time error. In this procedure, the desired look angle, which is a virtual control, is designed not to violate the FOV limit, and the actual look angle of the missile is kept within the FOV by tracking the desired look angle. To validate the performance of the guidance law, numerical simulation is conducted with different impact times. The result shows that the proposed guidance law intercepts the moving target at the desired impact time maintaining the target lock-on condition.

Download Full-text

Study on project trajectory of air-to-ground missile with strapdown seeker under multi constraints

Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University ◽

10.1051/jnwpu/20213910141 ◽

2021 ◽

Vol 39 (1) ◽

pp. 141-147

Author(s):

Junmin Zhao ◽

Cong Nie ◽

Guannan Chang ◽

Meibo Lyu ◽

Xinguo Li

Keyword(s):

Good Condition ◽

Field Of View ◽

Small Field ◽

Target Acquisition ◽

Moving Targets ◽

Proportional Navigation ◽

Terminal Stage ◽

Guidance Law ◽

Terminal Guidance ◽

Small Field Of View

The air-to-ground missile with strapdown seeker may have the problems, including small field of view(FOV), limited overload, and fall angle constraint. To solve the above mentioned problem, a phased guidance scheme is proposed. In this scheme, the attack trajectory is divided into the following six stages, including glided stage, fall angle constraint stage, target acquisition and adjustment stage, terminal guidance stage and blind zone stage. The glided stage is designed to increase range, the terminal fall angle is attained ahead of time at fall angle constraint stage. The aim of target acquisition and adjustment stage is to adjust the missile attitude, so that the target will fall within the FOV of the seeker. It creates good condition to capture the target for strapdown seeker. In the terminal stage, the guidance law of proportional navigation and attitude track are used to fit the needs of FOV constraint and attack accuracy. The simulation result shows that the project trajectory can solve the application of attacking moving targets for air-to-ground missile with strapdown seeker under multi constraints.

Download Full-text

Field-of-View Constrained Polynomial Guidance Law for Dual-Seeker Interceptors

2018 AIAA Guidance, Navigation, and Control Conference ◽

10.2514/6.2018-1325 ◽

2018 ◽

Cited By ~ 2

Author(s):

Vijay Hirwani ◽

Ashwini Ratnoo

Keyword(s):

Field Of View ◽

Guidance Law

Download Full-text

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.

Download Full-text

Guidance law to control impact time constraining the seeker’s field of view?

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-06-2017-0151 ◽

2018 ◽

Vol 91 (1) ◽

pp. 20-29 ◽

Cited By ~ 2

Author(s):

Jian Hu ◽

Naigang Cui ◽

Yuliang Bai ◽

Yunhai Geng

Keyword(s):

Stability Theory ◽

Lyapunov Stability Theory ◽

Field Of View ◽

Convergence Time ◽

Stationary Target ◽

Content Type ◽

Impact Time ◽

Finite Time Stability ◽

Guidance Law ◽

The Impact

Purpose The purpose of this paper is to present a novel guidance law that is able to control the impact time while the seeker’s field of view (FOV) is constrained. Design/methodology/approach The new guidance law is derived from the framework of Lyapunov stability theory to ensure interception at the desired impact time. A time-varying guidance gain scheme is proposed based on the analysis of the convergence time of impact time error, where finite-time stability theory is used. The circular trajectory assumption is adopted for the derivation of accurate analytical estimation of time-to-go. The seeker’s FOV constraint, along with missile acceleration constraint, is considered during guidance law design, and a switching strategy to satisfy it is designed. Findings The proposed guidance law can drive missile to intercept stationary target at the desired impact time, as well as satisfies seeker’s FOV and missile acceleration constraints during engagement. Simulation results show that the proposed guidance law could provide robustness against different engagement scenarios and autopilot lag. Practical implications The presented guidance law lays a foundation for using cooperative strategies, such as simultaneous attack. Originality/value This paper presents further study on the impact time control problem considering the seeker’s FOV constraint, which conforms better to reality.

Download Full-text

Look-Angle-Shaping Guidance Law for Impact Angle and Time Control With Field-of-View Constraint

IEEE Transactions on Aerospace and Electronic Systems ◽

10.1109/taes.2019.2924175 ◽

2020 ◽

Vol 56 (2) ◽

pp. 1602-1612 ◽

Cited By ~ 1

Author(s):

Hyeong-Geun Kim ◽

Jun-Yong Lee ◽

Hyoun Jin Kim ◽

Hyuck-Hoon Kwon ◽

Jang-Seong Park

Keyword(s):

Impact Angle ◽

Field Of View ◽

Time Control ◽

Guidance Law

Download Full-text

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

International Journal of Aerospace Engineering ◽

10.1155/2019/8939213 ◽

2019 ◽

Vol 2019 ◽

pp. 1-8

Author(s):

Jianbo Zhao ◽

Fenfen Xiong

Keyword(s):

Linear Quadratic ◽

Control Cost ◽

Proportional Navigation ◽

Two Stage ◽

Maximum Acceleration ◽

Linear Quadratic Optimal Control ◽

Position Information ◽

Precise Position ◽

Guidance Law ◽

Cooperative Guidance

A novel cooperative guidance scenario is proposed that implements fire-and-forget attacks for seeker-less missiles with a cheap finder for stationary targets and without requiring real-time communication among missiles or precise position information. Within the proposed cooperative scenario, the classic leader-follower framework is utilized, and a two-stage cooperative guidance law is derived for the seeker-less missile. Linear-quadratic optimal control and biased proportional navigation guidance (PNG) are employed to develop this two-stage cooperative guidance law to minimize the control cost in the first stage and to reduce the maximum acceleration command in the second stage when the acceleration command is continuous. Simulations and comparisons are conducted that demonstrate the effectiveness and advantages of the proposed guidance law.

Download Full-text