Spacecraft propulsion applications for field emission cathodes
We discuss the spacecraft propulsion applications for field emission cathodes.
Engineering topics
Publications and source records attributed to Mueller, J..
We discuss the spacecraft propulsion applications for field emission cathodes.
Explore the source record for details and available documents.
Development of MEMS (Microelectromechanical Systems) micropropulsion at the Jet Propulsion Laboratory (JPL) is reviewed. This includes a vaporizing liquid micro-thruster for microspacecraft attitude control, a micro-ion emgine for microspacecraft primary propulsion or large spacecraft fine attitude control, as well as several valve studies, including a solenoid valve studied in collaboration with Moog Space Products Division, and a piezoelectric micro-valve.
The ability to anodically bond Kovar to Pyrex 7740 significantly expands the packaging approaches available for MEMS devices. This technique greatly simplifies and reliably interconnects micropropulsion MEMS components (thrusters, valves) with the attached propellant system.
Continued experiments performed with a micro-isolation valve are being reported upon.
This article describes the configuration of the discharge chamber and design and fabrication of the grids and field emission array (FEA) cathodes.
The MEMS Technology Group is part of the Microdevices Laboratory (MDL) at the Jet Propulsion Laboratory (JPL). The group pursues the development of a wide range of advanced MEMS technologies that are primarily applicable to NASA's robotic as well as manned exploration missions.
Replacing hollow and filament cathodes with field emitter (FE) cathodes could significantly improve the scalability, power, and performance of some meso- and microscale Electric Propulsion (EP) systems. This article discusses the motivation and challenges of integrating of FE and Electric Propulsion systems.
Replacing hollow and filament cathodes with field emitter (FE) cathodes could significantly improve the scalability, power, and performance of some meso- and microscale Electric Propulsion (EP) systems.
We report on the development of silicon micro valves for micro-propulsion and other space applications here at JPL.
A feasibility investigation for a newly proposed microfabricated, normally-closed isolation valve was initiated.
A survey and evaluation of MEMS-based microvalves has been conducted to assess the applicability of this valve technology for propulsion applications on future microspacecraft.
A status of MEMS-based micropropulsion activities conducted at JPL will be given.
Recent advances in the development of several micropropulsion components performed at JPL for microscpacecraft applications are reported upon.
A microfabricated vaporizing liquid thruster was constructed and successfully tested for the first time.
Low-temperature (LTO) chemical vapor deposited (CVD) silicon dioxide was investigated for use as an insulator material in microfabricated ion engine accelerator grids.
A feasibility investigation for a newly proposed microfabricated, normally-closed isolation valve was initiated.
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