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• W2316230247 abstract "The Naval Research Laboratory (NRL) has developed a new bipropellant Upper Stage providing orbit transfer propulsion capabilities from a Delta II launch vehicle. This bipropellant stage utilizes a pair of Composite Overwrapped Pressure Vessels (COPV) to store helium for pressurization of the Upper Stage fuel and oxidizer propellant tanks. A systems engineering trade study was performed to determine the size requirements of the helium tanks followed by competitive vendor selection and subsequent tank development and qualification program. This paper discusses the helium tank sizing analysis and documents details of the COPV design and qualification testing effort. Additionally, spacecraft installation interfaces, a tank pressure hazard analysis, and on-orbit temperature and pressure performance are summarized and presented. Program description. The Naval Research Laboratory (NRL) is the corporate research laboratory for the United States Navy and Marine Corps and conducts a broad program of scientific research, technology and advanced development. The NRL, sponsored by the Defense Advanced Research Projects Agency (DARPA), developed the Upper Stage (US) for the Microsatellite Technology Experiment (MiTEx) program by drawing on its corporate experience building and operating spacecraft. The Upper Stage provided the orbit transfer propulsion for the MiTEx microsatellites and was launched on a Delta II in June of 2006. NRL personnel performed a series of mission analyses and trade studies that showed that an earth storable liquid bipropellant system would best satisfy the MiTEx orbital maneuvering requirements. A constant feed pressure is required to optimize bipropellant engine performance; therefore the propulsion subsystem design includes two Composite Overwrapped Pressure Vessels (COPV) to store helium pressurant. ARDE, Inc was selected as the COPV contractor after a competitive procurement. ARDE developed a tank design to meet the NRL requirements, and conducted extensive tests both to qualify the design and to provide thermal – helium expulsion data to support NRL mission planning needs. Mission sizing and blowdown. NRL personnel performed a series of analyses to support the COPV procurement. These included parametric studies, mission requirements flowdown, budget allocations to the various components including the COPV, and packaging studies. The key requirement addressed in these analyses was the pressure remaining in the COPV at the end of each maneuver and 1 Osborn, Clauss, Gorin, Netwall, “Micro-satellite Technology Experiment (MiTEx) Upper Stage Propulsion System Development,” AIAA 2007-5434 how well that pressure could satisfy feed system flow requirements. These analyses considered the propellant tank volume, the propellant volume required for various orbital maneuvers, the propellant volumetric flow rate, and the COPV’s operating pressure at the beginning of the maneuver to develop a trade-space that included helium end of maneuver pressure and helium flow path pressure drop. The parametric analyses showed that the temperature of the helium at the end of the maneuver is the driver for the final expected pressure. The helium tank blowdown can be modeled as a polytropic process using Equation 1 where n represents a constant for a particular process." @default.
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• W2316230247 date "2007-07-08" @default.
• W2316230247 modified "2023-09-27" @default.
• W2316230247 title "Design, Qualification and Thermal Testing of a Specialized Composite Overwrapped Pressure Vessel" @default.
• W2316230247 doi "https://doi.org/10.2514/6.2007-5558" @default.
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