Optical engineering requirements for the LISA wavefront error budget

Details Optical engineering requirements for the LISA wavefront error budget Optical engineering requirements for the LISA wavefront error budget

Dec 1998

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1998aipc..456..156c&link_type=abstract

The second international laser interferometer space antenna symposium (LISA) on the detection and observation of gravitational w

Other

Gravitational Wave Detectors And Experiments, Gravitational Radiation Detectors, Mass Spectrometers, And Other Instrumentation And Techniques

Scientific paper

Part of LISA's interferometer length error budget is assigned to the wave-front error (WFE) of the optical beam. That is, the aberration of the ideal beam due to the non-ideal effects of the real optical system. These produce interferometer length errors when they are combined with the non-ideal pointing effects (accuracy and stability) of the spacecraft. The aberration effects include fabrication errors such as in mirror surface form and alignment, and added effects in-flight, such as thermo-mechanical deformation. The LISA telescope is the most critical sub-system in this regard, and previously the error budget has been converted into a WFE for the primary mirror, for the case of de-focus aberration alone. Due to in-flight focus correction this effect reduces to that of astigmatic form error, with the result being an estimated requirement for WFE <λ/30. There is ultimately the need for a more comprehensive budget to include all aberration effects, especially since the above WFE requirement is very challenging from an optical engineering viewpoint. It is also appropriate to construct this budget at the same time as the spacecraft design is made, so that critical effects can be allowed for and, if necessary, traded-off in the design. Recent work has realized (a) a ray-trace model of the system to allow the full geometry and its deformation to be analyzed (b) an assessment of the size of the expected deformations, from the spacecraft structural and thermal designs. This model and its WFE predictions will be presented in this paper.

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