Proportional navigation law design of plane-symmetrical vehicle with terminal attack angle constraint for over target flight

2016 ◽  
Author(s):  
Bin Wu ◽  
Denggao Ji ◽  
Zhenxi Guo ◽  
Haibin Shen ◽  
Jianfei Zhang
Keyword(s):  
Attack Angle ◽  
Proportional Navigation ◽  
Proportional Navigation Law

Proportional Navigation and Model Predictive Control of an Unmanned Autonomous Vehicle for Obstacle Avoidance

2018 ◽  
Author(s):  
Ryan P. Shaw ◽  
David M. Bevly
Keyword(s):  
Obstacle Avoidance ◽  
Autonomous Vehicle ◽  
Integrated System ◽  
Reference Trajectory ◽  
Ground Vehicles ◽  
Proportional Navigation ◽  
Predictive Controller ◽  
Proportional Navigation Law ◽  
Vehicle Dynamic Model ◽  
And Control

This paper presents a new approach for the guidance and control of a UGV (Unmanned Ground Vehicle). An obstacle avoidance algorithm was developed using an integrated system involving proportional navigation (PN) and a nonlinear model predictive controller (NMPC). An obstacle avoidance variant of the classical proportional navigation law generates command lateral accelerations to avoid obstacles, while the NMPC is used to track the reference trajectory given by the PN. The NMPC utilizes a lateral vehicle dynamic model. Obstacle avoidance has become a popular area of research for both unmanned aerial vehicles and unmanned ground vehicles. In this application an obstacle avoidance algorithm can take over the control of a vehicle until the obstacle is no longer a threat. The performance of the obstacle avoidance algorithm is evaluated through simulation. Simulation results show a promising approach to conditionally implemented obstacle avoidance.

scholarly journals Biased retro-proportional navigation law for interception of high-speed targets with angular constraint

2014 ◽  
Vol 10 (1) ◽  
pp. 60-65 ◽  
Author(s):  
Liang Yan ◽  
Ji-guang Zhao ◽  
Huai-rong Shen ◽  
Yuan Li
Keyword(s):  
High Speed ◽  
Proportional Navigation ◽  
Proportional Navigation Law

AN ADAPTIVE PROPORTIONAL NAVIGATION GUIDANCE LAW FOR INTERCEPTION OF A MANEUVERING TARGET

2005 ◽  
Vol 29 (2) ◽  
pp. 195-209
Author(s):  
Dany Dionne ◽  
Hannah Michalska
Keyword(s):  
A Priori ◽  
Time Instant ◽  
Proportional Navigation ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Hierarchical Decision ◽  
On Line ◽  
Priori Information ◽  
Miss Distance ◽  
Proportional Navigation Law

A new adaptive proportional navigation law for interception of a maneuvering target is presented. The approach employs a bank of guidance laws and an on-line governor to select the guidance law in effect at each time instant. The members of the bank are the proportional navigation law and a companion law suitable for a target moving with a constant acceleration. The governor is a hierarchical decision rule which uses the outputs from a maneuver detector and the available a-priori information about the expected number of evasive maneuvers. Simulation results demonstrate that the adaptive approach leads to a reduction in the miss distance as compared with cases where only a single non-adaptive guidance law is available.

Influence of Time Delay on Engagement Process Under Proportional Navigation Law

2004 ◽  
Vol 37 (6) ◽  
pp. 433-436
Author(s):  
V.V. Alexandrov ◽  
O.Yu. Cberkasov ◽  
E.S. Manuilovich
Keyword(s):  
Time Delay ◽  
Proportional Navigation ◽  
Engagement Process ◽  
Proportional Navigation Law

Optimal Sliding-Mode Terminal Guidance Law Design of Airborne Boost-Phase Ballistic Missile Interception

2010 ◽  
Vol 40-41 ◽  
pp. 15-20
Author(s):  
Yan Kai Cui ◽  
Li Fu ◽  
Xiao Geng Liang ◽  
Ling Luo
Keyword(s):  
Control Theory ◽  
Sliding Mode ◽  
Ballistic Missile ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Motion Characteristic ◽  
Vehicle Motion ◽  
Proportional Navigation Law ◽  
Terminal Guidance

