Abstract
The Laser Interferometer Space Antenna (LISA) aims to observe gravitational waves in the mHz regime over its 10-year mission time. LISA will operate laser interferometers between three spacecrafts. Each spacecraft will utilize independent clocks which determine the sampling times of onboard phasemeters to extract the interferometric phases and, ultimately, gravitational wave signals. To suppress limiting laser frequency noise, signals sampled by each phasemeter need to be combined in postprocessing to synthesize virtual equal-arm interferometers. The synthesis in turn requires a synchronization of the independent clocks. This article reports on the experimental verification of a clock synchronization scheme down to LISA performance levels using a hexagonal optical bench. The development of the scheme includes data processing that is expected to be applicable to the real LISA data with minor modifications. Additionally, some noise coupling mechanisms are discussed.
Highlights
The first detection of the gravitational waves (GWs) by the Laser Interferometer Gravitational-Wave Observatory (LIGO) and Virgo in 2015 was the dawn of the gravitational wave astronomy [1]
This article reports on the experimental verification of a clock synchronization scheme down to Laser Interferometer Space Antenna (LISA) performance levels using a hexagonal optical bench
LISA-like frequency noises was added at the lock error point
Summary
The first detection of the gravitational waves (GWs) by the Laser Interferometer Gravitational-Wave Observatory (LIGO) and Virgo in 2015 was the dawn of the gravitational wave astronomy [1]. The target observation band of these ground-based detectors is 1 Hz to 1 kHz, being limited by seismic and gravity gradient noise below 1 Hz. The Laser Interferometer Space Antenna (LISA), being a gravitational-wave detector in space, will avoid the mentioned limitations, targeting the observation band from 0.1 mHz to 1 Hz. The Laser Interferometer Space Antenna (LISA), being a gravitational-wave detector in space, will avoid the mentioned limitations, targeting the observation band from 0.1 mHz to 1 Hz This mission is composed of three spacecraft (SC), forming a triangle with 2.5 million km arm lengths. The microscopic relative displacement of these TMs will be sensed using pinffitffieffiffirffiffisatellite heterodyne laser interferometry with 10 pm= Hz precision per TM pair. GW signals will be detectable in the interferometric phases extracted by digital phasemeters on each SC.
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