Abstract
In this paper, the motion of a smart rigid-flexible satellite considering large deflections for its flexible appendages in general planar motion is modeled. Also, the satellite can experience translational and rotational motions. In addition, its flexible appendages can vibrate arbitrarily in the motion plane. Two control forces perpendicular to each other and one control torque are responsible for controlling the motion of the satellite on the desired trajectories. Also, piezoelectric actuators and sensors suppress vibrations and estimate the transverse displacement of the satellite's flexible appendages, respectively. The coupled ordinary-partial differential equations of motion, equations of the sensors and boundary conditions of the system are obtained using the extended Hamilton's principle. Then, these equations are discretized using the Galerkin method. The discretized equations of motion are a set of coupled nonlinear ordinary differential equations due to the consideration of the large rotation angle of the satellite and large deflections for its flexible appendages. An adaptive super-twisting global nonlinear sliding mode controller is designed to satisfy the control objectives including position and attitude control, as well as suppressing vibrations of the flexible appendages in the presence of uncertainties and external disturbances. Eventually, numerical simulations are presented to validate the proposed dynamic model of a smart flexible satellite and illustrate the effectiveness of the proposed controller.
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The sources of all the data used in this study including properties, parameter values and required data for validation are included within the article.
Abbreviations
- \(A\) :
-
Cross-sectional area (m2)
- AGNSMC:
-
Adaptive global nonlinear sliding mode controller
- ASTGNSMC:
-
Adaptive super-twisting global nonlinear sliding mode controller
- \({\mathbf{C}}({\mathbf{q}},{\dot{\mathbf{q}}})\) :
-
Nonlinear vector including the effects of centrifugal and Coriolis accelerations and flexible appendages equations
- \({\mathbf{C}}_{0} ({\mathbf{q}},{\dot{\mathbf{q}}})\), \(\Delta {\mathbf{C}}({\mathbf{q}},{\dot{\mathbf{q}}})\) :
-
Known and uncertain parts of \({\mathbf{C}}({\mathbf{q}},{\dot{\mathbf{q}}})\)
- CRB:
-
Central rigid body
- \({\mathbf{D}}\) :
-
Lumped uncertainties and disturbances vector
- \(E\) :
-
Young's modulus of the flexible appendages (kg/m/s2)
- \(E_{p}\) :
-
Young's modulus of the piezoelectric patches (kg/m/s2)
- \(E_{z}\) :
-
Electric field of each piezoelectric patch
- \(e_{31}\) :
-
Equivalent piezoelectric coefficient
- \({\mathbf{e}}\), \({\dot{\mathbf{e}}}\), \({\dot{\mathbf{e}}}\) :
-
Position, velocity and acceleration tracking errors
- \(f_{xb}\) , \(f_{yb}\) :
-
Control forces in xb and yb directions (N)
- \({\mathbf{G}}\) :
-
A constant row vector in the sliding surface formula
- \(I\) :
-
Second cross-sectional area moment of inertia (m4)
- \(J\) :
-
Inertia of CRB (kg·m2)
- La:
-
Left flexible appendage
- LAE:
-
Element of the left flexible appendage
- \(l_{a}\) :
-
Length of the flexible appendages (m)
- \(l_{P}\) :
-
Length of the piezoelectric patches (m)
- \(M\) :
-
Mass of CRB (kg)
- \(m\) :
-
The number of generalized coordinates or the number of modes for each flexible appendage
- \({\mathbf{M}}({\mathbf{q}})\) :
-
Inertia matrix
- \({\mathbf{M}}_{0} ({\mathbf{q}})\), \(\Delta {\mathbf{M}}({\mathbf{q}})\) :
-
Known and uncertain parts of the inertia matrix
- \(N\) :
-
Number of piezoelectric patches for each flexible appendage
- \(N_{a}\) , \(N_{s}\) :
-
Number of actuator and sensor piezoelectric patches for each flexible appendage
- \(Q\) :
-
First cross-sectional area moment of inertia (m3)
- \(q_{j} (t)\) :
-
jTh generalized coordinate of the flexible appendages
- \({\mathbf{q}}\), \({\dot{\mathbf{q}}}\), \({\mathbf{\ddot{q}}}\) :
-
