scholarly journals Design and Simulation of a Flexible Bending Actuator for Solar Sail Attitude Control

Aerospace ◽  
2021 ◽  
Vol 8 (12) ◽  
pp. 372
Author(s):  
Meilin Liu ◽  
Zihao Wang ◽  
Daiki Ikeuchi ◽  
Junyu Fu ◽  
Xiaofeng Wu
Keyword(s):  
Attitude Control ◽  
Controller Design ◽  
Weight Ratio ◽  
Adaptive Controller ◽  
Solar Sail ◽  
Solar Sailing ◽  
Bending Actuator ◽  
Sma Actuator ◽  
And Performance ◽  
Actuator Control

This paper presents the design of a flexible bending actuator using shape memory alloy (SMA) and its integration in attitude control for solar sailing. The SMA actuator has advantages in its power-to-weight ratio and light weight. The bending mechanism and models of the actuator were designed and developed. A neural network based adaptive controller was implemented to control the non-linear nature of the SMA actuator. The actuator control modules were integrated into the solar sail attitude model with a quaternion PD controller that formed a cascade control. The feasibility and performance of the proposed actuator for attitude control were investigated and evaluated, showing that the actuator could generate 1.5 × 10−3 Nm torque which maneuvered a 1600 m2 CubeSat based solar sail by 45° in 14 h. The results demonstrate that the proposed SMA bending actuator can be effectively integrated in attitude control for solar sailing under moderate external disturbances using an appropriate controller design, indicating the potential of a lighter solar sail for future missions.

scholarly journals Neural Networks Approximator Based Robust Adaptive Controller Design of Hypersonic Flight Vehicles Systems Coupled with Stochastic Disturbance and Dynamic Uncertainties

2017 ◽  
Vol 2017 ◽  
pp. 1-10 ◽  
Author(s):  
Guoqiang Zhu ◽  
Lingfang Sun ◽  
Xiuyu Zhang
Keyword(s):  
Controller Design ◽  
Tracking Error ◽  
Adaptive Controller ◽  
Stochastic Disturbance ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Uncertain Dynamics ◽  
Robust Adaptive ◽  
And Performance ◽  
Dynamic Uncertainties

A neural network robust control is proposed for a class of generic hypersonic flight vehicles with uncertain dynamics and stochastic disturbance. Compared with the present schemes of dealing with dynamic uncertainties and stochastic disturbance, the outstanding feature of the proposed scheme is that only one parameter needs to be estimated at each design step, so that the computational burden can be greatly reduced and the designed controller is much simpler. Moreover, by introducing a performance function in controller design, the prespecified transient and performance of tracking error can be guaranteed. It is proved that all signals of closed-loop system are uniformly ultimately bounded. The simulation results are carried out to illustrate effectiveness of the proposed control algorithm.

A Novel Approach for Satellite Attitude Control by Using Solar Sailing

2018 ◽  
Author(s):  
Ni Li ◽  
Paolo Arguelles ◽  
Kevin Chaput ◽  
Stephen L. Kenan ◽  
Salla Kim ◽  
...  
Keyword(s):  
Attitude Control ◽  
European Space Agency ◽  
Solar Sail ◽  
Attitude Control System ◽  
Solar Sailing ◽  
Satellite Attitude ◽  
Space Agency ◽  
Novel Approach ◽  
Satellite Attitude Control ◽  
Orientation System

Solar sailing is a new satellite propulsion technology using radiation pressure exerted by sunlight on a large mirrored surface. Since it does not need propellants, it is increasingly being considered by both the European Space Agency and the National Aeronautics and Space Administration for future science missions. An attitude control system is essential for a sail craft to maintain a desired orientation. IKAROS, launched in 2010, practically proved the possibility of using a solar sail as a propulsion system. However, it also showed the current sail orientation system could change the attitude very slowly, about 1 degree per day. In contrast to the existing single solar sail design, a new distributed four-sail configuration is proposed in this paper and the coordinated motion of the four sails is used to control the attitude pointing of a satellite. The feasibility and efficiency of this proposed design were assessed and concluded that it is possible to steer a CubeSat up to 1 degree in 60 seconds for either the roll or pitch axes.

An anti-wind-up controller design for rocket control systems with control input saturation

1998 ◽  
Vol 212 (4) ◽  
pp. 261-269 ◽  
Author(s):  
J Kim ◽  
H D Choi ◽  
J H Lee ◽  
D S Lee
Keyword(s):  
Attitude Control ◽  
Controller Design ◽  
Input Saturation ◽  
Sounding Rocket ◽  
Feedback Signal ◽  
Control Input ◽  
Attitude Control System ◽  
Two Stage ◽  
The Difference ◽  
Actuator Control

An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.

