Attitude Tracking Control of Gravity Gradient Microsatellite in Maneuvering for Space Exploration

Sun, Liang; Zhao, Guowei; Zhang, Nan

doi:10.1007/s12217-018-9663-0

Cited by 4 publications

(5 citation statements)

References 13 publications

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“…Its origin E is the mass center of the Earth. The axis Ex ′ points toward the first Aries point, the axis Ey ′ is in the equatorial plane, and the coordinate system is right‐hand oriented [12].…”

Section: Dynamics Modelmentioning

confidence: 99%

“…Subsequently, let Oxyz be the orbital frame with the origin at the mass center of the microsatellite O . The Oz axis points toward the mass center of the Earth E , the Ox axis is normal to the Oz axis in the orbital plane and points along the direction of increasing polar angle α , and the coordinate system is right‐hand oriented [12].…”

Section: Dynamics Modelmentioning

confidence: 99%

“…Zhou et al presented a sliding mode control law for Earth-pointing satellite with a gravity gradient boom [11]. Sun et al presented an attitude tracking control of gravity gradient microsatellite in maneuvering for space exploration [12]. Hatten and Russell presented a closed-form first-order perturbation solution for the attitude evolution of a triaxial space object in an elliptical orbit [13].…”

Section: Introductionmentioning

confidence: 99%

“…In GPOPS, the node number ∈ [6,12] and the tolerance are less than 10 −6 . First of all, the OL optimal control is adopted, and the external disturbances are not considered.…”

mentioning

confidence: 99%

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Piecewise attitude tracking control of a gravity gradient microsatellite for coplanar orbital transfer

Sun

Zhao

et al. 2021

Asian Journal of Control

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The gravity gradient microsatellite applied to the exploration of space environment is subject to the problem of orbital transfer between two orbits. The contributions of this paper mainly include two aspects: (1) a segmented optimal trajectory and (2) the piecewise terminal tracking control method. In order to achieve orbital transfer between two coplanar orbits, an optimal controller is designed to obtain a segmented optimal trajectory and then it becomes a problem of attitude tracking in different segments. Compared with traditional finite‐time control methods, the adaptive sliding mode control method based on a finite‐time tracking error function is proposed, and the stability and robustness of the system can be guaranteed. A numerical case between two coplanar orbits is studied to validate the effectiveness of the control method.

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Section: Dynamics Modelmentioning

confidence: 99%

Section: Dynamics Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…In GPOPS, the node number ∈ [6,12] and the tolerance are less than 10 −6 . First of all, the OL optimal control is adopted, and the external disturbances are not considered.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Piecewise attitude tracking control of a gravity gradient microsatellite for coplanar orbital transfer

Sun

Zhao

et al. 2021

Asian Journal of Control

Self Cite

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show abstract

“…The latter with 10 cm in diameter and 2.0 m in length will be designed to unfold a 5 kg tip mass. The mass of mast is 150 g/m (without tip mass) [14]. The diameter of the former in one end is 5 cm and the other end is 6 cm, the mass is 182.4 g/m (excluding both 73.2 g end cap and 39.5 g top cap), and the former with 3.0 m in length including 2.0 kg tip mass was successfully deployed in space.…”

Section: Introductionmentioning

confidence: 99%

Design and testing of inflatable gravity-gradient booms in space

Wei

Tan

et al. 2019

CEAS Space J

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Inflatable space structures have many advantages such as small size, high reliability, and low cost. Aiming at a gravitygradient boom for an XY-1 satellite, New Technology Verifying Satellite-1, a slender inflatable boom with low magnetic is presented. First of all, an inflatable boom with six self-supporting thin shells made of carbon and Vectran fiber composite materials on the inner wall was designed for eliminating a magnetic dipole moment and increasing structural stiffness. A precise stowage was designed for a tip mass surrounded by a pair of lightweight honeycomb blocks added on the top of the boom. The stowed boom was tested by sine sweep vibrations with three directions on the ground to verify the reasonable design. The XY-1 satellite which carried the inflatable boom was launched into low orbit. After being stowed state in space for at least 6 months, the inflatable boom orderly unfolded a 2.0 kg tip mass to 3.0 m away in May, 2013. The inflatable boom was successfully deployed from a series of photographs received on the satellite. The results show that this kind of lightweight inflatable boom with self-supporting thin shells can orderly unfold and fulfil the function of gravity-gradient in space for a long time.

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A thrust inversion method for small satellite electric propulsion based on a momentum wheel

Sun,

Zhao,

Huang

et al. 2024

Acta Astronautica

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Attitude Tracking Control of Gravity Gradient Microsatellite in Maneuvering for Space Exploration

Cited by 4 publications

References 13 publications

Piecewise attitude tracking control of a gravity gradient microsatellite for coplanar orbital transfer

Piecewise attitude tracking control of a gravity gradient microsatellite for coplanar orbital transfer

Design and testing of inflatable gravity-gradient booms in space

A thrust inversion method for small satellite electric propulsion based on a momentum wheel

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