Modular, Adaptive, Reconfigurable Systems: Technology for Sustainable, Reliable, Effective, and Affordable Space Exploration

Abstract

Landsat 4 and 5. Earlier versions consisted of standard subsystem "module" or "box" components that cwld be replad witbin a structure based on predefined form hctors. Although the primary motivation for MMS was fastedchqer integration and test, standardization of interfaces, and ease of incorpomting new subsystem technology, it lacked the technology maturity and programmatic "upgrade infrastnactm?e" needed to satisfy varied mission requirements, and Uttimately it lacked user buy-in. cwsequently, it never evolved and was phased out !Such concepts as the Rapid Spacecraft Development Of€ice (RSDO) with its regularly updated atalogue of prequalifkd busses became the preferred method for acquiring satellites. N o t w i h~n ding, over the past 30 yems since MMS inception, technology h a advanced considerably and now modularity can be extended beyond &e traditiod MMS module M box to cover levels of integration, from the chip, card, box, subsystem, to the space system and to the system-ofsystems. This paper will present the MARS architecture, cast within the historical context of MMS. Its application will be highlighted by comparing a state-of-the-art point design vs. a MARS-enabled lunar mission, as a representative robotic case design.

Research on Integrated Interface Design of Small Modular Spacecraf

“…At the beginning of the design, the continuous changes in longterm missions were not foreseen, making the spacecraft unable to adapt to the changes well, let alone repairing malfunctioning systems. In the 1970s, NASA Goddard Space Flight Center proposed the design concept of multi-mission modular spacecraft(MMS) [2], and on this basis, it proposed a modular, adaptive, and reconfigurable system concept (MARS) [3]. The Air Force Research Laboratory of US proposed a plug-and-play system for aerospace and designed a spacecraft PnPSat with plug-and-play functionality [4].…”

Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite

“…From the United States of America, the significant contribution is from Cal Poly and Stanford University, University of Michigan, University of Texas, Air Force Academy, Massachusetts Institute of Technology, Colorado University Boulder, Santa Clara University, tasks, the whole EPS is subdivided into three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM). This modular design approach is not only cost effective because the design, development, and testing costs are shared among these modules but also time saving because of the parallel development approach rather than the classical serial one [13][14][15][16]. In addition, the modular design extensively results in overall cost reduction because the cost is shared among many modules that can be used several times in other missions.…”

Plug-and-play design approach to smart harness for modular small satellites

“…The modules are developed in parallel rather than a typical system developed using serial approach and this results in the reduction of design time. Modular design combines the advantages of standardization with those of customization [2][3][4][5][6]. Upon fabrication, the modules are rapidly combined into a custom-printed circuit board layout and the job of prototype testing can begin.…”