Micronozzle for satellite propulsion and mixture separation: a review

Sukesan, Manu K; Shine, S. R.

doi:10.1007/s10973-023-12227-9

Cited by 2 publications

(2 citation statements)

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“…The application of micronozzles for small satellite propulsion is a topic of great interest due to the new concept of mega-constellation of small satellites for various applications. Manu and Shine [1] provided a summary of micronozzle applications, diverse modeling approaches, and the impact of various parameters on performance. Since the size of the nozzle is of the micro level, and these devices operate in vacuum, regions of rarefied flow may exist towards the exit of the nozzle.…”

Section: Introductionmentioning

confidence: 99%

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Feasibility of macroscopic parameters for NS to DSMC solver switching in micronozzle simulations

Kumar M,

Shine

2023

Phys. Scr.

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Enhancing the design and performance of micronozzles could lead to novel applications and advancements in propulsion systems, making the exploration of micronozzles crucial for the future. This paper critically examines the feasibility of utilizing macroscopic property-based Kn as indicator for defining the breakdown region during the transition from the NS solver to the DSMC solver in micronozzle simulations. The aim is to specify a parameter that can be calculated from both NS and DSMC simulations, making it suitable for implementation in hybrid simulations that dynamically switch between the two solvers. The results show that the density-based Kn accurately represents the continuum breakdown, and it exhibits an earlier breakdown compared to pressure and temperature-based Kn values. The study also analyzes the rarefaction effects and introduces the rarefaction parameter (RP), quantifying the increase in Kn for a unit change in the non-dimensionalized distance. The findings demonstrate that at very low exit pressures, the rarefaction effects increase rapidly as the flow moves towards the nozzle exit, leading to a transition from the continuum to the rarefied regime. The hybrid NS-DSMC simulations show good agreement with experimental data, validating the proposed approach. Additionally, the research examines the effect of back pressure on the RP and identifies the transition regime based on the slope of the RP curve. Therefore, the manuscript provides detailed insights into novel elements, such as the quantification of rarefaction within the nozzle using the RP, the classification of the nozzle into different regimes (continuum, slip, and transition), the definition of an easily obtainable parameter for switching between NS and DSMC methods, and an examination of the contributions of the shear stress term and heat addition term to non-equilibrium conditions.

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Section: Introductionmentioning

confidence: 99%

“…Byod [7] proposed that the method can be improved using a local mean-free path and a length scale based on flow gradients. Boyd [7] defined a more accurate definition of Kn using the gradient length scale of a particular physical quantity, given by equation (1), where Q can be any property, namely P, ρ or T.…”

Section: Introductionmentioning

confidence: 99%

Feasibility of macroscopic parameters for NS to DSMC solver switching in micronozzle simulations

Kumar M,

Shine

2023

Phys. Scr.

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Micronewton Cold Gas Thruster Based on Silicon-Etched Two-Dimensional Nozzles

Hu,

Zhang,

Zhou

et al. 2024

AIAA Journal

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The micronewton thruster is one of the essential technologies for providing an ultrastable satellite platform for scientific experiments in space. Particularly, space gravitational wave detection requires a microthruster with continuously adjustable thrust, high resolution, low noise, and fast response. To meet these requirements, we designed a two-dimensional (2D) nozzle and manufactured it using micro-electro-mechanical systems (MEMS). Compared to the nozzles machined with conventional methods, the nozzles etched by the MEMS can easily reach a micron size and form arrays to create mutual backups and also provide a way to widen the thrust range by switching the number of openings. Based on a single 2D nozzle, a cold gas microthruster prototype is constructed with nitrogen gas as the propellant. The thrust of the prototype is tested by a pendulum, the range can span [Formula: see text], the thrust resolution is better than [Formula: see text], and the thrust noise reaches [Formula: see text] at 0.1 Hz. The result demonstrates that the scheme has the potential to be applied to gravitational wave detection missions.

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Micronozzle for satellite propulsion and mixture separation: a review

Cited by 2 publications

References 186 publications

Feasibility of macroscopic parameters for NS to DSMC solver switching in micronozzle simulations

Feasibility of macroscopic parameters for NS to DSMC solver switching in micronozzle simulations

Micronewton Cold Gas Thruster Based on Silicon-Etched Two-Dimensional Nozzles

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