Formation Control at the Sun-Earth L2 Libration Point Using Solar Radiation Pressure

Shahid, Kamran; Kumar, Krishna Dev

doi:10.2514/1.47342

Cited by 23 publications

(9 citation statements)

References 22 publications

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“…Let us assume that the estimation errorsW,, and are zero. Then settingŴ ¼ W, ¼ , and ¼ in (30), solving for u n , and noting that W and K f are diagonal matrices, one obtains…”

Section: Adaptive Attitude Control Systemmentioning

confidence: 99%

“…Solar sail has been used for the design of a sliding mode control law for the relative position control of a follower satellite at the L 2 sun-Earth/moon collinear libration point. 30 For the control of uncertain nonlinear timevarying systems, the L 1 adaptive control theory has been developed by Hovakimyan and Cao. 31 Unlike the traditional adaptive systems, 32 it uses a low-pass filter for attenuating the high-frequency components of the estimated control signal.…”

Section: Introductionmentioning

confidence: 99%

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Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Lee

Singh

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Based on the [Formula: see text] adaptive control theory, a novel three-axis attitude control system for an axisymmetric spacecraft with uncertain dynamics moving in elliptic orbits, using solar radiation pressure, is derived. The nonaffine-in-control nonlinear spacecraft model includes the gravity gradient torque, the control torque produced by four solar flaps, and external time-varying disturbance moments. For the three-axis attitude control, an [Formula: see text] adaptive control system is designed, which includes a state predictor. A smooth projection algorithm is used to confine the estimated parameters within a desirable set. In the closed-loop system, the designed adaptive law accomplishes three-dimensional attitude control. A special feature of the attitude control system is that it is possible to select large adaptation gains for fast adaptation and to obtain quantifiable performance bounds. Simulation results show that in the closed-loop system, precise roll, yaw, and pitch angle control is accomplished, despite unmodeled nonlinearities, parameter uncertainty, and external disturbance inputs in the model.

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“…Let us assume that the estimation errorsW,, and are zero. Then settingŴ ¼ W, ¼ , and ¼ in (30), solving for u n , and noting that W and K f are diagonal matrices, one obtains…”

Section: Adaptive Attitude Control Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Lee

Singh

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…K. Shahid and K.D. Kumar [25] have also studied the spacecraft formation control at L 2 using solar radiation pressure. Peng et al [20] utilized periodic optimal control to stabilize station and formation keeping of periodic orbits around the libration point with continuous low thrust.…”

Section: Introductionmentioning

confidence: 98%

Linear and nonlinear control strategies for formation and station keeping of spacecrafts within the context of the three body problem

Darvish

Pourtakdoust

Assadian

2015

Aerospace Science and Technology

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“…Therefore, the generation of artificial Lagrange points and formation flying using solar radiation pressure have been studied. [3][4][5][6] Although greater force is obtainable from solar radiation by wider appendages such as solar sails, the force caused by solar radiation pressure cannot be decreased beyond a lower limit determined by the required minimum area of spacecraft for power generation and by other factors. Consequently, the equilibrium point for all practical spacecraft is not the original L2 point.…”

Section: Introductionmentioning

confidence: 99%

Artificial Lagrange Points for Spacecraft with a Tethered Anchor

Ishimura

Kawachi

Tanaka

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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New artificial Lagrange points for spacecraft with a tethered anchor are presented in this paper. The positions of conventional artificial Lagrange points generated by solar radiation pressure are restricted depending on the sail lightness number. Using a tethered anchor, that restriction can be relaxed. Around the L2 point, the new artificial Lagrange points for spacecraft with a tethered anchor are derived based on the circular restricted three-body problem. The dependence of the position of the new artificial Lagrange point on the parameters such as mass ratio and tether's length is investigated for spacecraft with a tethered anchor. The trajectories of spacecraft with and without tethered anchors are calculated numerically. Results show that the tethered anchor can halve the offset of artificial Lagrange points. The effect of tethered anchor on the shift of artificial Lagrange point increases if a tether is long and the mass ratio

show abstract

Formation Control at the Sun-Earth L2 Libration Point Using Solar Radiation Pressure

Cited by 23 publications

References 22 publications

Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Linear and nonlinear control strategies for formation and station keeping of spacecrafts within the context of the three body problem

Artificial Lagrange Points for Spacecraft with a Tethered Anchor

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