Aeroastro, Inc.

Jonathon Miller

Scott A McDermott

Luis Jordan

Thomas Vaneck

Robert A Summers

Simon Morris Shand Weiss

Mark Carl Barton

A spacecraft architecture and accompanying standard allows for the creation of a spacecraft using an assortment of modules that comply with the standard. The standard preferably includes both mechanical and electrical compatibility criteria. To assure physical/mechanical compatibility, the structure of each module is constrained to be compatible with any other compatible module. To minimize the interference among modules, the extent of each module in select dimensions is also constrained. To assure functional compatibility, a common communication format is used to interface with each module, and each public-function module is configured to respond to requests for function capabilities that it can provide to other functions. Each module is preferably designed to provide structural support to the assemblage of modules, and an anchor module is provided or defined for supporting the entire assemblage and coupling the assemblage to other structures, such as a launch vehicle.

Modular spacecraft design architecture

A thermal management system for a spacecraft module includes a baseplate and wall system that is precharacterized to provide a given level of thermal performance regardless of an orientation of the spacecraft relative to a source of solar energy. The system is characterized at a worst-case hot orientation, and at a worst-case cold orientation. The characterization provides a maximum temperature and a minimum temperature of components mounted on the baseplate as a function of the height of the walls. The height of the walls is selected to provide a suitable temperature range for the components, based on the power dissipation of the components. The system is designed to be symmetric, so that this temperature range is assured regardless of the orientation of the spacecraft.

Thermal design for spacecraft modules

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Sterling, VA, United States of America

Jonathon Miller