This includes reporting on flight electric propulsion hardware development, ground and flight system operations, space qualification programs, flight plasma diagnostics development and experiments, and in-flight programs status.
Other areas of interest include: New propulsion system architecture approaches and technology demonstrations that are being pursued to reduce cost, expand capabilities, and enable new missions are also of significant interest.
Monopropellant technology is of critical importance to spacecraft operations and principally relies upon catalyst technology. Electric Propulsion Flight Programs: This includes reporting on mission studies that leverage electric propulsion systems to enable or enhance commercial, science, and human exploration space missions.
This includes electric propulsion subsystem design, propellant storage and feed systems development, power processing units design and testing and integrated system testing of electric propulsion subsystems.
Decreased toxicity monopropellant thruster technology development has been of primary interest for spacecraft applications in the last decade. Some current areas of interest include, but are not limited to, green propellants and propulsion system developments for modern spacecraft and new missions.
Papers are solicited on the following topics of particular interest for sessions supporting spacecraft chemical propulsion: Electric Propulsion Mission Studies: Applications, concepts, and designs for propulsion systems or components for small satellites are of interest.
Spacecraft propulsion technology issues examined include: The charter of the Spacecraft Propulsion Subcommittee addresses technical problems and issues of national needs associated with technology applied to space-based primary or auxiliary propulsion.
This area includes physics of electric propulsion processes, thruster technology development, advanced and breakthrough concepts, high-power electric propulsion, hybrid and dual-mode systems using electric propulsion, alternate propellant research, laboratory plasma diagnostic techniques, and electric propulsion ground test facilities effects.
This includes the reuse of heritage components and developments in reusable vehicles, systems, or components. SPS Mission Areas The 9th JANNAF Spacecraft Propulsion Subcommittee SPS seeks abstracts on the full array of spacecraft propulsion technology interests including electric propulsion, chemical propulsion, micro-thrust propulsion, solar thermal propulsion, nuclear thermal propulsion, aerocapture, solar sails, tether systems, and technologies for the future.
Topics of interest include: Also, reuse or modification of existing propulsion systems and components has been an ongoing and emerging area of development where publications are sought.
Of particular interest are papers on components such as valves, tankage, propellant feed system elements, and power conditioning for micro-propulsion applications. Systems Engineering of Electric Propulsion Subsystems: These issues for both system and component level include design, development, materials, lifetime, performance, ground testing, flight testing, validation, qualification, spacecraft integration, fabrication processes, standards and cost.
Increasing community knowledge of lessons learned and the relative impact of forthcoming technologies and approaches will support the transition and evolution of these propulsion approaches.A propulsion system is the primary mobility device of a spacecraft and helps with orbit modifications and attitude control.
This paper provides an overview of micro-propulsion technologies that have been developed or are currently being developed for CubeSats. Some of the micro-propulsion technologies listed have also flown as secondary propulsion systems on larger spacecraft.
Proof-of-Concept Demonstration of a Vaporizing Liquid Micro-Thruster Juergen Mueller*, Indrani Chakraborty", termed a Vaporizing Liquid Micro-Thruster4 (VLM) and relies in its construction on silicon-based microfabrication for a multiply redundant attitude control system, thus.
The intended purpose of this thruster concept is for use as an attitude control device o n have lacked propulsion systems altogether, future micro- Design, analysis and fabrication of a vaporizing liquid micro. - Each Micro Propulsion Attitude Control System (MPACS) tube underwent testing prior to assembly and launch.
The first tests for MPACS occurred on 10 and 13 May These tests involve firing each tube and documenting how many pulses are observed.
This attitude control system will control the complete 6U P-Spec satellite during the initial detumbling and experimental preparation phases, and it will continue to control the 2U Detector-Sat with +/-5° pointing accuracy after separation.
Plasma-Sat will not contain any active attitude control hardware. The basic performance test of μ-PPT electric propulsion system performance test for the thruster head was conducted at intervals of 5min, or approximately ignitions.
The pressure was maintained by the pumping system between × Pa and × Pa throughout the basic performance tests.Download