International Systems Integration on the International Space Station

Over the next few months, the International Space Station (ISS), and human spaceflight in general, will undergo momentous change. The European Columbus and Japanese Kibo Laboratories will be added to the station joining U.S. and Russian elements already on orbit. Columbus, Jules Vernes Automated Transfer Vehicle (ATV) and Kibo Control Centers will soon be joining control centers in the US and Russia in coordinating ISS operations and research. The Canadian Special Purpose Dexterous Manipulator (SPDM) will be performing extra vehicular activities that previously only astronauts on EVA could do, but remotely and with increased safety. This paper will address the integration of these international elements and operations into the ISS, both from hardware and human perspectives. Interoperability of on-orbit systems and ground control centers and their human operators from Europe, Japan, Canada, Russia and the U.S. pose significant and unique challenges. Coordination of logistical support and transportation of crews and cargo is also a major challenge. As we venture out into the cosmos and inhabit the Moon and other planets, it's the systems and operational experience and partnership development on ISS, humanity's orbiting outpost that is making these journeys possible

International Space Station Systems Engineering Case Study

This case study on the International Space Station considers what many believe to have been the ultimate international engineering project in history. The initial plans involved the direct participation of 16 nations, 88 launches and over 160 spacewalks-more space activities than NASA had accomplished prior to the 1993 International Space Station decision. Probably more important was the significant leap in System Engineering (SE) execution that would be required to build and operate a multi-national space station. In a short period of time, NASA and its partners had to work out how to integrate culturally different SE approaches, designs, languages and operational perspectives on risk and safety

International Space Station Systems Engineering Case Study

This case study on the International Space Station considers what many believe to have been the ultimate international engineering project in history. The initial plans involved the direct participation of 16 nations, 88 launches and over 160 spacewalks-more space activities than NASA had accomplished prior to the 1993 International Space Station decision. Probably more important was the significant leap in System Engineering (SE) execution that would be required to build and operate a multi-national space station. In a short period of time, NASA and its partners had to work out how to integrate culturally different SE approaches, designs, languages and operational perspectives on risk and safety

In-Orbit Demonstration of the iSIM-170 Optical Payload Onboard the ISS

iSIM-170 is anoptical payload for Earth Observations with sub-meterresolution in VNIR bands. The payload will be in-orbit-demonstrated at the ISS after a successful launch with the HTV-9 mission by JAXA and afte its installation on the Kibo module occurred on June 11th, 2020. Prior to its flight, iSIM-170 underwent an accelerated development programme culminating in the successful completion of all verifications and reviews. iSIM-170 has been developed by the Spanish company SATLANTIS, in collaboration with the University of Florida, to become the gold standard of imaging payloads for microsatellites. It consists of four integrated components: a binocular diffraction-limited set of telescopes; a high precision, robust and light alloy structure; a set of CMOS array detector units; and a high-performance-reconfigurable on-board image processor. The goal of this in-orbit-demonstration mission consists of commissioning the payload and characterizing the overall instrument’s capabilities, especially its ability to provide a factor ~2-3 improvement on spatial resolution below its diffraction limit design, using our super-resolution algorithms. The payload will be operated for three months to obtain TRL-8 qualification performing uplink and downlink activities managed by JAXA, as intermediary between iSIM-170and SATLANTIS. Preliminary results demonstrating iSIM image quality will be shown at this conference

Mission Analysis and Design for Space Based Inter-Satellite Laser Power Beaming

This research effort develops an interdisciplinary design tool to optimize an orbit for the purpose of wirelessly beaming power from the International Space Stations (ISS) Japanese Experimental Module Exposed Facility (JEM/EF) to a target satellite. For the purpose of this initiative, the target satellite will be referred to as FalconSAT6, a reference to the proposed follow-on satellite to the U.S. Air Force Academy’s (USAFA) FalconSAT5 program. The USAFA FalconSAT program provides cadets an opportunity to design, analyze, build, test and operate small satellites to conduct Department of Defense (DoD) space missions. The tool developed for this research is designed to find an optimal solution balancing the need to maximize the amount of access time between the ISS and FalconSAT6 while minimizing the range between the spacecraft. This tool places mathematical rigor to the problem and determines realistic solutions using current technology. Using this tool allows mission planners to economically and accurately predict the outcome of a proposed wireless power beaming mission

Investigation of a Novel Compact Vibration Isolation System for Space Applications

A novel compact vibration isolation system was designed, built, and tested for the Space Chromotomography Experiment (CTEx) being built by Air Force Institute of Technology (AFIT) researchers. CTEx is a multifunctional experimental imaging chromotomographic spectrometer designed for flight on the International Space Station (ISS) and is sensitive to jitter caused by vibrations both through the support structure as well as those produced on the optical platform by rotating optical components. CTEx demands a compact and lightweight means of vibration isolation and suppression from the ISS structure. Vibration tests conducted on an initial isolator design resulted in changes in the chosen spring and damping material properties but confirmed finite element (FE) model results and showed that the spring geometry meets preliminary design goals. The FE model served as a key tool in evaluating material and spring designs and development of the final drawing sets for fabrication. Research efforts led to a final design which was tested in the final flight configuration. This final configuration proved the potential for a compact means of vibration isolation for space applications

International Space Station External Payload Accommodations/Interfaces

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