On payload architecture and pointing control strategies for TianQin

TL;DR

This paper evaluates payload architecture and pointing control strategies for the TianQin gravitational-wave mission, confirming the feasibility of using two test masses and rotating assemblies for precise constellation control in orbit.

Contribution

It provides a detailed analysis of control forces, torques, and configuration optimizations supporting the proposed payload architecture for TianQin.

Findings

Test mass control forces are within noise budget limits.

Optimized configuration favors collinear and equidistant test masses.

Control strategies are feasible with current technology constraints.

Abstract

TianQin is a proposed mission for space-based gravitational-wave detection that features a triangular constellation in circular high Earth orbits. The mission entails three drag-free controlled satellites and long-range laser interferometry with stringent beam pointing requirements at remote satellites. For the payload architecture and pointing control strategies, having two test masses per satellite, one for each laser arm, and rotating entire opto-mechanical assemblies (each consisting of a telescope, an optical bench, an inertial sensor, etc.) for constellation breathing angle compensation represent an important option for TianQin. In this paper, we examine its applicability from the perspectives of test mass and satellite control in the science mode, taking into account of perturbed orbits and orbital gravity gradients. First, based on the orbit-attitude coupling relationship, the required electrostatic forces and torques for the test mass suspension control are estimated and found to be sufficiently small for the acceleration noise budget. Further optimization favors configuring the centers of masses of the two test masses collinear and equidistant with the center of mass of the satellite, and slightly offsetting the assembly pivots from the electrode housing centers forward along the sensitive axes. Second, the required control forces and torques on the satellites are calculated, and thrust allocation solutions are found under the constraint of having a flat-top sunshield on the satellite with varying solar angles. The findings give a green light to adopting the two test masses and telescope pointing scheme for TianQin.