Lightweight and high resolution mirrors are needed for future space-based X-ray telescopes to achieve advances in high-energy
astrophysics. The slumped glass mirror technology in development at NASA GSFC aims to build X-ray mirror
modules with an area to mass ratio of ~17 cm2/kg at 1 keV and a resolution of 10 arc-sec Half Power Diameter (HPD) or
better at an affordable cost. As the technology nears the performance requirements, additional engineering effort is
needed to ensure the modules are compatible with space-flight. This paper describes Flight Mirror Assembly (FMA)
designs for several X-ray astrophysics missions studied by NASA and defines generic driving requirements and
subsequent verification tests necessary to advance technology readiness for mission implementation.
The requirement to perform X-ray testing in a horizontal beam, based on the orientation of existing facilities, is
particularly burdensome on the mirror technology, necessitating mechanical over-constraint of the mirror segments and
stiffening of the modules in order to prevent self-weight deformation errors from dominating the measured performance.
This requirement, in turn, drives the mass and complexity of the system while limiting the testable angular resolution.
Design options for a vertical X-ray test facility alleviating these issues are explored. An alternate mirror and module
design using kinematic constraint of the mirror segments, enabled by a vertical test facility, is proposed. The kinematic
mounting concept has significant advantages including potential for higher angular resolution, simplified mirror
integration, and relaxed thermal requirements. However, it presents new challenges including low vibration modes and
imperfections in kinematic constraint. Implementation concepts overcoming these challenges are described along with
preliminary test and analysis results demonstrating the feasibility of kinematically mounting slumped glass mirror