LISA spacecraft maneuver design to estimate tilt-to-length noise during gravitational wave events

Houba, Niklas; Delchambre, Simon; Ziegler, T.; Hechenblaikner, Gerald; Fichter, Walter

doi:10.1103/physrevd.106.022004

Cited by 13 publications

(5 citation statements)

References 19 publications

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“…Gravitational wave spacecraft control system structure CCD and Quadrant photodiodes (differential wavefront sensing, effective after attitude adjustment) [18][19][20] are used to measure the position of the target spacecraft. The description of the OB attitude need to be converted into the description of the spacecraft attitude and MOA turning angle relative to the nominal angle by the coordinate transformation (the relevant method can be found in the literature [21,22]). This is the coordinate transformation 1 after the sensor in the control system of Fig.…”

Section: Figurementioning

confidence: 99%

Decoupling Algorithms for the Gravitational Wave Spacecraft

Wang,

Zhu,

Cui

et al. 2024

CMES

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The gravitational wave spacecraft is a complex multi-input multi-output dynamic system. The gravitational wave detection mission requires the spacecraft to achieve single spacecraft with two laser links and high-precision control. Establishing one spacecraft with two laser links, compared to one spacecraft with a single laser link, requires an upgraded decoupling algorithm for the link establishment. The decoupling algorithm we designed reassigns the degrees of freedom and forces in the control loop to ensure sufficient degrees of freedom for optical axis control. In addressing the distinct dynamic characteristics of different degrees of freedom, a transfer function compensation method is used in the decoupling process to further minimize motion coupling. The open-loop frequency response of the system is obtained through simulation. The upgraded decoupling algorithms effectively reduce the open-loop frequency response by 30 dB. The transfer function compensation method efficiently suppresses the coupling of low-frequency noise.

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Section: Figurementioning

confidence: 99%

Decoupling Algorithms for the Gravitational Wave Spacecraft

Wang,

Zhu,

Cui

et al. 2024

CMES

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“…The phasemeter model of ( 1)-( 4) as well as ( 7)-( 9) will be required for estimating the coupling factors via TDI second generation and TDI-∞, in particular. TTL coupling noise calibration with TDI second generation is covered in [18][19][20][21][22], for example. It should be noted that TTL coupling in LISA's TM interferometers is not calibrated here.…”

Section: Ttl Coupling Noisementioning

confidence: 99%

“…The design matrix M ∈ R 6n×3n is to be filled so that the relations in ( 5) are met and the form of n TTL is derived in the next section. The TDI-∞ observable that considers the realistic LISA setup is given by ( 19) taking into account ( 20) and (22) this time. Equation ( 24) illustrates the shape of M for the simplified case where light travel times are integer multiples of the sample cadence ∆T.…”

Section: Extension Of Time Delay Interferometry Infinity For the Lisa...mentioning

confidence: 99%

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Time-delay interferometry infinity for tilt-to-length noise estimation in LISA

Houba

Delchambre

Hechenblaikner

et al. 2023

Class. Quantum Grav.

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The Laser Interferometer Space Antenna (LISA) mission is a space-borne observatory designed to detect and characterize gravitational wave sources inaccessible to ground-based detectors. The mission relies on laser interferometry to measure changes in space-time. In this context, non-avoidable noise sources within the LISA system, including tilt-to-length coupling, reduce the detector's resolution and complicate achieving the mission's goals unless appropriate mitigation strategies are implemented. This paper applies Time-Delay Interferometry Infinity (TDI-∞) for tilt-to-length noise estimation in LISA and assesses its suitability from the perspective of system identification and calibration for the first time. The recently published TDI-∞ concept indicates a different frequency response within the LISA measurement band compared to the standard methodology of TDI second-generation. Our main contribution is demonstrating the advantages of the TDI-∞ algorithm for tilt-to-length noise calibration in space-borne interferometer constellations. Specifically, we show that this algorithm improves the estimation performance of tilt-to-length noise due to its frequency behavior while requiring less computation time. The reduction in computational effort afforded by the TDI-∞ algorithm accelerates the availability of calibrated TDI data for astrophysical analysis if required by the LISA science community. The improvement in estimation performance underscores the concept's potential to enhance the detector's sensitivity further.

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“…For space-based laser interferometers, such as those in the LISA mission and the LISA Pathfinder (LPF) mission, the tilt-to-length coupling is one of the main error sources. A series of studies on TTL coupling have been carried out for these missions [5][6][7][8][9]. For gravity missions like GRACE-FO, the tilt-to-length coupling in LRI is mainly due to the CM-VP offset as mentioned above.…”

Section: Introductionmentioning

confidence: 99%

Alternative Approach to Tilt-to-Length Coupling Estimation for Laser Ranging Interferometers in Future Gravity Missions

Wang,

Yang,

Jia

et al. 2024

Remote Sensing

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Tilt-to-length coupling, a non-constant systematic error source caused by satellite attitude variations, has been observed in the laser ranging signals of the GRACE Follow-On mission. This error can be corrected by certain calibration maneuvers performed regularly in orbit. In this paper, we introduce an alternative approach to tilt-to-length coupling estimation for a laser ranging interferometer in future gravity missions, using the ranging signals without any specific calibration maneuvers, which allows daily estimation. An analytical model of laser ranging signals is derived. The tilt-to-length estimation is performed under different conditions using the least squares method as well as the simulated data. The pointing angle noise is found to be the most significant limiting factor. When the pointing angle noise is below 0.3μrad/Hz1/2, the RMS of the estimation error is below 4 nm, much better than the tilt-to-length error of GRACE Follow-On. In the case of low pointing angle noise, the estimation error of an under 1.5 m offset between the center of mass and the interferometer reference point is not obviously different from the case with only a 0.5 mm offset, which provides installation flexibility for the laser ranging interferometer.

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LISA spacecraft maneuver design to estimate tilt-to-length noise during gravitational wave events

Cited by 13 publications

References 19 publications

Decoupling Algorithms for the Gravitational Wave Spacecraft

Decoupling Algorithms for the Gravitational Wave Spacecraft

Time-delay interferometry infinity for tilt-to-length noise estimation in LISA

Alternative Approach to Tilt-to-Length Coupling Estimation for Laser Ranging Interferometers in Future Gravity Missions

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