【摘要】 在空间引力波探测中，由于轨道力学会引起三角形分布探测系统形状发生周期性的变化，从而产生一个光束前指角。因此，在引力波探测频段内，需要具有pm量级光程扰动的激光指向机构来校正该角度，确保航天器间激光链路的稳定性。针对这一问题，提出一种激光指向机构。通过将一对柔性轴承的理论旋转中心轴线放置于反射镜面，减小由反射镜倾斜引入的光学范围噪声，同时采用双端差分测量闭环控制，有效提高该机构的闭环精度。对该激光指向机构进行理论和仿真分析，结果表明机构活塞位移引起的纵向光程差优于0.007 15 pm/Hz ^1/2，偏转角度为990.69μrad，同时该机构的一阶频率为280.86 Hz，满足发射动力学环境要求。更多还原

【Abstract】 In space gravitational wave detection,the shape of the detection system triangle changes periodically due to orbital motion, which produces a beam point-ahead angle. Within the gravitational wave detection band, the laser pointing mechanism with picometerlevel optical path disturbance is needed to correct the angle and ensure the stability of the spacecraft laser link.To solve this problem, a laser pointing mechanism is proposed in this paper. By placing the theoretical rotation center axis of a pair of flexible bearings on the mirror, the optical range noise introduced by the tilt of the mirror is reduced, and the double-ended differential measurement closed-loop control is used adopted to effectively improve the closed-loop accuracy of the mechanism. Theoretical and simulation analyses of the laser pointing mechanism show that the longitudinal optical path difference caused by the piston displacement of the mechanism is better than 0.007 15 pm/Hz1/2, and the deflection angle is 990.69 μrad. Meanwhile, the first-order frequency of the mechanism is 280.86Hz, which satisfies the launching dynamic environment.更多还原