Modeling coupled constellation dynamics for TianQin under self-gravity

TL;DR

This paper develops a comprehensive coupled 9-body dynamic model for TianQin, addressing orbit-attitude interactions caused by self-gravity and control systems, enhancing simulation accuracy for gravitational wave detection missions.

Contribution

It introduces a full 9-body coupled dynamic model for TianQin, accounting for self-gravity and control back-action, which improves upon previous decoupled simulation approaches.

Findings

Self-gravity significantly affects satellite orbit stability.

Minimizing differential self-gravity enhances constellation stability.

High-precision light path simulation confirms decoupling feasibility.

Abstract

TianQin is a dedicated geocentric mission for space-based gravitational wave (GW) detection. Among its core technologies, the drag-free and pointing control subsystem (DFPCS) - consisting of suspension, drag-free and pointing controls - keeps the two test masses (TMs) centered and aligned within their housings while maintaining drag-free conditions and precise telescope pointing along the laser-arm directions. This results in orbit-attitude coupled dynamics for the constellation. The coupling is made more prominent due to satellite self-gravity, which requires compensation from DFPCS and generally makes the satellites deviate from pure free-fall orbits. Previous studies assumed that the orbit and attitude dynamics could be decoupled in numerical simulation, neglecting the back-action from the closed-loop control to orbit propagation. To address this, we develop a comprehensive model that can propagate the full 9-body (6 TMs + 3 satellites, orbits and attitudes) dynamics inter-dependently under the inter-satellite pointing and drag-free conditions. This paper is threefold. First, we reassess the applicability of the two TMs and telescope pointing scheme to TianQin using the new model, and confirm the previous conclusion. Second, to meet the constellation stability requirements, it is found that the DC common self-gravity in the flight direction should be minimized, or kept close for the three satellites. Finally, we simulate the long-range light path between two TMs/satellites with a precision of sub-pm/Hz$^{1/2}$, and the results support the decoupling of the closed-loop dynamics and high-precision orbit for computational efficiency. The method is instrumental to other future missions where the orbit-attitude coupling needs careful consideration.