Composite control system of hybrid-driven mid-altitude airship

2017 ◽  
Vol 122 (1248) ◽  
pp. 173-204
Author(s):  
L. Chen ◽  
Q. Dong ◽  
G. Zhang ◽  
D. Duan
Keyword(s):  
Control System ◽  
Attitude Control ◽  
High Speed ◽  
High Efficiency ◽  
Position Control ◽  
Controller Design ◽  
Weight Ratio ◽  
Composite Control ◽  
Primary Object ◽  
Aerodynamic Surfaces

ABSTRACTIn general, an airship is equipped with hybrid-heterogeneous actuators: the aerodynamic surfaces, the vectored propellers and the buoyant ballonets. The aerodynamic surfaces have high efficiency in attitude control at high speed. However, vectored propellers are also introduced here for attitude control under the special working condition of low airspeed. Due to the lower thrust-to-weight ratio, the composite control of hybrid-heterogeneous actuators is the primary object in controller design for an airship. In composite attitude control, first the attitude moment allocation between aerodynamic control surfaces and vectored propellers is designed according to different dynamic airspeed, to achieve the smooth motion transition from low to high airspeed, then the weighted generalised inverse (WGI) is used to design the reconfigurable actuator allocation among the homogeneous multi-actuators, where the authority of every actuator can be decided by setting the corresponding value of the weight matrix, thus the control law is unchanged under different actuator configurations. Taking the mid-altitude airship as an example, the simulations of position control, trace tracking and altitude control are provided. Simulation results demonstrate that the attitude moments allocation obtains moment distribution between the aerodynamic surfaces and the vectored propellers under different airspeeds; the reconfigurable actuator allocation achieves a good distribution and reconfiguration among homogeneous actuators, thereby enhancing the reliability of the control system.

A Non-Conservative Approach for the Estimation of the Region of Operation of Uncertain Adaptive Control Systems

2015 ◽  
Author(s):  
Mario Luca Fravolini ◽  
Tansel Yucelen ◽  
Antonio Moschitta ◽  
Benjamin Gruenwald
Keyword(s):  
Adaptive Control ◽  
Control Systems ◽  
Lyapunov Functions ◽  
Controller Design ◽  
Tracking Error ◽  
Adaptive Controller ◽  
Adaptive Control Systems ◽  
Short Period ◽  
Conservative Estimation ◽  
And Performance

A challenging problem for Model Reference Adaptive Control Systems is the accurate characterization of the transient response in the presence of large uncertainties. Early prior research by the authors has demonstrated that using a projection mechanism for parameters adaptation the tracking error dynamics behaves as a linear system perturbed by bounded uncertainties. This brings the benefit that the stability analysis can be cast in terms of a convex optimization problem with LMI constraints so that efficient numerical tools can be used for the adaptive controller design. A possible limitation of the approach is that the design is restricted to quadratic control Lyapunov functions that could produce a conservative estimation of the regions of operation for the actual uncertain adaptive system. In this paper this approach is extended to arbitrary high degree polynomial Lyapunov functions by translating the design and performance requirements in terms of Sum of Square (SOS) inequalities and then using SOS optimization tools for the design. In this effort the new SOS approach is introduced and compared with the previous one. A numerical example based on the short period longitudinal dynamics of the F16 aircraft is used to demonstrate the efficacy of the novel method.

Modeling, Design and Analysis of a Robot System for Garment Inspection

2009 ◽  
Author(s):  
E. H. K. Fung ◽  
Long Cheng ◽  
Y. K. Wong ◽  
X. Z. Zhang ◽  
C. W. M. Yuen ◽  
...  
Keyword(s):  
Fuzzy Logic ◽  
Pid Control ◽  
Control Method ◽  
Controller Design ◽  
Adaptive Controller ◽  
Degree Of Freedom ◽  
Fuzzy Pid Control ◽  
Robot System ◽  
Non Linear ◽  
And Performance

This paper presents the design and performance of a robot system that exerts a prescribed tension on fabrics to facilitate the inspection process. The robot system consists of a 3-DOF (degree-of-freedom) robotic hanger and an adaptive controller. In the hanger design, the second link is kept vertical, while that of the previous hanger has a redundant degree of freedom. In addition, this hanger has a shoulder link and a sleeve link that provide convenience for holding the garment. In the controller design, structure friction caused by joints and belt elasticity, which is non-linear in nature, are taken into consideration. Besides, the clothing stiffness also changes non-linearly with extension, which cannot be well handled by simple proportional-integral-derivative (PID) control. Due to these points, the fuzzy logic PID controller is chosen to deal with the non-linear features in this design. After establishing the system, the performance is analyzed by computer simulation, where different conditions are applied to compare fuzzy logic control with conventional PID control. The simulation results show that the fuzzy PID control method is effective in controlling the robot hanger and regulating the garment forces.

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