Partial Stabilization Approach to 3-Dimensional Guidance Law Design

2011 ◽  
Vol 133 (6) ◽  
Author(s):  
T. Binazadeh ◽  
M. J. Yazdanpanah
Keyword(s):  
System Dynamics ◽  
The State ◽  
Guidance System ◽  
Missile Guidance ◽  
State Variables ◽  
New Approach ◽  
3 Dimensional ◽  
Guidance Law ◽  
Maneuvering Targets

In this paper, a new approach to design the 3-dimensional missile guidance law, based on partial stabilization, is presented. The approach is based on the classification of the state variables within the guidance system dynamics with respect to their required stabilization properties. The resulting guidance law enables the missile to intercept highly maneuvering targets within a finite interception time. Effectiveness of the proposed guidance law is demonstrated through analysis and simulations.

Robust partial control design for non-linear control systems: a guidance application

2011 ◽  
Vol 226 (2) ◽  
pp. 233-242 ◽  
Author(s):  
T Binazadeh ◽  
M-J Yazdanpanah
Keyword(s):  
Control Systems ◽  
Input Vector ◽  
Guidance System ◽  
Linear Control Systems ◽  
Missile Guidance ◽  
Partial Control ◽  
New Approach ◽  
Guidance Law ◽  
Non Linear ◽  
Guidance Problem

In this paper, a general approach for robust partial stabilization of uncertain non-linear systems is presented. In this approach, the non-linear dynamic system is divided into two subsystems, called the first and the second subsystems. This division is done based on the required stability properties of the system’s states. The reduced input vector (the vector that includes components of the input vector appearing in the first subsystem) is designed to asymptotically stabilize the first subsystem. The proposed scheme is then applied for designing a guidance law as a potential application. Indeed, the paper presents a new approach to the missile guidance problem and shows that asymptotic stability behaviour is not realistic for all states of the guidance system. The effectiveness of the proposed guidance law in interception of manoeuvring targets is demonstrated analytically and through computer simulations.

Fast fixed-time convergent smooth adaptive guidance law with terminal angle constraint for interception of maneuvering targets

2020 ◽  
pp. 095441002096509
Author(s):  
Peng Zhang ◽  
Xiaoyu Zhang
Keyword(s):  
Stability Theory ◽  
Sliding Mode ◽  
Fixed Time ◽  
Guidance System ◽  
Time Stability ◽  
Terminal Sliding Mode ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
System States ◽  
Terminal Angle Constraint

This paper introduces a fast fixed-time guidance law with terminal angle constraint for interception of maneuvering targets, which is based on the structure of singularity-free fast terminal sliding mode and the fixed-time stability theory. Different from the finite-time stability, the fixed-time stability can predefine the maximum stabilization time of system states which is independent on the initial value of system states. Under the proposed guidance law, the guidance system can achieve stabilization within settling time which decides by the parameters of controller. In addition, an adaptive law is proposed which alleviate the chattering of sliding mode and smooths the guidance law. Meanwhile, the proof of the sliding mode manifold and system states fixed-time convergence is given by Lyapunov stability theory. Finally, numerical simulations demonstrate the performance of the proposed guidance law is satisfying.

Design of 3-Dimensional Guidance Law of Missile Based on Discrete Sliding Mode

2013 ◽  
Vol 816-817 ◽  
pp. 976-980
Author(s):  
Nuan Wen ◽  
Zheng Hua Liu ◽  
Le Chang
Keyword(s):  
Discrete Time ◽  
Relative Motion ◽  
Sliding Mode ◽  
Dimensional Space ◽  
Three Dimensional ◽  
New Approach ◽  
3 Dimensional ◽  
Guidance Law ◽  
Guidance Laws ◽  
Three Dimensional Space

In this article, a new approach to design discrete-time sliding-mode guidance laws is presented based on the target-missile relative motion equation in three-dimensional space. This method significantly reduced system chattering and could be easily achieved on engineering. Furthermore, effectiveness of the proposed guidance laws is demonstrated through simulation by comparing with the traditional proportional guidance laws.