Aiming at terminal guidance law design of airborne boost-phase ballistic missile interception under acceleration of target without availability, we study on optimal sliding-mode terminal guidance law design of Kinetic-Kill Vehicle. Motion characteristic and infrared characteristic of ballistic missile are analyzed basing on founding ballistic missile boost-phase motion equations. Optimal terminal guidance law of Kinetic-Kill Vehicle is designed basing on undershoot quantity least and energy minimum. Optimal guidance law and augmented proportional navigation law having the same form is proved in theory. Optimal sliding-mode terminal guidance law is designed under acceleration of target without availability, using optimal control theory and sliding-mode control theory. Simulation show that optimal sliding-mode terminal guidance law satisfies required index, reaching the aim to direct hit the target. The correctness and effectiveness of the optimal sliding-mode guidance law are proved.

scholarly journals Combined proportional navigation law for interception of high-speed targets

2014 ◽  
Vol 10 (3) ◽  
pp. 298-303 ◽  
Author(s):  
Yuan Li ◽  
Liang Yan ◽  
Ji-guang Zhao ◽  
Fan Liu ◽  
Tao Wang
Keyword(s):  
High Speed ◽  
Proportional Navigation ◽  
Proportional Navigation Law

A 3D pitch and impact-angle constrained guidance scheme

2018 ◽  
Vol 233 (5) ◽  
pp. 1571-1584
Author(s):  
S Aditya Varma ◽  
Mangal Kothari
Keyword(s):  
Velocity Vector ◽  
Impact Angle ◽  
Simple Approach ◽  
The Body ◽  
Computationally Efficient ◽  
Proportional Navigation ◽  
First Order ◽  
Proportional Navigation Law ◽  
Impact Angles ◽  
3D Problem

In this paper, a guidance scheme for achieving all the possible impact angles constraints for 3D engagements is proposed. For a simple and computationally efficient solution, our approach considers proportional navigation based impact-angle constrained guidance. However, the 3D proportional navigation law cannot be directly applied. This paper proposes a guidance strategy in which a 3D problem is divided into two consecutive 2D problems using a temporary target. The missile switches between the two planes using a temporary target. The paper begins with a simple approach and finally proposes a realistic solution. In all the scenarios considered, the guidance scheme achieves the desired impact angles. To further increase its effectiveness, the paper considers pitch constrained impact-angle law that drives the terminal angle of attack to zero. This ensures that the body axis of the missile will be aligned with its velocity vector at the time of impact. The effectiveness of the proposed guidance schemes are systematically verified through numerical simulations considering both kinematic and realistic models with first-order autopilot lag.

scholarly journals Pursuer Navigation Based on Proportional Navigation and Optimal Information Fusion

Complexity ◽  
2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Shulin Feng ◽  
Zhanxin Li ◽  
Li Liu ◽  
Hongyong Yang ◽  
Yuanhua Yang ◽  
...  
Keyword(s):  
Obstacle Avoidance ◽  
Information Fusion ◽  
Three Dimensional ◽  
Proportional Navigation ◽  
Kinematics Model ◽  
Application Range ◽  
Environment Simulation ◽  
Optimal Information ◽  
Point To Point ◽  
Proportional Navigation Law

Pursuer navigation is proposed based on the three-dimensional proportional navigation law, and this method presents a family of navigation laws resulting in a rich behavior for different parameters. Firstly, the kinematics model for the pursuer and the target is established. Secondly, the proportional navigation law is deduced through the kinematics model. Based on point-to-point navigation, obstacle avoidance is implemented by adjusting the control parameters, and the combination can enrich the application range of obstacle avoidance and guidance laws. Thirdly, information fusion weighted by diagonal matrices is used for decreasing the tracking precision. Finally, simulations are conducted in the MATLAB environment. Simulation results verify the availability of the proposed navigation law.

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