Development of a Spaceborne GPS Receiver for Precise Relative Navigation of Formation Flying Small Satellites

2012 ◽  
pp. 467-476 ◽  
Author(s):  
Yong Li ◽  
Eamonn Glennon ◽  
Rui Li ◽  
Yuanyuan Jiao ◽  
Andrew G Dempster
Keyword(s):  
Formation Flying ◽  
Relative Navigation ◽  
Gps Receiver ◽  
Small Satellites

Fault-tolerant pose and inertial parameters estimation of an uncooperative spacecraft based on dual vector quaternions

2018 ◽  
Vol 233 (4) ◽  
pp. 1250-1269 ◽  
Author(s):  
Jianping Yuan ◽  
Xianghao Hou ◽  
Chong Sun ◽  
Yu Cheng
Keyword(s):  
Kalman Filter ◽  
Extended Kalman Filter ◽  
Formation Flying ◽  
Fault Tolerant ◽  
Estimation Algorithm ◽  
Parameters Estimation ◽  
Small Satellites ◽  
Dual Vector ◽  
Inertial Parameters ◽  
Space Target

Estimating the parameters of an unknown free-floating tumbling spacecraft is an essential task for the on-orbit servicing missions. This paper proposes a dual vector quaternion based fault-tolerant pose and inertial parameters estimation algorithm of an uncooperative space target using two formation flying small satellites. Firstly, by utilizing the dual vector quaternions to model the kinematics and dynamics of the system, not only the representation of the model is concise and compacted, but also the translational and rotational coupled effects are considered. By using this modeling technique along with the measurements from the on-board vision-based sensors, a dual vector quaternion based extended Kalman filter for each of the two small satellites is designed. Secondly, both of the estimations from each small satellite will be used as inputs of the fault-tolerant algorithm. This algorithm is based on the fault-tolerant federal extended Kalman filter strategy to overcome the estimation errors caused by the faulty measurements, the unknown space environment and the computing errors by setting the appropriate ratios of the two estimations from the first step dual vector quaternions extended Kalman filter. Together with the first and second steps, a novel fault-tolerant dual vector quaternions federal extended Kalman filter using two formation flying small satellites is proposed by this paper to estimate the pose and inertial parameters of a free-floating tumbling space target. By utilizing the estimation algorithm, a good prior knowledge of the unknown space target can be achieved. Finally, the proposed dual vector quaternion federal extended Kalman filter is validated by mathematical simulations to show its robust performances.

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

Sensors ◽  
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.

scholarly journals Formation Flying of small Satellites Using Coulomb Force

2006 ◽  
Vol 7 (1) ◽  
pp. 84-90 ◽  
Author(s):  
Dong-Hun Lee ◽  
Hyun-Jae Lee ◽  
Hyo-Choong Bang
Keyword(s):  
Formation Flying ◽  
Coulomb Force ◽  
Small Satellites

GPS-based relative navigation for the Proba-3 formation flying mission

2013 ◽  
Vol 91 ◽  
pp. 341-355 ◽  
Author(s):  
Jean-Sébastien Ardaens ◽  
Simone D'Amico ◽  
Alexander Cropp
Keyword(s):  
Formation Flying ◽  
Relative Navigation

scholarly journals Closed Relative Trajectories for Formation Flying with Single-Input Control

2012 ◽  
Vol 2012 ◽  
pp. 1-20 ◽  
Author(s):  
Anna Guerman ◽  
Michael Ovchinnikov ◽  
Georgi Smirnov ◽  
Sergey Trofimov
Keyword(s):  
Control System ◽  
Relative Motion ◽  
Attitude Control ◽  
Shape Control ◽  
Formation Flying ◽  
Linear Equations ◽  
Attitude Control System ◽  
Small Satellites ◽  
Orbit Control ◽  
Input Control

We study the problem of formation shape control under the constraints on the thrust direction. Formations composed of small satellites are usually subject to serious limitations for power consumption, mass, and volume of the attitude and orbit control system (AOCS). If the purpose of the formation flying mission does not require precise tracking of a given relative trajectory, AOCS of satellites may be substantially simplified; however, the capacity of AOCS to ensure a bounded or even periodic relative motion has to be studied first. We consider a formation of two satellites; the deputy one is equipped with a passive attitude control system that provides one-axis stabilization and a propulsion system that consists of one or two thrusters oriented along the stabilized axis. The relative motion of the satellites is modeled by the Schweighart-Sedwick linear equations taking into account the effect ofJ2perturbations. We prove that both in the case of passive magnetic attitude stabilization and spin stabilization for all initial relative positions and velocities of satellites there exists a control guaranteeing their periodic relative motion.

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