Design of 3D Guidance Law for Tactical Missiles

Author(s):  
Sikander Kumar Pandit ◽  
Bhavnesh Panchal ◽  
S. E. Talole
Keyword(s):  
2011 ◽  
Vol 317-319 ◽  
pp. 727-733
Author(s):  
Shuang Chun Peng ◽  
Liang Pan ◽  
Tian Jiang Hu ◽  
Lin Cheng Shen

A new three-dimensional (3D) nonlinear guidance law is proposed and developed for bank-to-turn (BTT) with motion coupling. First of all, the 3D guidance model is established. In detail, the line-of-sight (LOS) rate model is established with the vector description method, and the kinematics model is divided into three terms of pitching, swerving and coupling, then by using the twist-based method, the LOS direction changing model is built for designing the guidance law with terminal angular constraints. Secondly, the 3D guidance laws are designed with Lyapunov theory, corresponding to no terminal constraints and terminal constraints, respectively. And finally, the simulation results show that the proposed guidance law can effectively satisfy the guidance precision requirements of BTT missile.


1999 ◽  
Vol 35 (1) ◽  
pp. 72-83 ◽  
Author(s):  
E. Duflos ◽  
P. Penel ◽  
P. Vanheeghe
Keyword(s):  

2012 ◽  
Vol 548 ◽  
pp. 719-723
Author(s):  
Qiang Xing ◽  
Wan Chun Chen ◽  
Bao Yin Ming

In the modern warfare, the trajectory of flight vehicle was required to have the ability to be adjusted in specified shape to increasing the penetration force. This paper deals with the guidance law and data fusion system to impact a target in specified direction for precision guided munitions. A three-dimensional guidance law is designed by combining the optimal guidance law and terminal acceleration tuning methodology. A new configuration of Extended Kalman Filter (EKF) is employed to obtain the range and angle information from INS and infrared seeker to improve the survivability of guidance system in the circumstance with strong electromagnetic interference.


1966 ◽  
Author(s):  
R. JOHNSON ◽  
C. LEONDES ◽  
J. PAYNE

2019 ◽  
Vol 2 (1) ◽  
pp. 43-52
Author(s):  
Alireza Alikhani ◽  
Safa Dehghan M ◽  
Iman Shafieenejad

In this study, satellite formation flying guidance in the presence of under actuation using inter-vehicle Coulomb force is investigated. The Coulomb forces are used to stabilize the formation flying mission. For this purpose, the charge of satellites is determined to create appropriate attraction and repulsion and also, to maintain the distance between satellites. Static Coulomb formation of satellites equations including three satellites in triangular form was developed. Furthermore, the charge value of the Coulomb propulsion system required for such formation was obtained. Considering Under actuation of one of the formation satellites, the fault-tolerance approach is proposed for achieving mission goals. Following this approach, in the first step fault-tolerant guidance law is designed. Accordingly, the obtained results show stationary formation. In the next step, tomaintain the formation shape and dimension, a fault-tolerant control law is designed.


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