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

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.

scholarly journals Generalized Guidance Formulation for Impact Angle Interception with Physical Constraints

Aerospace ◽  
2021 ◽  
Vol 8 (10) ◽  
pp. 307
Author(s):  
Hyeong-Geun Kim ◽  
Jun-Yong Lee
Keyword(s):  
Impact Angle ◽  
Field Of View ◽  
Line Of Sight ◽  
Physical Constraints ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Rate Profile ◽  
Homing Missiles ◽  
Impact Angles ◽  
General Guidance

This paper proposes an optimal impact angle control guidance law for homing missiles with a narrow field-of-view of the seekers. As groundwork for designing a guidance law, we first present a general guidance structure that can achieve any terminal constraint of the line-of-sight rate based on the optimal control theory. We configure the desired profile of the line-of-sight rate using a saturation function whose exact form is determined to satisfy the required boundary conditions. By combining the line-of-sight rate profile with the optimal guidance structure, we develop a guidance law that achieves an impact angle interception with the field-of-view constraint. Herein, as the entire guidance structure is derived based on exact kinematics without any approximation, the proposed law ensures the accurate impact angle interception for various engagement scenarios. This precise consideration of the engagement kinematics also accurately ensures the energy optimality of preventing the excessive use of control inputs when homing. To evaluate the performance of the proposed method, numerical simulations with various engagement scenarios are conducted, and the results demonstrate that the proposed law allows missiles to accurately intercept their targets with the desired impact angles and without violating the prescribed field-of-view constraint.

Field-of-view-constrained impact angle control guidance with error convergence before interception considering speed changes

2020 ◽  
pp. 095441002094201
Author(s):  
Jinrae Kim ◽  
Namhoon Cho ◽  
Youdan Kim
Keyword(s):  
Impact Angle ◽  
Field Of View ◽  
Time Varying ◽  
Angle Error ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Guidance Law ◽  
Independent Variable ◽  
Angle Interval ◽  
The Impact

An impact angle control guidance law is proposed for stationary target interception considering missile's field-of-view limit and speed changes. The proposed impact angle control guidance law is structured as a biased proportional navigation with a time-varying bias. The proposed guidance law does not involve any switching logic for maintaining lock-on; hence, the guidance command is continuous during the entire engagement. Unlike the most existing studies, the proposed method guarantees that the impact angle error converges to zero before interception without the constant-speed assumption. To realize these desirable properties, the positive invariance of the bounded look angle interval and the change of independent variable are utilized. Numerical simulations are conducted to demonstrate the performance of the proposed guidance law.

Polynomial guidance law for impact angle control with a seeker look angle limit

2019 ◽  
Vol 234 (3) ◽  
pp. 857-870
Author(s):  
Zhou Zhiming ◽  
Xiaoxian Yao
Keyword(s):  
Impact Angle ◽  
Line Of Sight ◽  
Time Varying ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Nonlinear Simulations ◽  
Impact Angles ◽  
The Impact ◽  
Guidance Laws

In this paper, the impact angle control problem is investigated by applying the polynomial shaping method. By shaping the light-of-sight angle with relative range, a guidance law called range polynomial guidance is proposed, and the coefficients are determined by boundary conditions. The range polynomial guidance law can be applied to maneuvering targets. By profiling the seeker look angle with the light-of-sight angle, a guidance law called line-of-sight polynomial guidance is developed for impact angle control under a limitation on the seeker look angle. The line-of-sight polynomial guidance law is also effective in intercepting a non-maneuvering moving target at the desired impact angle. Guidance laws with different gain sets are discussed in this paper. The proposed guidance laws take the form of proportional navigation with a time-varying navigation gain. Nonlinear simulations are performed to validate the efficacy of the proposed guidance laws in various engagement conditions. Comparison with other studies demonstrates the practicality and flexibility of the proposed guidance laws in the design of desired impact angles and maximum look angles.

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

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.

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

2020 ◽  
Vol 56 (2) ◽  
pp. 1602-1612 ◽  
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

Generalized optimal impact-angle-control guidance with terminal acceleration response constraint

2017 ◽  
Vol 231 (14) ◽  
pp. 2515-2536 ◽  
Author(s):  
Hui Wang ◽  
Jiang Wang ◽  
Defu Lin
Keyword(s):  
General Expression ◽  
Impact Angle ◽  
Acceleration Response ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Terminal Constraints ◽  
Miss Distance ◽  
Guidance Laws ◽  
Impact Angle Constraint

To study the optimal impact-angle-control guidance problem with multiple terminal constraints, a generalized optimal impact-angle-control guidance law with terminal acceleration response constraint (GOIACGL-TARC) is proposed. In the deriving, a time-to-go − nth power weighted object function is adopted to derived the GOIACGL-TARC and a general expression of GOIACGL-TARC is presented. Based on the general expression of GOIACGL-TARC, three guidance laws, GOIACGL-TARC1/TACC0/TACC1 are proposed and the inheritance relationship between GOIACGL-TACC0/TACC1/TARC1 and the conventional optimal guidance law with impact angle constraint is demonstrated. Performance analysis of the proposed guidance laws shows that in the case of GOIACGL-TACC0, the terminal acceleration is not zero at n = 0 and only as n > 0, the terminal acceleration converges to zero; in the case of GOIACGL-TACC1 and GOIACGL-TARC1, GOIACGL-TARC1 can guarantee the acceleration response to reach the exactly zero value but GOIACGL-TACC1 cannot, which can only guarantee the acceleration command to reach the exactly zero value. It is pointed out that compared with the biased proportional navigation guidance law, GOIACGL-TARC1 has an outstanding guidance performance in acceleration response, miss distance, and terminal impact angle error.

scholarly journals Impact Time Control Cooperative Guidance Law Design Based on Modified Proportional Navigation

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 231
Author(s):  
Zhanyuan Jiang ◽  
Jianquan Ge ◽  
Qiangqiang Xu ◽  
Tao Yang
Keyword(s):  
Constant Velocity ◽  
Three Dimensional ◽  
Estimation Method ◽  
Time Varying ◽  
Two Dimensional ◽  
Proportional Navigation ◽  
Impact Time ◽  
Time Control ◽  
Guidance Law ◽  
Cooperative Guidance

The paper proposes a two-dimensional impact time control cooperative guidance law under constant velocity and a three-dimensional impact time control cooperative guidance law under time-varying velocity, which can both improve the penetration ability and combat effectiveness of multi-missile systems and adapt to the complex and variable future warfare. First, a more accurate time-to-go estimation method is proposed, and based on which a modified proportional navigational guidance (MPNG) law with impact time constraint is designed in this paper, which is also effective when the initial leading angle is zero. Second, adopting cooperative guidance architecture with centralized coordination, using the MPNG law as the local guidance, and the desired impact time as the coordination variables, a two-dimensional impact time control cooperative guidance law under constant velocity is designed. Finally, a method of solving the expression of velocity is derived, and the analytic function of velocity with respect to time is given, a three-dimensional impact time control cooperative guidance law under time-varying velocity based on desired impact time is designed. Numerical simulation results verify the feasibility and applicability of the methods.

scholarly journals Impact Angle Control Guidance Law Considering the Seeker’s Field-of-View Constraint Applied to Variable Speed Missiles

IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 100608-100619
Author(s):  
Shou Zhou ◽  
Cheng Hu ◽  
Pan Wu ◽  
Shifeng Zhang
Keyword(s):  
Impact Angle ◽  
Field Of View ◽  
Variable Speed ◽  
Guidance Law
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