Optimal Control of an Unmanned Lighter-Than-Air Vehicle Through Way-Point Navigation

2012 ◽  
Author(s):  
Ghassan M. Atmeh ◽  
Kamesh Subbarao
Keyword(s):  
Optimal Control ◽  
Kalman Filter ◽  
Wind Disturbance ◽  
Linear Quadratic ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Air Vehicle ◽  
Optimal Linear ◽  
Guidance Laws ◽  
Proportional Navigation Guidance

The work presented in this paper deals with designing two, optimal, Linear-Quadratic controllers that are capable of navigating an airship through a series of planar waypoints. Two guidance laws are considered, a track-specific guidance law and a proportional navigation guidance law. Each provides commands to their corresponding controller based on vehicle and waypoint positions. A novel implementation of the extended Kalman filter (EKF) provides the required states and wind speed estimates to enhance the performance of the track-specific guidance law in the presence of wind disturbance.

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.

Time-energy optimal guidance strategy for realistic interceptor using pseudospectral method

2020 ◽  
Vol 42 (13) ◽  
pp. 2361-2371 ◽  
Author(s):  
Arunava Banerjee ◽  
Mashuq Nabi ◽  
T. Raghunathan
Keyword(s):  
Optimal Control ◽  
Pseudospectral Method ◽  
Two Dimensional ◽  
Energy Usage ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Legendre Pseudospectral Method ◽  
The Cost ◽  
Guidance Laws

This paper proposes the use of Legendre pseudospectral method (PSM) to obtain the optimal guidance strategy for a two-dimensional interceptor problem. An optimal control problem is formulated that addresses the conflicting objective of minimizing the energy usage, along with minimizing the time taken by missile to capture the target. The PSM-based guidance strategy is compared with other conventional guidance laws such as pure proportional navigation (PPN) guidance law and also evolutionary algorithm inspired differential evolution tuned proportional navigation (DEPN) guidance law. A scheme by which the PSM guidance strategy can be applied online is also included in this paper. The cost function value and the interception time indicates the superiority of the PSM-based guidance strategy.

Study of Proportional Navigation Guidance of Reentry Vehicle Considering Wind Disturbance

2014 ◽  
Vol 490-491 ◽  
pp. 368-374
Author(s):  
Li Jia Zhang ◽  
Yi Xin Huang ◽  
Yu Zhang ◽  
Zhao Ying Li
Keyword(s):  
Wind Disturbance ◽  
Proportional Navigation ◽  
Reentry Vehicle ◽  
Guidance Law ◽  
Terminal Constraints ◽  
Velocity Deviation ◽  
The Impact ◽  
Large Wind ◽  
Terminal Guidance ◽  
Proportional Navigation Guidance

Proportional navigation guidance law is widely applied in the terminal guidance of the reentry vehicle. However, the guidance accuracy of the traditional PNG law is largely affected by the wind disturbance. To improve the impact precision, the proposed method applies a feedback of angular velocity deviation to the traditional PNG law. With the proposed method, the vehicle could satisfy the terminal constraints under large wind disturbance. Also, simulation results validate that the proposed method can well enhance the performance of the vehicle.

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.

Application of optimal control law to laser guided bomb

2018 ◽  
Vol 122 (1251) ◽  
pp. 785-797
Author(s):  
Takieddine Mouada ◽  
Milos V. Pavic ◽  
Bojan M. Pavkovic ◽  
Sasa Z. Zivkovic ◽  
Mirko S. Misljen
Keyword(s):  
Noise Removal ◽  
Control Law ◽  
State Variables ◽  
Linear Quadratic ◽  
State Variable ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Differential Game Theory ◽  
Miss Distance ◽  
Guidance Laws

ABSTRACTThe paper presents a laser guided bomb guidance law based on the linear quadratic differential game theory, where a case of two perpendicular planes with two state variables in each plane has been considered. The Kalman filtering method has been used for noise removal from the measured signals and for estimation of the missing state variable values needed for the optimal guidance law. Optimisation has been conducted with respect to minimisation of the performance index. Comparative analysis of different guidance laws is done. A statistical analysis is performed to obtain the terminal miss distance in dependence on total flight time.

scholarly journals Cooperative Guidance of Seeker-Less Missiles for Precise Hit

2019 ◽  
Vol 2019 ◽  
pp. 1-8
Author(s):  
Jianbo Zhao ◽  
Fenfen Xiong
Keyword(s):  
Linear Quadratic ◽  
Control Cost ◽  
Proportional Navigation ◽  
Two Stage ◽  
Maximum Acceleration ◽  
Linear Quadratic Optimal Control ◽  
Position Information ◽  
Precise Position ◽  
Guidance Law ◽  
Cooperative Guidance

A novel cooperative guidance scenario is proposed that implements fire-and-forget attacks for seeker-less missiles with a cheap finder for stationary targets and without requiring real-time communication among missiles or precise position information. Within the proposed cooperative scenario, the classic leader-follower framework is utilized, and a two-stage cooperative guidance law is derived for the seeker-less missile. Linear-quadratic optimal control and biased proportional navigation guidance (PNG) are employed to develop this two-stage cooperative guidance law to minimize the control cost in the first stage and to reduce the maximum acceleration command in the second stage when the acceleration command is continuous. Simulations and comparisons are conducted that demonstrate the effectiveness and advantages of the proposed guidance law.

scholarly journals Retraction notice

SIMULATION ◽  
2015 ◽  
Vol 91 (8) ◽  
pp. NP1-NP1 ◽  
Keyword(s):  
Differential Game ◽  
Linear Quadratic ◽  
Guidance Control ◽  
Guidance Law ◽  
Retraction Notice ◽  
Guidance Laws

At the request of the Editor(s) and the Publisher and author(s), the following article “Differential Game Guidance Law for a Kinetic Kill Vehicle and Its Simulation” by Xing-Yuan Xu, Xiao-Na Song and Yuan-Li Cai. Simulation, first published June 10, 2015, DOI 10.1177/0037549715588839 . has been retracted. The Editor has judged that the paper plagiarized the following article, and the authors have agreed to their paper being retracted: “Linear Quadratic Guidance Laws for Imposing a Terminal Intercept Angle” by Vitaly Shaferman and Tal Shima, Journal of Guidance, Control, and Dynamics, Vol. 31, No. 5, DOI 10.2514/1.32836.

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