Structural Dynamics and Attitude Control of a Solar Sail Using Tip Vanes

Choi, Mirue; Damaren, Christopher J.

doi:10.2514/1.a33179

Cited by 28 publications

(5 citation statements)

References 30 publications

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“…From Equation (23), it follows that 2V 1 ≤ s 2 . Substituting Equation (25) into Equation (24), and then from Lemma 1, we obtain:…”

Section: Lemma 3 ([50]mentioning

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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“…From Equation (23), it follows that 2V 1 ≤ s 2 . Substituting Equation (25) into Equation (24), and then from Lemma 1, we obtain:…”

Section: Lemma 3 ([50]mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Attitude Tracking Adaptive Control of a Geocentric Polar Displaced Solar Sail

Zhang

2023

Aerospace

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“…Thus great attentions have been paid to the dynamic features of these appendages, for example, natural frequencies, modal damping, modal vectors, coupling coefficients, and so forth, not only during the design stage on the ground (Boni et al, 2017; Ha et al, 2013; Ha et al, 2015), but also during the working stage on the orbit. These features provide significant information for vibration monitoring, control (Chen et al, 2018; Cao and Hang, 2020), and suppression (Choi and Damaren, 2015).…”

Section: Introductionmentioning

confidence: 99%

Configuration optimization of photogrammetry system based on spectral radius for on-orbit measurement

Wang

Pan²,

et al. 2021

Transactions of the Institute of Measurement and Control

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Non-contact optical measurement is a potential approach to on-orbit vibration measurement for flexible appendages, providing dynamic information for spacecraft control system. Binocular photogrammetry system is a practical configuration to achieve this measurement. In this paper, optimization approach and strategy for configuration parameters of this system are raised. Measurement matrix is specially defined to obtain the objective function for the optimization. Successive linear programming algorithm is used for optimization iteration. Transient responses of flexible appendages calculated by finite element model and corresponding images generated by OpenGL help to achieve this simulation-based optimization. The feasibility and effectiveness of the optimization are verified both by numerical study and experiment. Error analysis of the optimal system reveals great improvement in accuracy and robustness after optimization. This optimization is a promising approach to designing the configuration of binocular photogrammetry system and helping to achieve reliable on-orbit dynamic measurement results.

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“…The most common type of gossamer spacecraft which appears in the technical literature is the solar sail, for which a number of attitude control strategies have been proposed. These include reaction wheels, gimballed counterweight systems and the use of solar radiation pressure via controllable tip vanes or sail elements [5][6][7][8]. However, this paper focuses on the use of magnetic control, where Lorentz forces are generated by current carrying elements embedded within the gossamer spacecraft support structure.…”

Section: Introductionmentioning

confidence: 99%