Details
| Originalsprache | Englisch |
|---|---|
| Aufsatznummer | 082001 |
| Seitenumfang | 14 |
| Fachzeitschrift | Physical Review D |
| Jahrgang | 99 |
| Ausgabenummer | 8 |
| Publikationsstatus | Veröffentlicht - 15 Apr. 2019 |
Abstract
The science operations of the LISA Pathfinder mission have demonstrated the feasibility of sub-femto-g free fall of macroscopic test masses necessary to build a gravitational wave observatory in space such as LISA. While the main focus of interest, i.e., the optical axis or the x-axis, has been extensively studied, it is also of great importance to evaluate the stability of the spacecraft with respect to all the other degrees of freedom (d.o.f.). The current paper is dedicated to such a study: the exhaustive and quantitative evaluation of the imperfections and dynamical effects that impact the stability with respect to its local geodesic. A model of the complete closed-loop system provides a comprehensive understanding of each component of the in-loop coordinates spectral density. As will be presented, this model gives very good agreement with LISA Pathfinder flight data. It allows one to identify the noise source at the origin and the physical phenomena underlying the couplings. From this, the stability performance of the spacecraft with respect to its geodesic is extracted as a function of frequency. Close to 1 mHz, the stability of the spacecraft on the XSC, YSC and ZSC d.o.f. is shown to be of the order of 5.0×10-15 m s-2 Hz-1/2 for X, 6.0×10-14 m s-2 Hz-1/2 for Y, and 4.0×10-14 m s-2 Hz-1/2 for Z. For the angular d.o.f., the values are of the order of 3×10-12 rad s-2 Hz-1/2 for ΘSC, 5×10-13 rad s-2 Hz-1/2 for HSC, and 3×10-13 rad s-2 Hz-1/2 for ΦSC. Below 1 mHz, however, the stability performances are worsened significantly by the effect of the star tracker noise on the closed-loop system. It is worth noting that LISA is expected to be spared from such concerns, as differential wave-front sensing, an attitude sensor system of much higher precision, will be utilized for attitude control.
ASJC Scopus Sachgebiete
- Physik und Astronomie (insg.)
- Physik und Astronomie (sonstige)
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in: Physical Review D, Jahrgang 99, Nr. 8, 082001, 15.04.2019.
Publikation: Beitrag in Fachzeitschrift › Artikel › Forschung
}
TY - JOUR
T1 - LISA Pathfinder platform stability and drag-free performance
AU - LISA Pathfinder Collaboration
AU - Armano, M.
AU - Audley, H.
AU - Baird, J.
AU - Binetruy, P.
AU - Born, M.
AU - Bortoluzzi, D.
AU - Castelli, E.
AU - Cavalleri, A.
AU - Cesarini, A.
AU - Cruise, A. M.
AU - Danzmann, K.
AU - De Deus Silva, M.
AU - Diepholz, I.
AU - Dixon, G.
AU - Dolesi, R.
AU - Ferraioli, L.
AU - Ferroni, V.
AU - Fitzsimons, E. D.
AU - Freschi, M.
AU - Gesa, L.
AU - Gibert, F.
AU - Giardini, D.
AU - Giusteri, R.
AU - Grimani, C.
AU - Grzymisch, J.
AU - Harrison, I.
AU - Heinzel, G.
AU - Hewitson, M.
AU - Hollington, D.
AU - Hoyland, D.
AU - Hueller, M.
AU - Inchauspé, H.
AU - Jennrich, O.
AU - Jetzer, P.
AU - Karnesis, N.
AU - Kaune, B.
AU - Korsakova, N.
AU - Killow, C. J.
AU - Lobo, J. A.
AU - Lloro, I.
AU - Liu, L.
AU - López-zaragoza, J. P.
AU - Maarschalkerweerd, R.
AU - Mance, D.
AU - Meshksar, N.
AU - Martín, V.
AU - Martin-polo, L.
AU - Martino, J.
AU - Martin-porqueras, F.
AU - Mateos, I.
AU - Nofrarias, Miguel
AU - Paczkowski, S.
AU - Perreur-Lloyd, M.
AU - Petiteau, A.
AU - Pivato, P.
AU - Plagnol, E.
AU - Ramos-Castro, J.
AU - Reiche, Jens
AU - Robertson, D. I.
AU - Rivas, F.
AU - Russano, G.
AU - Slutsky, J.
AU - Sopuerta, Carlos F.
AU - Sumner, Tim J.
AU - Texier, D.
AU - Thorpe, J. I.
AU - Vetrugno, D.
AU - Vitale, S.
AU - Wanner, Gudrun
AU - Ward, H.
AU - Wass, P. J.
AU - Weber, W. J.
AU - Wissel, L.
AU - Wittchen, A.
