Preliminary Jitter Stability Results for the Large UV/Optical/Infrared (LUVOIR) Surveyor Concept Using a Non-Contact Vibration Isolation and Precision Pointing System

Sacks, Lia W ; Blaurock, Carl ; Dewell, Larry D ; Tajdaran, Kiarash ; Liu, Kuo-Chai ; Collins, Christine ; West, Garrett J ; Ha, Kong Q ; Bolcar, Matthew R ; Crooke, Julie A(NASA Goddard Space Flight Center, Greenbelt, MD, United States)

关键词: DYNAMIC STABILITY;    INFRARED RADIATION;    LINE OF SIGHT;    OPTICAL EQUIPMENT;    POINTING CONTROL SYSTEMS;    SPACECRAFT STRUCTURES;    TELESCOPES;    ULTRAVIOLET SPECTRA;    WAVE FRONTS;    ATTITUDE CONTROL;    CONTROL MOMENT GYROSCOPES;    FINITE ELEMENT METHOD;    ISOLATION;    MATHEMATICAL MODELS;    SYSTEMS ENGINEERING;    VIBRATION ISOLATORS;   

RP-ID  :  GSFC-E-DAA-TN57171-1

学科分类：地球科学(综合)

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来源: NASA Technical Reports Server

【 摘 要 】

The need for high payload dynamic stability and ultra-stable mechanical systems is an overarching technology need for large space telescopes such as the Large Ultraviolet / Optical / Infrared (LUVOIR) Surveyor concept. The LUVOIR concept includes a 15-meter-diameter segmented-aperture telescope with a suite of serviceable instruments operating over a range of wavelengths between 100nm to 2.5 um. Wavefront error (WFE) stability of less than 10 picometers RMS of uncorrected system WFE per wavefront control step represents a drastic performance improvement over current space-based telescopes being fielded. Through the utilization of an isolation architecture that involves no mechanical contact between the telescope and the host spacecraft structure, a system design is realized that maximizes the telescope dynamic stability performance without driving stringent technology requirements on spacecraft structure, sensors or actuators. Through analysis of the LUVOIR finite element model and linear optical model, the wavefront error and Line-Of-Sight (LOS) jitter performance is discussed in this paper when using the Vibration Isolation and Precision Pointing System (VIPPS) being developed cooperatively with Lockheed Martin in addition to a multi-loop control architecture. The multi-loop control architecture consists of the spacecraft Attitude Control System (ACS), VIPPS, and a Fast Steering Mirror on the instrument. While the baseline attitude control device for LUVOIR is a set of Control Moment Gyroscopes (CMGs), Reaction Wheel Assembly (RWA) disturbance contribution to wavefront error stability and LOS stability are presented to give preliminary results in this paper. CMG disturbance will be explored in further work to be completed.