Session
Technical Session IV: Future Missions 2
Abstract
The Space Development and Test Wing (SDTW) of the Space and Missile Systems Center (SMC) is midway through the development of a new means of spaceflight access for the science and technology (S&T) community. The goal is to make available to the entire space community a standard spacecraft (SC) to payload (PL) interface on which to base PL designs and enable access to space in a shorter timeframe, with less cost and reduced risk. Rather than designing a unique SC for each payload; the STP Standard Interface Vehicle (SIV) is a recurrent SC bus with adaptable interfaces to accommodate a range of payloads. The SC will accommodate one to four payloads totaling up to 60 kg mass and 100 watts orbit average power mounted to an external payload interface plate. The space vehicle is designed for orbits ranging from 400 to 850 km and inclinations of 0 to 98.8 degrees. The program offers a Payload User’s Guide which defines the mechanical, thermal, power and data interfaces to help facilitate PL design and integration. This paper focuses on the PL design criteria to meet the standard interface and the adaptable capabilities of the SC to perform a variety of low earth orbit (LEO) missions.
Presentation Slides
Department of Defense (DoD) Space Test Program (STP) Payload Design Criteria for the STP Standard Interface Vehicle (SIV)
The Space Development and Test Wing (SDTW) of the Space and Missile Systems Center (SMC) is midway through the development of a new means of spaceflight access for the science and technology (S&T) community. The goal is to make available to the entire space community a standard spacecraft (SC) to payload (PL) interface on which to base PL designs and enable access to space in a shorter timeframe, with less cost and reduced risk. Rather than designing a unique SC for each payload; the STP Standard Interface Vehicle (SIV) is a recurrent SC bus with adaptable interfaces to accommodate a range of payloads. The SC will accommodate one to four payloads totaling up to 60 kg mass and 100 watts orbit average power mounted to an external payload interface plate. The space vehicle is designed for orbits ranging from 400 to 850 km and inclinations of 0 to 98.8 degrees. The program offers a Payload User’s Guide which defines the mechanical, thermal, power and data interfaces to help facilitate PL design and integration. This paper focuses on the PL design criteria to meet the standard interface and the adaptable capabilities of the SC to perform a variety of low earth orbit (LEO) missions.
