Attitude Dynamics and Control of Liquid Filled Spacecraft with Large Amplitude Fuel Slosh

2016 ◽  
Vol 33 (1) ◽  
pp. 125-136 ◽  
Author(s):  
M.-L. Deng ◽  
B.-Z. Yue
Keyword(s):  
Control Strategy ◽  
Attitude Control ◽  
Large Amplitude ◽  
Lyapunov Theory ◽  
Attitude Dynamics ◽  
Equivalent Mechanical Model ◽  
Attitude Maneuver ◽  
Dynamics And Control ◽  
Fuel Slosh ◽  
And Control

AbstractThis paper focuses on the attitude dynamics and control of liquid filled spacecraft, and the large amplitude fuel slosh dynamics is included by using an improved moving pulsating ball model. The moving pulsating ball model is an equivalent mechanical model that is capable of imitating the whole liquid reorientation process, specifically for the occurrence of large amplitude slosh. This model is improved by incorporating a static capillary force and an effective mass factor. The improvements on this model are validated with previously published experiment results. The spacecraft attitude maneuver is implemented by the momentum transfer technique, and the feedback control strategy is designed based on Lyapunov theory. The effects of liquid viscosity, tank location and desired steady time on sloshing torque and control torque are investigated. The attitude control strategy applied in this paper is proved to be applicable for the coupled liquid filled spacecraft system. The obtained conclusions are useful to aid in liquid filled spacecraft overall design.

Control and Simulation of Spacecraft's Attitude Control Based on Quaternions

2013 ◽  
Vol 380-384 ◽  
pp. 298-301
Author(s):  
Xu Min Song ◽  
Yong Chen
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Control Model ◽  
Dynamic Equations ◽  
Control Law ◽  
Attitude Dynamics ◽  
Attitude Maneuver ◽  
Spacecraft Attitude Dynamics ◽  
Dynamics And Control ◽  
And Control

The large attitude maneuver is studied in this paper. The quarternion form attitude is appilied to avoid the singularity of dynamic equations, and sliding mode control law based on quarternion is desined. The spacecraft attitude dynamics and control model is builted using simulink, which was valided by simulation.

Attitude maneuver control of liquid-filled spacecraft with unknown inertia and disturbances

2019 ◽  
Vol 25 (8) ◽  
pp. 1460-1469 ◽  
Author(s):  
Xiao Juan Song ◽  
Shu Feng Lu
Keyword(s):  
Control Strategy ◽  
Sliding Mode ◽  
Adaptive Sliding Mode Control ◽  
Underactuated System ◽  
Mass Model ◽  
Attitude Maneuver ◽  
Dynamics And Control ◽  
Conservation Of Momentum ◽  
And Control ◽  
The Mathematical Model

The attitude maneuver dynamics and control strategy for a fuel-filled spacecraft with uncertain inertia and external disturbances are studied. The mathematical model of a three-axis stabilized spacecraft is established based on the law of conservation of momentum, and the liquid fuel inside the partially-filled fuel tank is represented by an equivalent two-mode spring-mass model. The adaptive sliding mode control law is designed for this kind of underactuated system, and the Lyapunov stability analysis guarantees that all system trajectories reach and remain on the sliding surface. Then, the multiple mode input shapers are used to suppress the sloshing of the fluid fuel. The numerical results show good performance and effectiveness of the control strategy.

scholarly journals Adaptive Backstepping Attitude Control Law with L2-Gain Performance for Flexible Spacecraft

2019 ◽  
Vol 2019 ◽  
pp. 1-11
Author(s):  
Rui-Qi Dong ◽  
Yu-Yao Wu ◽  
Ying Zhang ◽  
Ai-Guo Wu
Keyword(s):  
Attitude Control ◽  
External Disturbance ◽  
Performance Criterion ◽  
Lyapunov Theory ◽  
Flexible Spacecraft ◽  
Control Law ◽  
Adaptive Backstepping ◽  
Unknown Parameters ◽  
Inertia Matrix ◽  
Attitude Maneuver

In this paper, an observer-based adaptive backstepping attitude maneuver controller (briefly, OBABC) for flexible spacecraft is presented. First, an observer is constructed to estimate the flexible modal variables. Based on the proposed observer, a backstepping control law is presented for the case where the inertia matrix is known. Further, an adaptive law is developed to estimate the unknown parameters of the inertia matrix of the flexible spacecraft. By utilizing Lyapunov theory, the proposed OBABC law can guarantee the asymptotical convergence of the closed-loop system in the presence of the external disturbance, incorporating with the L2-gain performance criterion constraint. Simulation results show that the attitude maneuver can be achieved by the proposed observer-based adaptive backstepping attitude control law.

Dynamics and Control of Electroporation

2008 ◽  
Author(s):  
Susan Basile ◽  
Xiaopeng Zhao ◽  
Mingjun Zhang
Keyword(s):  
Drug Delivery ◽  
Bifurcation Analysis ◽  
Control Strategy ◽  
Control Algorithm ◽  
Pore Radius ◽  
Dynamical Analysis ◽  
Dimensional Model ◽  
Electric Pulses ◽  
Dynamics And Control ◽  
And Control

Electroporation has become an important tool for drug delivery such as gene therapy. The technique uses electric pulses to create transient pores in the cell membrane. To ensure proper uptake of targeted molecules, it is essential to create sufficiently large pores, which remain open long enough. In this work, we explore evolution of the pores using dynamical analysis and control of electroporation based on a simplified two-dimensional model. A detailed bifurcation analysis reveals the existence of saddle-node bifurcations, which induce hysteresis into the system dynamics. The bifurcation analysis also sheds light on the relation between the applied voltage and the pore radius. Based on the dynamics and bifurcation analysis, we design a feedback control algorithm that is able to achieve any desired pore size. Numerical examples demonstrate the control strategy is robust. The control algorithm will improve the operation of electroporation in drug delivery.

scholarly journals The Coupled Orbit-Attitude Dynamics and Control of Electric Sail in Displaced Solar Orbits

2017 ◽  
Vol 2017 ◽  
pp. 1-12 ◽  
Author(s):  
Mingying Huo ◽  
He Liao ◽  
Yanfang Liu ◽  
Naiming Qi
Keyword(s):  
Linear Quadratic Regulator ◽  
Coupled System ◽  
Control Force ◽  
Attitude Dynamics ◽  
Voltage Distribution ◽  
Linear Quadratic ◽  
Displaced Orbit ◽  
Dynamics And Control ◽  
And Control ◽  
Small Torque

Displaced solar orbits for spacecraft propelled by electric sails are investigated. Since the propulsive thrust is induced by the sail attitude, the orbital and attitude dynamics of electric-sail-based spacecraft are coupled and required to be investigated together. However, the coupled dynamics and control of electric sails have not been discussed in most published literatures. In this paper, the equilibrium point of the coupled dynamical system in displaced orbit is obtained, and its stability is analyzed through a linearization. The results of stability analysis show that only some of the orbits are marginally stable. For unstable displaced orbits, linear quadratic regulator is employed to control the coupled attitude-orbit system. Numerical simulations show that the proposed strategy can control the coupled system and a small torque can stabilize both the attitude and orbit. In order to generate the control force and torque, the voltage distribution problem is studied in an optimal framework. The numerical results show that the control force and torque of electric sail can be realized by adjusting the voltage distribution of charged tethers.

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