Planar Pursuit-Evasion Subjected to Control Energy Constraint

1989 ◽  
Vol 111 (4) ◽  
pp. 661-666
Author(s):  
Y. Yavin ◽  
R. deVilliers
Keyword(s):  
Differential Games ◽  
Vertical Plane ◽  
Variable Speed ◽  
Proportional Navigation ◽  
Optimal Feedback ◽  
Pursuit Evasion ◽  
Gravitational Forces ◽  
Guidance Law ◽  
Pursuit Strategy ◽  
Proportional Navigation Guidance

This work deals with two stochastic planar pursuit-evasion differential games where the pursuer is subject to constraints on its control magnitude and its control energy, whereas the evader is subject only to a magnitude constraint on its control. In the first game the motion of the players is confined to the horizonal plane, while in the second their motion is confined to the vertical plane. In both games, owing to thrust, drag, and gravitational forces, the pursuer has a variable speed. The treatment is concerned mainly with the question of how far a certain type of proportional navigation guidance law is a good approximation to an optimal feedback pursuit strategy.

Co-operative 3D salvo attack of multiple missiles under switching topologies subject to time-varying communication delays

2019 ◽  
Vol 123 (1262) ◽  
pp. 464-483
Author(s):  
X.L. Ai ◽  
L.L. Wang ◽  
Y.C. Shen
Keyword(s):  
Initial Conditions ◽  
Sufficient Conditions ◽  
Time Varying ◽  
Communication Delays ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Switching Topologies ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Proportional Navigation Guidance

ABSTRACTThis study focuses on the co-operative salvo attack problem of multiple missiles against a stationary target under jointly connected switching topologies subject to time-varying communication delays. By carefully exploring certain features of the typical pure proportional navigation guidance law, a two-stage distributed guidance scheme is proposed without any information on time-to-go in this study to realise the simultaneous attack of multiple missiles. In the first guidance stage, a co-operative guidance law is proposed using local neighbouring communications only to achieve consensus on range-to-go and heading error to provide favourable initial conditions for the latter phase, in which switching topologies and time-varying communication delays are taken into account when obtaining sufficient conditions of consensus in terms of linear matrix inequalities. Then, missiles disconnect from each other and are guided individually by the typical pure proportional navigation guidance law with the same navigation gain to realise salvo attack in the second guidance phase. Finally, numerical simulations are carried out to clearly validate the theoretical results.

A generalized design method for three-dimensional guidance laws

2016 ◽  
Vol 231 (1) ◽  
pp. 47-60 ◽  
Author(s):  
Sheng Sun ◽  
Di Zhou ◽  
Jingyang Zhou ◽  
Kok Lay Teo
Keyword(s):  
Lyapunov Function ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Line Of Sight ◽  
Generalized Function ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Target Acceleration ◽  
Guidance Laws ◽  
Proportional Navigation Guidance

The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopilot dynamics as a first-order lag, we design three-dimensional nonlinear guidance laws by using the backstepping technique for three cases: (1) the target does not maneuver; (2) the information of target acceleration can be acquired; and (3) the target acceleration is not available but its bound is known a priori. In the first step of the backstepping design of the control law, there is no need to cancel the nonlinear coupling terms in the three-dimensional guidance dynamics in such way that the final expressions of the proposed guidance laws are significantly simplified. Thus, the proposed nonlinear Lyapunov function for the line-of-sight angular rates is a generalized function for designing three-dimensional guidance laws. Simulation results of a missile interception mission show that the proposed guidance laws are highly effective.

A novel robust proportional navigation guidance law design for missile considering autopilot dynamic

2013 ◽  
Vol 35 (5) ◽  
pp. 703-710 ◽  
Author(s):  
Seyyed Sajjad Moosapour ◽  
Ghasem Alizadeh ◽  
Sohrab Khanmohammadi ◽  
Hamzeh Moosapour
Keyword(s):  
Proportional Navigation ◽  
Guidance Law ◽  
Proportional Navigation Guidance
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