Switching LPV control for electromagnetic formation flying on highly elliptical orbit

A Submillimeter-Level Relative Navigation Technology for Spacecraft Formation Flying in Highly Elliptical Orbit

Sensors ◽

10.3390/s20226524 ◽

2020 ◽

Vol 20 (22) ◽

pp. 6524

Author(s):

Xiaoliang Wang ◽

Deren Gong ◽

Yifei Jiang ◽

Qiankun Mo ◽

Zeyu Kang ◽

...

Keyword(s):

Degrees Of Freedom ◽

Formation Flying ◽

Dynamic Models ◽

Elliptical Orbit ◽

Relative Navigation ◽

Estimation Errors ◽

Spacecraft Formation ◽

Spacecraft Formation Flying ◽

Orbit Dynamic ◽

Range Rate

Spacecraft formation flying (SFF) in highly elliptical orbit (HEO) has attracted a great deal of attention in many space exploration applications, while precise guidance, navigation, and control (GNC) technology—especially precise ranging—are the basis of success for such SFF missions. In this paper, we introduce a novel K-band microwave ranging (MWR) equipment for the on-orbit verification of submillimeter-level precise ranging technology in future HEO SFF missions. The ranging technique is a synchronous dual one-way ranging (DOWR) microwave phase accumulation system, which achieved a ranging accuracy of tens of microns in the laboratory environment. The detailed design and development process of the MWR equipment are provided, ranging error sources are analyzed, and relative orbit dynamic models for HEO formation scenes are given with real perturbations considered. Moreover, an adaptive Kalman filter algorithm is introduced for SFF relative navigation design, incorporating process noise uncertainty. The performance of SFF relative navigation while using MWR is tested in a hardware-in-the-loop (HIL) simulation system within a high-precision six degrees of freedom (6-DOF) moving platform. The final range estimation errors from MWR using the adaptive filter were less than 35 μm and 8.5 μm/s for range rate, demonstrating the promising accuracy for future HEO formation mission applications.

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High-Order Analytical Solution of Relative Motion Equation for Satellite Formation Flying in Elliptical Orbit

Proceedings of the 11th International Conference on Informatics in Control, Automation and Robotics ◽

10.5220/0004996902560263 ◽

2014 ◽

Author(s):

Ting Wang ◽

Hanlun Lei ◽

Bo Xu ◽

Jun Guo

Keyword(s):

Analytical Solution ◽

Relative Motion ◽

Formation Flying ◽

High Order ◽

Motion Equation ◽

Elliptical Orbit ◽

Satellite Formation Flying ◽

Satellite Formation

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A new approach to derive a formation flying model in the presence of a perturbing body in inclined elliptical orbit: relative hovering analysis

Astrophysics and Space Science ◽

10.1007/s10509-016-2968-9 ◽

2017 ◽

Vol 362 (2) ◽

Cited By ~ 6

Author(s):

M. Bakhtiari ◽

K. Daneshjou ◽

E. Abbasali

Keyword(s):

Formation Flying ◽

Elliptical Orbit ◽

New Approach

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Linearized Dynamics of Formation Flying Spacecraft on a J2-Perturbed Elliptical Orbit

Journal of Guidance Control and Dynamics ◽

10.2514/1.29438 ◽

2007 ◽

Vol 30 (6) ◽

pp. 1649-1658 ◽

Cited By ~ 45

Author(s):

Jean-Francois Hamel ◽

Jean de Lafontaine

Keyword(s):

Formation Flying ◽

Elliptical Orbit ◽

Formation Flying Spacecraft

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Formation Flying Configuration Design for Highly Elliptical Orbit Satellites

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.246-247.687 ◽

2012 ◽

Vol 246-247 ◽

pp. 687-691

Author(s):

Xiao Kun Zhang ◽

Chao Yuan ◽

Xiao Jing Wu

Keyword(s):

Formation Flying ◽

Design Method ◽

Elliptical Orbit ◽

Configuration Design ◽

Satellite Orbits ◽

Constellation Design

A constellation design method is presented which applies to formation flying configuration of highly elliptical orbit satellites. The design method uses approximately relative kinematics equation in determining initial satellite orbits elements of the constellation with an envisaged formation flying configuration and precisely relative kinematics equation in predicting orbits, and then analyzes the envisaged configuration stability so as to judge whether or not the configuration can be well maintained only by natural disturbing forces, without the need to add any control. The approximately relative kinematics equation is derived from the precisely relative kinematics equation on the basis of two assumptions. The precisely relative kinematics equation can take into account all kinds of disturbing forces in order to analyze the constellation configuration stability in as real dynamics circumstances as possible. In the presented work, the configuration design example of a constellation composed of five surrounding satellites and an objective satellite, all with high eccentricities, are analyzed by simulations. It is seen that the constellation design method effectively solves formation flying configuration for highly elliptical orbit satellites.

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