Large Angle Reorientation of a Solar Sail Using Gimballed Mass Control

Sperber, Evan; Fu, Bo; Eke, Fidelis O.

doi:10.1007/s40295-016-0085-1

Cited by 11 publications

(5 citation statements)

References 9 publications

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“…where s = s 1 s 2 s 3 T ∈ R 3 ; λ 1 , λ 2 and k denote adjustable slip surface coefficients, Substituting Equations ( 5) and (8) into Equation (11), we obtain:…”

Section: Attitude Tracking Controller Designmentioning

confidence: 99%

“…Polar displaced solar sails are always controlled using three-axis stabilization, whereas a solar sail for triaxial stabilization is generally a square sail with booms [4]. So far, there are three main ways to obtain torque for attitude control studies of solar sails [5,6]: adjusting the center of mass (including sliding masses [7][8][9][10] and gimbaled masses [11][12][13][14]); adjusting the center of pressure (including sail panel translation/rotation [15][16][17][18][19][20][21][22], control vanes [23,24] and reflectivity modulation [25][26][27][28][29][30]); and passive stability design (seeking to stabilize solar sail geometry in the presence of SRP [31,32]).…”

Section: Introductionmentioning

confidence: 99%

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Attitude Tracking Adaptive Control of a Geocentric Polar Displaced Solar Sail

Zhang

2023

Aerospace

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To deal with the attitude tracking control problem of a struck or pierced geocentric polar displaced solar sail (GPDSS), an attitude adaptive control strategy is proposed in this paper under the complex conditions of unknown inertial parameters, external disturbance and input saturation. First, on the basis of a flexible solar sail spacecraft attitude dynamics model with damping terms and vibration initial values, an integrated disturbance term, including inertial parameter uncertainties and external disturbance, is constructed. Second, a radial basis function neural network is applied to design a disturbance estimator with an adaptive law to estimate the integrated disturbance in real time. Then, a sliding-mode controller with fixed-time convergence in the reach phase and finite-time stability in the sliding phase is designed, and stability analysis is conducted by using the Lyapunov theory. Finally, comparative simulations with a linear sliding-mode controller and numerical simulations under various workings are performed. The results show that the designed adaptive control strategy can effectively achieve the attitude tracking control of the GPDSS.

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“…where s = s 1 s 2 s 3 T ∈ R 3 ; λ 1 , λ 2 and k denote adjustable slip surface coefficients, Substituting Equations ( 5) and (8) into Equation (11), we obtain:…”

Section: Attitude Tracking Controller Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Attitude Tracking Adaptive Control of a Geocentric Polar Displaced Solar Sail

Zhang

2023

Aerospace

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“…In terms of attitude control, although there exists a variety of conventional attitude control methods such as reaction wheels, control moment gyroscopes (CMGs) and thrusters, these methods cannot effectively control the attitude of solar sails due to the mass limitation and the required long mission lifetime [1,3,11]. Currently, several methods for attitude control for solar sails exist [17], including the control vane method [18], gimbaled masses method [19,20], sliding masses method, shifted wings method, tilted wings method and billowed wings method for rigid solar sail and sail film with controllable reflectivity method for non-rigid solar sail [3,[21][22][23]. Qu et al also proposed a control method utilizing individually controllable elements to control each sail [24].…”

Section: Introductionmentioning

confidence: 99%

“…This paper presents a flexible bending actuator for solar sail attitude control using the Shape Memory Alloy (SMA). Due to the feature that SMA can recover its original shape after deflection by heating over its transformation temperature, lightweight SMA-based actuators are attractive alternatives for solar sail boom control [19]. Compared with the drawbacks of the conventional actuators for attitude control, SMA-based actuators present a higher power-to-weight ratio due to their much lower weight [25].…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2021

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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.

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“…TVC methods such as moving plates (31) are accompanied by a highly nonlinear behaviour in comparison with the gimbaled thruster. A gimbaled TVC can be also employed for a solar-sail spacecraft (32) . The gimbaled nozzle (gimbaled thruster) can be very useful in preserving weight, simplifying the attitude control system and reducing the requirements of the CM positioning accuracy (3,4,28) .…”

Section: Introductionmentioning

confidence: 99%

Gimbaled-thruster based nonlinear attitude control of a small spacecraft during thrusting manoeuvre

et al. 2017

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In this paper, a novel thrusting manoeuvre control scheme is proposed for a small spacecraft which is based only on the gimbaled thrust vector control (TVC) system. The spacecraft structure is composed of a body and a gimbaled thruster where common attitude control systems such as reaction control system (RCS) and spin stabilisation are not employed. A nonlinear two-body model is considered for the characterisation of the gimbaled-nozzle spacecraft where the gimbal actuator provides the only active control input. The spacecraft attitude is affected by a large exogenous disturbance torque which is generated by a thrust vector misalignment from the centre of mass (CM). To achieve some performance goals in the both transient and steady-state modes, a new control scheme is derived based on the combination of two linear and nonlinear controllers. The proposed method ensures the attitude and thrust vector stability during an impulsive orbital manoeuvre while eliminating and rejecting an exogenous disturbance torque. The numerical simulations illustrate the applicability of this method for using in a small spacecraft and its efficiency in sustained operation.

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Large Angle Reorientation of a Solar Sail Using Gimballed Mass Control

Cited by 11 publications

References 9 publications

Attitude Tracking Adaptive Control of a Geocentric Polar Displaced Solar Sail

Attitude Tracking Adaptive Control of a Geocentric Polar Displaced Solar Sail

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

Gimbaled-thruster based nonlinear attitude control of a small spacecraft during thrusting manoeuvre

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