A vector which includes position, angular position of the satellite and generalized coordinates of its flexible appendages and its time derivatives
- \({\mathbf{q}}_{d}\), \({\dot{\mathbf{q}}}_{d}\), \({\mathbf{\ddot{q}}}_{d}\) :
-
Desired position, velocity and acceleration trajectories
- \(r\) :
-
Distance from the beginning of the appendages to the center of the CRB
- Ra:
-
Right flexible appendage
- RAE:
-
Element of the right flexible appendage
- \(s\) , \(\dot{s}\) :
-
Sliding surface and its time derivative
- \(T\) :
-
Kinetic energy
- \(t_{p}\) :
-
Thickness of each piezoelectric patch (m)
- \(U\) :
-
Potential energy
- \(u(x,t)\) :
-
Longitudinal displacement of the flexible appendage (m)
- \(V\), \(\dot{V}\) :
-
The Lyapunov function and its time derivative
- \(V_{p}\) :
-
Voltage of each piezoelectric patch (V)
- \({\mathbf{V}}\) :
-
Velocity vector (m/s)
- \(W_{nc}\) :
-
Work done by the control forces and control torque
- \(w(x,t)\) :
-
Lateral displacement of the flexible appendages (m)
- \(XY\) :
-
Inertial reference frame
- \(x_{b} y_{b}\) :
-
Fixed body coordinate system on the CRB
- \(\beta\), \(k\), \(\kappa\), \(\lambda\) :
-
Constant coefficients in the Lyapunov function and proposed controllers
- \(\Gamma\), \(\hat{\Gamma }\) :
-
The upper bound of lumped uncertainties and disturbances, estimated value of Γ
- \(\tilde{\Gamma }\) :
-
Difference between \(\hat{\Gamma }\) and Γ (i.e., \(\hat{\Gamma } - \Gamma\))
- \(\delta\) :
-
The variation operator
- \(\delta_{D}\) :
-
The Dirac delta function
- \(\overline{\delta }\) :
-
Boundary layer width of the proposed controllers
- \(\varepsilon_{{x_{i} }}\) :
-
Longitudinal normal strain for left or right flexible appendage
- \(\varepsilon_{p}\) :
-
Dielectric constant of the piezoelectric material
- \(\theta (t)\) :
-
Rotation angle of the satellite (rad)
- \(\upsilon\) :
-
Adaptive gain of the ASTGNSM controller
- \(\rho\) :
-
Density (kg/m3)
- \(\sigma_{{x_{i} }}\) :
-
Longitudinal normal stress for left or right appendage (N/m2)
- \(\tau\) :
-
Control torque (N.m)
- \({{\varvec{\uptau}}}\) :
-
Control inputs vector
- \({{\varvec{\uptau}}}_{d}\) :
-
External disturbances vector
- \({{\varvec{\uptau}}}_{0}\), \({{\varvec{\uptau}}}_{1}\) :
-
Equivalent and axillary control laws
- \(\phi_{j} (x)\) :
-
jth known independent comparison function of the assumed mode method
- \(\phi_{s} (x)\) :
-
sth known independent comparison function of the Galerkin method
- \(a\) :
-
Flexible appendage
- \(L\) :
-
Left side
- \(R\) :
-
Right side
- LAj , LS j :
-
jth piezoelectric actuator and sensor of the left panel
- LPi :
-
ith piezoelectric patch of the left panel
- PZT, \(p\) :
-
Piezoelectric patch
- RAj , RS j :
-
jth piezoelectric actuator and sensor of the right panel
- RPi :
-
ith piezoelectric patch of the right panel
- \(x_{b}\), \(y_{b}\) :
-
xb And yb axis directions
- elec:
-
Electrical part
- elec-mech:
-
Electromechanical part
- mech:
-
Mechanical part
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Appendices
Appendix A
Applying the variation operator to Eqs. (3) and (10) leads to Eqs. (A.1) and (A.2), respectively.
Appendix B
The relations obtained from integration by parts (B.1) and (B.2) are used in the simplification of Eqs. (A.1) and (A.2) to obtain the equations of motion, the equations of sensors and the boundary conditions of the system.
Appendix C
The relations obtained from integration by parts (C.1) are used in the process of reducing the order of Eqs. (15) and (16) after the discretization process.
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Ghorbani, H., Vatankhah, R. & Farid, M. General planar motion modeling and control of a smart rigid-flexible satellite considering large deflections. Nonlinear Dyn 108, 911–939 (2022). https://doi.org/10.1007/s11071-022-07242-8
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DOI: https://doi.org/10.1007/s11071-022-07242-8