Conference Program of WCICA 2012

WCICA 2012
Book of Abstracts: Friday Sessions
Yao, Pengfei
Chinese Acad. of Sci.
We consider modeling of a nonlinear thin plate and a nonlinear thin
shell under the following assumptions: (a) the materials are nonlinear;
(b) the deflections are small (linear strain displacement relations). For
a plate with a planar middle surface, we consider the bending of the
plate to establish the strain energy, the equilibrium equations, and the
motion equations. For a shell with a curved middle surface in R 3 , we
derive a nonlinear model where a deformation in three-dimensions is
concerned.
◮ FrA04-6 15:10–15:30
Multiple Models Adaptive Control Based on Cluster-Optimization for a
Class of Nonlinear System, pp.1367–1371
Huang, Miao
WANG, Xin
Wang, Zhenlei
Qian, Feng
East China Univ. of Sci. & Tech.
Shanghai Jiao Tong Univ.
East China Univ. of Sci. & Tech.
East China Univ. of Sci. & Tech.
For a class of nonlinear discrete time system with fast time-varying
or jumping parameters, a multiple models adaptive controller (MMAC)
based on cluster-optimization is proposed. Based on the input-output
data, the sample data are classified into several clusters by the fuzzy
kernel clustering adaptive algorithm. Then the local models can be constructed
corresponding clusters by the least square method. To improve
the transient response during the change of the working points, besides
the distance, the directional derivative of system is computed also. It is
utilized to identify the system trend of changing working point. Before
the changing occurs, new weighted models are developed by the corresponding
local models, indicated by the system directional derivative.
Meanwhile the distance between the data and the centre of clusters are
used to find the weighted coefficients. So a better approach ability can
be got than that designed only by the distance. The simulation results
show that the proposed controller is superior to that of the conventional
multiple models controller.
FrA05 13:30–15:30 Room 203E
Control Theory (I)
Chair: ZHOU, Shiliang
North China Electric Power Univ.
Co-Chair: ROY, TUSHAR KANTI UNSW, Canberra, ACT 2600
◮ FrA05-1 13:30–13:50
Robust Maneuver Control with Disturbance Attenuation for Flexible S-
pacecraft, pp.1269–1275
ZHOU, Duan
Guo, Yu
Chen, Qingwei
Hu, Weili
Nanjing Univ. of Sci. & Tech.
Nanjing Univ. of Sci. & Tech.
Nanjing Univ. of Sci. & Tech.
Nanjing Univ. of Sci. &Tech.
Disturbance attenuation and model parametric uncertainties must be
solved in large angle attitude maneuvering control for flexible spacecraft.
A robust attitude maneuvering controller with disturbance attenuation
inspired by the model of cell membrane discharge is proposed for
flexible spacecraft, considering external disturbances and parametric
uncertainties. The control strategy is designed to make the closed-loop
system to be able to suppress interference and to be globally asymptotically
stable. Also, it is considered particularly to solve the problem
of jump of control quantity which will make the pointing accuracy and
stability become poor in large angle maneuver of flexible spacecraft.
When the external disturbances and the estimate errors of parametric
uncertainties are bounded, the ability of disturbance attenuation and
the stability of the controller proposed are proved through Lyapunov
analysis. The simulation results demonstrate the effectiveness of the
robust controller proposed.
◮ FrA05-2 13:50–14:10
Hover Flight Control of a Small Helicopter Using Robust Backstepping
and PID , pp.1688–1693
ROY, TUSHAR KANTI UNSW, Canberra, ACT 2600
In this paper, a robust control strategy applying on a small helicopter
is proposed. The controller is designed using the backstepping approach
based on Lyapunov function. In control design, a hierarchical
inner-outer loop based structure is proposed to control the hover flight
in the presence of external wind gusts. The outer loop employs robust
backstepping controller to control the translational trajectory, while the
inner loop (attitude control) controller is designed by means of PID controller
that allow the stabilization of the attitude of a small helicopter.
This new method combines the advantages of both robust backstepping
and PID, particularly it is simple and easy to implement and tune
in future real flight test. Finally, a computer simulation is conducted to
show the hover flight control performance of the proposed controller in
a gusty environment.
◮ FrA05-3 14:10–14:30
Research on Robust Control Allocation for the Advanced Configuration
Aircraft, pp.1722–1726
Zou, Jingfeng
Yang, Lingyu
Zhang, Jing
Shen, Gongzhang
beihang Univ.
Beijing Univ. of Aeronautics & Astronautics
Beihang Univ.
Beijing Univ. of Aeronautics & Astronautics
Abstract: The accuracy of control allocation algorithms rely on control
effectiveness matrix. To address this issue, this paper focuses on the
robustness of control allocation. Several existing robust control allocation
algorithms are analyzed at first. Then performance evaluation
criteria for robust control allocation, which are designed for flight control,
are proposed based on performance requirements of flight control
system. Comparisons among existing robust control allocation algorithms
are conducted via simulations. And robustness of existing robust
control allocation algorithms are evaluated according to the proposed
robustness evaluation criteria.
◮ FrA05-4 14:30–14:50
Low Order Structured Weight Optimization for H∞Loop Shaping Design
Procedure, pp.2257–2262
Liu, Yuyan
ZHOU, Shiliang
North China Electric Power Univ.
North China Electric Power Univ.
A low order structured weight optimization algorithm for H∞loop shaping
design procedure is proposed, which can be used for single input
single output plant H∞controller design. This work is build on the
method given by Lanzon[3], where special structured decision variables
are defined according to low order structured weight, and additional linear
matrix inequalities are given which place constraints on parameters
of weight. Instead of fit transfer function using complex cepstrum algorithm,
parameters of weight can be derived directly by solving corresponding
LMIs. Numerical example shows that lower computational
cost is spent and desired control performance is obtained using the
proposed approach.
◮ FrA05-5 14:50–15:10
Research on Terminal Guidance Method in Glide Attack Phase of Aerodynamic
Missile, pp.1150–1155
Zhang, Zhi-kai
Guo, Qing
Univ. of Electronic Sci. & Tech. of China
Univ. of Electronic Sci. & Tech. of China
On basis of trimming glide and horizontal flight modes, the Miniderivative
linearization model of aeromarine aerodynamic missile is
constructed. As the mathematical model of missile plant, inertia component
and rudder are combined, the PID parameters and lead/lag correction
network is designed by frequency domain method to ensure the
stability margin of attitude inner loop and the maneuverability of outer
loop. The ballistic obliquity and height of missile are controlled in longitudinal
plane. At the same time, the anticipant overload command is
gained by revised proportional navigation law in lateral plane. Simulation
results show that this terminal guidance method in glide attack
phase can realize efficiently aeromarine horizontal flight in longitudinal
plane and tracking target warship quickly with little miss distance.
◮ FrA05-6 15:10–15:30
Robust Diving Control of AUV with L2 Disturbance Attenuation Method,
pp.1356–1360
WANG, Hongjian
Chen, Ziyin
Harbin Engineering Univ.
Harbin Engineering Univ.
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