scholarly journals Impact Angle Control Guidance to Intercept Moving Targets by Virtual Target Technique

2021 ◽  
Vol 2021 ◽  
pp. 1-12
Author(s):  
Libing Hou ◽  
Jihong Zhu ◽  
Minchi Kuang ◽  
Heng Shi
Keyword(s):  
Numerical Simulations ◽  
Pid Controller ◽  
Impact Angle ◽  
Lateral Acceleration ◽  
Stable Theory ◽  
Moving Targets ◽  
Guidance Law ◽  
Flight Path Angle ◽  
Virtual Target ◽  
The Impact

To solve the problem regarding the impact angle of the missile, this paper proposes a novel guidance law, which can control the missile to hit the target at the desired angle. The key of the guidance law is selecting a moving point on the collision line as the virtual target, and the tactical requirements can be fulfilled by the missile directly pursuing the virtual target. The Lyapunov stable theory is used to prove the convergence of the proposed guidance law. The guidance command is generated by a PID controller to make the missile towards the virtual target. The proposed guidance law makes the lateral acceleration of the missile converge to zero, which leads the angle of attack to zero, and it theoretically guarantees the flight path angle equals the attitude angle. Numerical simulations demonstrate this impact angle control guidance law is very accurate and robust. Regardless of whether the initial heading error is large or small, the missile which employs the proposed guidance law can always hit the target from the preset direction and the guidance process is smooth.

Guidance law for mimicking short-range ballistic trajectories

2018 ◽  
Vol 233 (11) ◽  
pp. 4176-4190 ◽  
Author(s):  
Yash Raj Sharma ◽  
Ashwini Ratnoo
Keyword(s):  
Short Range ◽  
Impact Angle ◽  
Lateral Acceleration ◽  
Time Varying ◽  
Guidance Law ◽  
Point Analysis ◽  
Ballistic Trajectory ◽  
The Impact ◽  
Launch Angle ◽  
The Ideal

This paper considers the problem of mimicking short-range ballistic trajectories and presents a feedback guidance law addressing that. Analysis of the ideal ballistic trajectory is carried out and closed-form expressions are derived for the heading error and its derivative. Satisfying the launch angle, the impact angle, and the initial heading error rate of the ballistic trajectory, a guidance law is proposed using bearings-only information of the impact point. Analysis of the proposed guidance law is carried out evaluating the variation in guidance gains, the maximum look-angle, and the capturability. Analyzing the time-varying effective navigation gain, boundedness of the lateral acceleration is also ascertained. Simulations are carried out mimicking the ideal and realistic ballistic trajectories. Robustness of the proposed guidance method is verified against wind disturbances and error in modeling drag coefficient.

scholarly journals Intercepting Higher-Speed Targets Using Generalized Relative Biased Proportional Navigation

2019 ◽  
Vol 37 (4) ◽  
pp. 682-690
Author(s):  
Ronggang Wang ◽  
Shuo Tang
Keyword(s):  
High Speed ◽  
Impact Angle ◽  
Time Varying ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Flight Path Angle ◽  
Proportional Navigation Law ◽  
The Impact ◽  
Terminal Guidance

To intercept a higher-speed target in the terminal guidance phase, this paper proposes a generalized relative biased proportional navigation (BPN) law. In order to enlarge the capture domain of the classical proportional navigation (PN) law and make full use of the maneuverability of a missile, the paper designs time-varying navigation coefficients; thus the modified PN guidance law integrates the advantages of the PN guidance law with those of the retro-PN guidance law. In order to intercept high-speed targets with impact angle constraints, the relative BPN law is introduced, and the impact angle is achieved by controlling the relative flight-path angle. In order to improve the performance of the guidance law for intercepting higher-speed maneuvering targets, some compensation measures are designed for guidance commands. Extensive simulations are conducted to verify the design features of the proportional navigation law.

Trajectory shaping guidance law design using constraint-combining multiplier

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.

scholarly journals Design of Three-Dimensional Path Following Guidance Logic

2018 ◽  
Vol 2018 ◽  
pp. 1-11 ◽  
Author(s):  
Sungsu Park
Keyword(s):  
Numerical Simulations ◽  
Three Dimensional ◽  
Path Following ◽  
Guidance Law ◽  
Virtual Target ◽  
Projection Point ◽  
Motion Strategy

This paper presents a three-dimensional path following guidance logic. The proposed guidance logic is composed of the guidance law and the motion strategy of virtual target along the desired path. The guidance law makes a vehicle purse the virtual target, and the motion strategy explicitly specifies the motion of virtual target by introducing the concept of the projection point and the tangentially receding distance. The proposed logic is simple and efficient and yet provides precise path following. Numerical simulations are performed to demonstrate the effectiveness of the proposed guidance logic.

scholarly journals Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

2017 ◽  
Vol 2017 ◽  
pp. 1-12 ◽  
Author(s):  
Tianning Wang ◽  
Shengjing Tang ◽  
Jie Guo ◽  
Haoqiang Zhang
Keyword(s):  
Sliding Mode ◽  
Information Matrix ◽  
Impact Angle ◽  
Estimation Accuracy ◽  
Two Phase ◽  
Terminal Sliding Mode ◽  
Guidance Law ◽  
Optimal Guidance ◽  
The Impact ◽  
Impact Angle Constraint

