Performance-related effects of system level temperature changes can be a key consideration in the design of many types of optical instruments. This is especially true for space-based imagers, which may require complex thermal control systems to maintain alignment of the optical components. Structural-Thermal-Optical-Performance (STOP) analysis is a multi-disciplinary process that can be used to assess the performance of these optical systems when subjected to the expected design environment. This type of analysis can be very time consuming, which makes it difficult to use as a trade study tool early in the project life cycle. In many cases, only one or two iterations can be performed over the course of a project. This limits the design space to best practices since it may be too difficult, or take too long, to test new concepts analytically. In order to overcome this challenge, automation, and a standard procedure for performing these studies is essential. A methodology was developed within the framework of the Comet software tool that captures the basic inputs, outputs, and processes used in most STOP analyses. This resulted in a generic, reusable analysis template that can be used for design trades for a variety of optical systems. The template captures much of the upfront setup such as meshing, boundary conditions, data transfer, naming conventions, and post-processing, and therefore saves time for each subsequent project. A description of the methodology and the analysis template is presented, and results are described for a simple telescope optical system.

Thermal baseplates are sized to limit high temperature excursions when spacecraft electronics modules are generating peak thermal loads. Because of relatively high nominal conductivity, at low loads makeup heat is required to maintain acceptable temperatures, adding weight associated with batteries, heaters, and thermal control. Thermal switches are systems that are capable of switching between high and low effective conductivity. These systems have been used to eliminate the need for makeup heaters; however, because these systems are electronically driven they add weight in the form of batteries and thermal control. Contact-aided Cellular Compliant Mechanisms (C 3 M) employ internal contact mechanisms to enable high effective strains in response to mechanical loads. When active, these contacts also introduce new thermal conductive pathways and, using multiple materials, provide a novel avenue to passive thermal control. This paper is concerned with the development of a structure that exhibits effective variable thermal conductivity through its thickness. The proposed concept consists of compliant cells that deform in response to a temperature gradient, alternately creating and breaking heat conduction paths. Initial results indicate that multiple-material C 3 M devices have the potential to create a large switch ratio between high-conductivity and low-conductivity modes. Complex heat paths through the geometry and thermal characteristc differences between the metal/ceramic pieces help to increase thermal resistance for the low-conductivity mode and generate higher thermal deformation at targeted points. Nomenclature α = coefficient of thermal expansion TCC = thermal contact conductance, W/m 2 K TCR = thermal contact resistance, m 2 K/W k = thermal conductivity, W/mK E = modulus of elasticity q = thermal flux, W/m 2 σ = stress, Pa ΔT = change in temperature R" = thermal resistance, W/K