Engineering topics
Publications and source records attributed to Mueller, J..
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.
Explore the source record for details and available documents.
Agenda: Design and Use of the Microisolation Valve; Geometry of the Microisolation Valve; FEA Model Objectives; Results of the 10 and 50 microns Thick Wall Models; Results of the Thermally-Induced Stresses.
Strong recent interest with the aerospace community to build smaller spacecraft necessitates the development of space hardware able to fit the unique requirements with respect to mass, size, and power.
Low-temperature (LTO) chemical vapor deposited (CVD) silicon dioxide was investigated for use as an insulator matierial in microfabriacted ion engine accelerator grids.
Proof-of-concept testing of a microfabricated vaporizing liquid thruster was performed.
State-of-the-art thruster technologies are reviewed and evaluated in view of potential microspacecraft applications.
The design and fabrication of a newly proposed vaporizing liquid micro-thruster concept is described.