The implementation of advanced guidance laws with bearings-only measurements requires estimation of the range information. To improve estimation accuracy and satisfy the impact angle constraint, this paper proposes a two-phase optimal guidance law consisting of an observing phase and an attacking phase. In the observing phase, the determinant of Fisher information matrix is maximized to achieve the optimal observability and a suboptimal solution expressed by leading angle is derived analytically. Then, a terminal sliding-mode guidance law is designed to track the desired leading angle. In the followed attacking phase, an optimal guidance law is integrated with a switching term to satisfy both the impact angle constraint and the field-of-view constraint. Finally, comparison studies of the proposed guidance law and a traditional optimal guidance law are conducted on stationary targets and maneuvering targets cases. Simulation results demonstrate that the proposed guidance law is able to improve the range observability and achieve better terminal performances including impact angle accuracy and miss distance.

Fixed-time three-dimensional guidance law with input constraint and actuator faults

2020 ◽  
pp. 095441002097197
Author(s):  
Peng Li ◽  
Qi Liu ◽  
Chen-Yu He ◽  
Xiao-Qing Liu
Keyword(s):  
Fault Tolerant ◽  
Sliding Mode ◽  
Input Saturation ◽  
Three Dimensional ◽  
Impact Angle ◽  
Actuator Faults ◽  
Input Constraint ◽  
Guidance Law ◽  
The Impact ◽  
Impact Angle Constraint

This paper investigates the three-dimensional guidance with the impact angle constraint, actuator faults and input constraint. Firstly, an adaptive three-dimensional guidance law with impact angle constraint is designed by using the terminal sliding mode control and nonhomogeneous disturbance observer. Then, in order to solve the problem of the input saturation and actuator faults, an adaptive anti-saturation fault-tolerant three-dimensional law is proposed by using the hyperbolic tangent function based on the passive fault-tolerant control. Finally, the effectiveness of the designed guidance laws is verified by using the Lyapunov function and simulation.

scholarly journals A New Impact Time and Angle Control Guidance Law for Stationary and Nonmaneuvering Targets

2016 ◽  
Vol 2016 ◽  
pp. 1-14 ◽  
Author(s):  
Zhe Yang ◽  
Hui Wang ◽  
Defu Lin ◽  
Luyao Zang
Keyword(s):  
Sliding Mode Control ◽  
Sliding Mode ◽  
Impact Angle ◽  
Accurate Solution ◽  
Control Surface ◽  
Impact Time ◽  
Tuning Parameters ◽  
Mode Control ◽  
Guidance Law ◽  
The Impact

A guidance problem for impact time and angle control applicable to cooperative attack is considered based on the sliding mode control. In order to satisfy the impact angle constraint, a line-of-sight rate polynomial function is introduced with four tuning parameters. And the time-to-go derivative with respect to a downrange orientation is derived to minimize the impact time error. Then the sliding mode control surface with impact time and angle constraints is constructed using nonlinear engagement dynamics to provide an accurate solution. The proposed guidance law is easily extended to a nonmaneuvering target using the predicted interception point. Numerical simulations are performed to verify the effectiveness of the proposed guidance law for different engagement scenarios.

Optimal Guidance Law: Impact Angle & Terminal Lateral Acceleration Control

2009 ◽  
Vol 42 (2) ◽  
pp. 321-325 ◽  
Author(s):  
Chang-Kyung Ryoo ◽  
H. Jin Kim ◽  
Min-Jea Tahk ◽  
Jin-Ik Lee
Keyword(s):  
Impact Angle ◽  
Lateral Acceleration ◽  
Guidance Law ◽  
Optimal Guidance

Dispersion reduction of artillery rockets guided by flight path steering method

2016 ◽  
Vol 120 (1225) ◽  
pp. 435-456 ◽  
Author(s):  
S. Mandić
Keyword(s):  
Measurement Errors ◽  
Flight Path ◽  
Guidance System ◽  
Lateral Acceleration ◽  
Dominant Factor ◽  
Measurement Unit ◽  
Impact Point ◽  
Angle Correction ◽  
Flight Path Angle ◽  
The Impact

ABSTRACTArtillery rockets are sensitive to disturbances (total impulse variation, wind, thrust misalignment, etc.). As the range of ground-to-ground rockets increases, the accuracy of free flight rockets decreases. Requirements for the increase of the range and minimisation of the impact point dispersions can be solved by adding guidance and control systems to rockets. Based on the differences between the measured flight parameters and the calculated parameters for the nominal trajectory, the flight path angle correction algorithm is obtained by adding the correction to the nominal value. The flight path steering guidance system with lateral acceleration autopilot in the inner loop, is used for the guidance of hypothetical artillery rockets. The guidance algorithm given in this paper eliminates the time correction due to rocket velocity variations. Efficiency of the proposed algorithm is illustrated by numerical simulation. There is no practical influence of the external disturbances on impact point dispersion. It is also shown that the measurement errors of the inertial measurement unit are the dominant factor affecting impact point dispersion of artillery rockets modified by adding a guidance system based on the flight path steering method.

Sign in / Sign up

Export Citation Format

Share Document