The Film-Evaporation MEMS Tunable Array (FEMTA) concept for propulsion and thermal control of picosats exploits microscale surface tension effect in conjunction with temperature- dependent vapor pressure to realize compact, tunable and low-power thermal valving system. The FEMTA is intended to be a self-contained propulsion unit requiring only a low-voltage DC power source to operate. The microfabricated thermal valving and very-high-integration level enables fast high-capacity cooling and high-resolution, low-power micropropulsion for picosats that is superior to existing smallsat micropropulsion and thermal management alternatives
Potential civilian and government users have expressed a strong interest in CubeSat class satellites...
To further the applicability of nano-satellites in large scale relevant missions, it is necessary th...
In this thesis, components intended for vehicles in space and other extreme environments have been r...
Current small sat propulsion systems require a substantial mass fraction of the vehicle involving tr...
The MEMS Reaction Control and Maneuvering for Picosat Beyond LEO project will further develop a mult...
Nano and pico-class satellite platforms such as 1U CubeSats, PocketQubes, and ThinSats introduce uni...
The aim of the Distributed Attitude Control and Maneuvering for Deep Space SmallSats project is to a...
The need for compact, low-power micropropulsion systems to increase the maneuverability and lifespan...
There are no mature technologies currently available for tunable propulsion and precise attitude con...
Since their inception two decades ago, CubeSats have become dominant in the small satellite market, ...
Size and power are primary limitations on nanosat missions, especially for propulsion, attitude cont...
This thesis details the heat and mass transfer analysis of a MEMs microthruster designed to provide ...
ABSTRACT Microelectromechanical systems (MEMS) and nanoelectromechanical systems (NEMS) have produce...
CUA has developed an electrothermal thruster which consumes an inert polymer propellant fiber. This ...
Progress on miniaturization techniques in the last two decades has made it possible to scaledown spa...
Potential civilian and government users have expressed a strong interest in CubeSat class satellites...
To further the applicability of nano-satellites in large scale relevant missions, it is necessary th...
In this thesis, components intended for vehicles in space and other extreme environments have been r...
Current small sat propulsion systems require a substantial mass fraction of the vehicle involving tr...
The MEMS Reaction Control and Maneuvering for Picosat Beyond LEO project will further develop a mult...
Nano and pico-class satellite platforms such as 1U CubeSats, PocketQubes, and ThinSats introduce uni...
The aim of the Distributed Attitude Control and Maneuvering for Deep Space SmallSats project is to a...
The need for compact, low-power micropropulsion systems to increase the maneuverability and lifespan...
There are no mature technologies currently available for tunable propulsion and precise attitude con...
Since their inception two decades ago, CubeSats have become dominant in the small satellite market, ...
Size and power are primary limitations on nanosat missions, especially for propulsion, attitude cont...
This thesis details the heat and mass transfer analysis of a MEMs microthruster designed to provide ...
ABSTRACT Microelectromechanical systems (MEMS) and nanoelectromechanical systems (NEMS) have produce...
CUA has developed an electrothermal thruster which consumes an inert polymer propellant fiber. This ...
Progress on miniaturization techniques in the last two decades has made it possible to scaledown spa...
Potential civilian and government users have expressed a strong interest in CubeSat class satellites...
To further the applicability of nano-satellites in large scale relevant missions, it is necessary th...
In this thesis, components intended for vehicles in space and other extreme environments have been r...