Numerical Simulation of a Free Molecular Electro Jet (FMEJ) for In-Space Propulsion

Abstract

A design of a new class of plasma-based micro-thrusters is being proposed for in-space propulsion. This device, called Free Molecular Electro Jet (FMEJ), utilizes micro-actuators to accelerate the flow in a micro-channel with rarified gas. Numerical modeling of this device is being performed in order to predict the nature of the flow inside a micro-channel and the effectiveness of actuators for the given application. The numerical model is used to assess the improvements over existing micro-thruster designs such as free molecular micro resistojets and anode layer Hall thrusters. A finite element based multiscale ionized gas (MIG) flow code utilizing the Galerkin weak statement algorithm combined with an artificial diffusion method called Sub Grid eMbedding (SGM), is used to model the thruster using continuum approach. The results show that the thrust, specific impulse and efficiency seem to be similar to other electrical propulsion devices with similar input power despite the simplicity of the micro-thruster design.

Optimization of micro single dielectric barrier discharge plasma actuator models based on experimental velocity and body force fields

“…As proceeded for Eq. (8), Eqs (12). and(16)were solved only 296 once and a coupled matrix approach was used to solve the φ field in both fluid and solid.297 Theρ c value in Eq.…”

“…(8), Eq (12). was solved normalizing φ with the value of the AC voltage 292 applied to the exposed electrode φ(t ).…”

A review of MEMS micropropulsion technologies for CubeSats and PocketQubes

“…But on the other hand, a more controllable operation of the thruster may be achieved therefore increasing the performance and optimal use of propellant. n/a n/a n/a n/a [77] ES 6.50E-01 4.00E-01 2.00E-05 3.00E-05 3.00E+03 3.00E+03 n/a n/a n/a n/a [75] ES 1.00E-01 8.00E-01 5.00E-06 5.00E-05 1.50E+03 3.26E+03 n/a n/a n/a n/a [80] ES n/a n/a 1.00E-04 1.00E-04 2.00E+03 4.60E+03 n/a n/a n/a n/a [69] LP n/a n/a 0.00E+00 1.00E+00 0.00E+00 1.50E+02 0.00E+00 1.20E+06 n/a n/a [87] LP n/a n/a 2.00E-04 1.97E-03 2.92E+00 1.34E+01 n/a n/a n/a n/a [47] LPM 1.16E+00 1.16E+00 1.70E-03 1.70E-03 5.60E+01 5.60E+01 n/a n/a n/a n/a [43] LPM n/a n/a 1. n/a n/a n/a n/a [59] SP 3.40E-01 3.40E-03 3.62E+00 3.62E+00 6.23E+01 6.23E+01 n/a n/a n/a n/a [55] SP 0.00E+00 7.50E-01 4.00E-02 5.10E-02 n/a n/a n/a n/a 1.53E+03 1.53E+03 [67] SP 1.60E-01 1.60E-01 5.00E-02 6.00E-01 2.68E+00 2.83E+01 n/a n/a n/a n/a [28] VLM n/a n/a 2.00E-03 6.50E-03 n/a n/a n/a n/a [36] VLM 9.00E-01 9.70E-01 7.10E-07 2.86E-06 1.91E+00 7.68E+00 n/a n/a n/a n/a…”

“…The type of resistance and the manufacturing approach is also important to ensure an optimal conversion of electrical to thermal energy. In general, these devices are simulated or tested with inert gasses, such as helium or nitrogen, or water but other propellants might be also considered [25], [43], [47], [48].…”

Effects of plasma kinetic modeling on performance characterization of plasma actuators for active flow control

“…Nowadays, dielectric barrier discharge plasma actuator (DBD-PA) technology has demonstrated to be interesting in active flow control systems for fluidic machinery and aeronautic foils applications, e.g. boundary layer transition and turbulence control [1,2] and noises reduction [3,4]. In fact, its peculiar characteristics make this solution ideal for real time control systems because of frequencies, no moving parts, easy and cheap installation and low power consumption [5][6][7][8].…”