The authors completed those propulsion system for microsatellite based on the SAFETY FIRST policy and EFFECTIVE COTS, by the beginning of 2008, which can work as both monoand bi-propellant propulsion system and attain wide-range impulse bit and total impulse by switching the monoand bi-propellant modes. We have been devoting ourselves to develop an upgraded version of the propulsion system sice...

Abstract In this study, we fabricated nano-capillary emitter arrays for stable ion emission of ionic liquid electrospray thrusters, employing the fabrication field or gated nano electron sources. A was successfully with a 100–300 nm capillary diameter, which prevented leakage by significantly increasing fluidic impedance compared to previously proposed emitter. An experiment conducted 1-ethyl-3...

EZ, E,^, EP Results are reported from preliminary tests to evaluate the high power microwave electrothermal thruster (MET) fr concept, which employs a free-floating plasma discharge maintained by applied continuous wave (CW) microwave Hz, H,^, HP power to heat a propellant gas flow. Stable plasmas were created and maintained in helium (He), nitrogen (N 2), and hydrogen (H2) as propellants in bo...

Nitromethane is a potential green monopropellant, but there are limited kinetic studies on its burning behavior in oxygen-free conditions, such as those required byunderwater and space propulsion applications. Mechanisms for nitromethane combustion have generally been validated against experiments oxidative environments. These provide valuable data gas-phase kinetics,but they less informative e...

The ffx code was used to investigate the lifetime and propellant throughput capability of the High Power Electric Propulsion (HiPEP) thruster ion optics as part of NASA’s Project Prometheus. Erosion predictions are presented as a function of beamlet current, accel grid voltage, and propellant utilization efficiency. These predictions were then compared to the lifetime goals of the thruster, and...

A differential game guidance law for an endoatmospheric interceptor missile steered by aero fins and reaction jets is developed in this paper with bounded controls. For a low-altitude endoatmospheric interceptor, the propellant of the reaction-jet control system (RCS) is restricted by the missile configuration. Considering propellant limits, the effect of the RCS thrust on homing performance is...

NOL large card gap test is not suitable to assess the shock sensitivity of granular propellant beds made of large grains. The result can be strongly influenced by the heterogeneity of the bed. A new small scale gun propellant shock sensitivity test has been developed at ARDEC. This test is a sensitive discriminator to assess gun propellant shock sensitivity. INTRODUCTION Shock-to-detonation sen...