Simulation and experiment research on vaporizing liquid micro-thruster

Computational study on vaporizing liquid micro-thruster

“…Based on our previous study [10], the straight heating channel of the VLM still fills with the tiny droplets, even with suitable operation conditions, as shown in Fig. 1.…”

“…The flow field in vaporizing liquid micro-thruster resembles the two-phase flow phenomena in micro-channels and is associated with liquid phase, vapor phase, evaporation, capillary force, heat transfer, and dynamic instability [12][13][14][15]. The phenomena are too complicated to model the problem completely in the current numerical studies.…”

“…The discrete phase was the tiny water droplets without evaporation. Based on the realistic structure of the VLM and experimental conditions [10], the upper surface of the simulation model was assumed as an adiabatic wall and the rest of surfaces as isothermal walls due to the extremely low thermal conductivity of Pyrex glass and high thermal conductivity of silicon. The wall temperature was set to be 300 °C.…”

“…The discrete droplets were tracked through the computational domain by solving the Lagrangian equations. The normal and parallel coefficients of restitution were set as 0.3 and 0.9 respectively by referring to the data from Yu et al [16] and our experimental results [10]. The size of the seeding droplets was set as 15 m, which was a…”

A review of MEMS micropropulsion technologies for CubeSats and PocketQubes

“…In these standards, a satellite is composed of one or more modular units, which, in the case of a CubeSat, is a cube of 10 10 10 cm  denoted 1U CubeSat. Therefore, a 3U CubeSat is a satellite composed by three of these modules with a form factor of 30 10 10 cm  [6]. For a PocketQube, a unit is a cube of 5 5 5 cm  .…”