PROBA-3 mission and the Shadow Position Sensors: Metrology measurement concept and budget

Loreggia, D.; Fineschi, Silvano; Capobianco, Gerardo; Бемпорад, А.; Casti, Marta; Landini, Federico; Nicolini, G.; Zangrilli, L.; Massone, G.; Romoli, M.; Terenzi, L.; Morgante, G.; Belluso, M.; Thizy, Cédric; Galy, Camille; Hermans, Aline; Franco, Pierre; Pirard, Ariane; Rossi, Laurence; Buckley, Steve; Spillane, Raymond; O'Shea, Martin; Galano, Damien; Versluys, Jorg; Hernan, Ken; Accatino, L.

doi:10.1016/j.asr.2020.07.022

Cited by 5 publications

(2 citation statements)

References 18 publications

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“…The longer mission lifetime allows for repeat observations, i.e., an increase in the integration time, thus improving the noise performance and/or the calibration accuracy. Further details on the formation flying satellite subsystems and operations are reported in the literature [26][27][28].…”

Section: Orbit and Operationmentioning

confidence: 99%

GLADE: Gravitational Light-Bending Astrometry Dual-Satellite Experiment

Gai,

Vecchiato,

Riva

et al. 2024

Applied Sciences

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Light bending is one of the classical tests of general relativity and is a crucial aspect to be taken into account for accurate assessments of photon propagation. In particular, high-precision astrometry can constrain theoretical models of gravitation in the weak field limit applicable to the Sun neighborhood. We propose a concept for experimental determination of the light deflection close to the Sun in the 10−7 to 10−8 range, in a modern rendition of the 1919 experiment by Dyson, Eddington and Davidson, using formation flying to generate an artificial long-lasting eclipse. The technology is going to be demonstrated by the forthcoming ESA mission PROBA3. The experimental setup includes two units separated by 150 m and aligned to the mm level: an occulter and a small telescope (0.3 m diameter) with an annular field of view covering a region 0∘.7 from the Sun. The design is compatible with a space weather payload, merging several instruments for observation of the solar corona and environment. We discuss the measurement conditions and the expected performance.

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Section: Orbit and Operationmentioning

confidence: 99%

GLADE: Gravitational Light-Bending Astrometry Dual-Satellite Experiment

Gai,

Vecchiato,

Riva

et al. 2024

Applied Sciences

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“…Some preliminary design parameters of master/slave spacecrafts include: mass: 200 kg/400 kg; reference area: 1.81 m

/3.34 m

; dimensional drag coefficient: 1.29/1.5; dimensional solar radiation pressure coefficient: 1.2/3.27 [ 21 , 22 ].…”

Section: Mission Orbit and Relative Navigation Filtermentioning

confidence: 99%

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

Wang

Gong

Jiang

et al. 2020

Sensors

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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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