AU - Zweifel, Philipp
N1 - Funding Information: This work has been made possible by the LISA Pathfinder mission, which is part of the space-science program of the European Space Agency. The French contribution has been supported by the CNES (Accord spécifique de projet CNES 1316634/CNRS 103747), the CNRS, the Observatoire de Paris and the University Paris-Diderot. E. P. and H. I. would also like to acknowledge the financial support of the UnivEarthS Labex program at Sorbonne Paris Cité (Grants No. ANR-10-LABX-0023 and No. ANR-11-IDEX-0005-02). The Albert-Einstein-Institut acknowledges the support of the German Space Agency, DLR. The work is supported by the Federal Ministry for Economic Affairs and Energy based on a resolution of the German Bundestag (Grants No. FKZ 50OQ0501 and No. FKZ 50OQ1601). The Italian contribution has been supported by Agenzia Spaziale Italiana and Istituto Nazionale di Fisica Nucleare. The Spanish contribution has been supported by Contracts No. AYA2010-15709 (MICINN), No. ESP2013-47637-P, and No. ESP2015-67234-P (MINECO). M. N. acknowledges support from Fundacion General CSIC (Programa ComFuturo). F. R. acknowledges a FPI contract (MINECO). The Swiss contribution acknowledges the support of the Swiss Space Office (SSO) via the PRODEX Programme of ESA. L. F. is supported by the Swiss National Science Foundation. The U.K. groups wish to acknowledge support from the United Kingdom Space Agency (UKSA), the University of Glasgow, the University of Birmingham, Imperial College, and the Scottish Universities Physics Alliance (SUPA). J. I. T. and J. S. acknowledge the support of the U.S. National Aeronautics and Space Administration (NASA).
PY - 2019/4/15
Y1 - 2019/4/15
N2 - The science operations of the LISA Pathfinder mission have demonstrated the feasibility of sub-femto-g free fall of macroscopic test masses necessary to build a gravitational wave observatory in space such as LISA. While the main focus of interest, i.e., the optical axis or the x-axis, has been extensively studied, it is also of great importance to evaluate the stability of the spacecraft with respect to all the other degrees of freedom (d.o.f.). The current paper is dedicated to such a study: the exhaustive and quantitative evaluation of the imperfections and dynamical effects that impact the stability with respect to its local geodesic. A model of the complete closed-loop system provides a comprehensive understanding of each component of the in-loop coordinates spectral density. As will be presented, this model gives very good agreement with LISA Pathfinder flight data. It allows one to identify the noise source at the origin and the physical phenomena underlying the couplings. From this, the stability performance of the spacecraft with respect to its geodesic is extracted as a function of frequency. Close to 1 mHz, the stability of the spacecraft on the XSC, YSC and ZSC d.o.f. is shown to be of the order of 5.0×10-15 m s-2 Hz-1/2 for X, 6.0×10-14 m s-2 Hz-1/2 for Y, and 4.0×10-14 m s-2 Hz-1/2 for Z. For the angular d.o.f., the values are of the order of 3×10-12 rad s-2 Hz-1/2 for ΘSC, 5×10-13 rad s-2 Hz-1/2 for HSC, and 3×10-13 rad s-2 Hz-1/2 for ΦSC. Below 1 mHz, however, the stability performances are worsened significantly by the effect of the star tracker noise on the closed-loop system. It is worth noting that LISA is expected to be spared from such concerns, as differential wave-front sensing, an attitude sensor system of much higher precision, will be utilized for attitude control.
AB - The science operations of the LISA Pathfinder mission have demonstrated the feasibility of sub-femto-g free fall of macroscopic test masses necessary to build a gravitational wave observatory in space such as LISA. While the main focus of interest, i.e., the optical axis or the x-axis, has been extensively studied, it is also of great importance to evaluate the stability of the spacecraft with respect to all the other degrees of freedom (d.o.f.). The current paper is dedicated to such a study: the exhaustive and quantitative evaluation of the imperfections and dynamical effects that impact the stability with respect to its local geodesic. A model of the complete closed-loop system provides a comprehensive understanding of each component of the in-loop coordinates spectral density. As will be presented, this model gives very good agreement with LISA Pathfinder flight data. It allows one to identify the noise source at the origin and the physical phenomena underlying the couplings. From this, the stability performance of the spacecraft with respect to its geodesic is extracted as a function of frequency. Close to 1 mHz, the stability of the spacecraft on the XSC, YSC and ZSC d.o.f. is shown to be of the order of 5.0×10-15 m s-2 Hz-1/2 for X, 6.0×10-14 m s-2 Hz-1/2 for Y, and 4.0×10-14 m s-2 Hz-1/2 for Z. For the angular d.o.f., the values are of the order of 3×10-12 rad s-2 Hz-1/2 for ΘSC, 5×10-13 rad s-2 Hz-1/2 for HSC, and 3×10-13 rad s-2 Hz-1/2 for ΦSC. Below 1 mHz, however, the stability performances are worsened significantly by the effect of the star tracker noise on the closed-loop system. It is worth noting that LISA is expected to be spared from such concerns, as differential wave-front sensing, an attitude sensor system of much higher precision, will be utilized for attitude control.
UR - http://www.scopus.com/inward/record.url?scp=85065086779&partnerID=8YFLogxK
U2 - 10.1103/PhysRevD.99.082001
DO - 10.1103/PhysRevD.99.082001
M3 - Article
VL - 99
JO - Physical Review D
JF - Physical Review D
SN - 2470-0010
IS - 8
M1 - 082001
ER -