Design of Guidance Law with Impact Angle and Impact Time Constraints

2014 ◽  
Vol 945-949 ◽  
pp. 1493-1499 ◽  
Author(s):  
Lin Ping Feng ◽  
Zuo E Fan ◽  
You Gen Zhang
Keyword(s):  
Control Theory ◽  
State Feedback ◽  
Impact Angle ◽  
The State ◽  
Guidance System ◽  
Time Constraints ◽  
Impact Time ◽  
Guidance Law ◽  
Optimal Guidance ◽  
The Impact

In order to achieve the tactical mission of cooperative attack for multi-missiles, in a predetermined direction at a predetermined time, this paper studies the design of guidance law with impact angle and impact time constraints. Firstly, using the optimal control theory, the optimal guidance law is designed to control the impact angle, based the relative motion between missile and target. Then the state feedback guidance law is designed to control the arrival impact time, with the application of feedback linearization control theory. Finally, reference the design idea of two-stage guidance system, the anti-ship missile use two different guidance laws in the process of attacking the target. During the first stage, the state feedback guidance law is used to accurately control the impact time and coarsely control the impact angle. During the second stage, the optimal guidance law is used to accurately control the impact angle. And the correctness and effectiveness of the design method is verified by simulation.

scholarly journals A Fuzzy Guidance System for Rendezvous and Pursuit of Moving Targets

Robotics ◽  
2020 ◽  
Vol 9 (4) ◽  
pp. 110
Author(s):  
Michael Alibani ◽  
Mario Innocenti ◽  
Lorenzo Pollini
Keyword(s):  
Direction Of Arrival ◽  
Guidance System ◽  
Target Velocity ◽  
Control Loops ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Heading Control ◽  
Rendezvous Point ◽  
Takagi Sugeno

This article presents the development of a fuzzy guidance system (FGS) for unmanned aerial vehicles capable of pursuing and performing rendezvous with static and mobile targets. The system is designed to allow the vehicle to approach a maneuvering target from a desired direction of arrival and to terminate the rendezvous at a constant distance from the target. In order to perform a rendezvous with a maneuvering target, the desired direction of arrival is adjusted over time to always approach the target from behind, so that the aircraft and target velocity vectors become aligned. The proposed guidance system assumes the presence of an autopilot and uses a set of Takagi–Sugeno fuzzy controllers to generate the orientation and speed references for the velocity and heading control loops, given the relative position and velocity between the aircraft and the target. The FGS treats the target as a mobile waypoint in a 4-D space (position in 2-dimensions, desired crossing heading and speed) and guides the aircraft on suitable trajectories towards the target. Only when the vehicle is close enough to the rendezvous point, the guidance law is complemented with an additional linear controller to manage the terminal formation keeping phase. The capabilities of the proposed rendezvous-FGS are verified in simulation on both maneuvering and non-maneuvering targets. Finally, experimental results using a multi-rotor aerial system are presented for both fixed and accelerating targets.

Geotechnical Monitoring Of Frozen Earth Foundation By Cone Penetration Test

2019 ◽  
pp. 52-59
Keyword(s):  
The State ◽  
Frozen Soil ◽  
Cone Penetration ◽  
Protection Measures ◽  
New Approach ◽  
Cone Penetration Testing ◽  
Geotechnical Monitoring ◽  
Permafrost Soils ◽  
Engineering Protection

This paper introduces a new approach to the diagnostics of frozen earth foundation condition and some aspects of physical processes, which impacts on properties and condition of permafrost soils. The influence of temperature change in the range from 0 to -10 °C on the state of frozen soil is considered. The significance of the concentration of salts in the pore water in the frozen earth is shown. On the example of recent studies of specialists of the "Fugro Group" on various sites it is revealed that with the help of cone penetration testing it is possible to assess the state of frozen soils and take into account their properties for the design of bases and foundations of structures. The new classification of frozen earth base condition with relation to pile foundation based on the new approach to geotechnical monitoring is proposed that makes it possible to adopt a sound decision on engineering protection measures. The proposed approach makes it possible to diagnose permafrost weakening/degradation under monitored structures at early stages and timely take proper adequate actions on engineering protection measures.

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