Abstract
The interest in developing efficient nano and pico-satellites has grown in the last 20 years. Secondary propulsion systems capable of serving specific maneuvers are an essential part of these small satellites. In particular, Micro-Electro-Mechanical Systems (MEMS) Vaporizing Liquid Microthrusters (VLM), using water as a propellant, represent today a smart choice in terms of simplicity and cost. In this paper, we first propose a review of the international literature focused on MEMS VLM development, reviewing the different geometries and heating solutions proposed in the literature. Then, we focus on a critical aspect of these micro thrusters: the presence of unstable phenomena. In particular, the boiling instabilities and reverse channel flow substantially impact the MEMS VLMs’ performance and limit their applicability. Finally, we review the research focused on the passive and active control of the boiling instabilities, based on VLM geometry optimization and active heating strategies, respectively. Today, these ones represent the two principal research axes followed by the scientific community to mitigate the drawbacks linked to the use of MEMS VLMs.
Highlights
The reduction in the launch and space mission costs is one of the main objectives of the space industry
First, we propose a review focused on Mechanical Systems (MEMS) Vaporizing Liquid Microthrusters (VLM) geometries and heating solutions proposed in the literature
We focus on a critical aspect of these micro thrusters: the presence of boiling instabilities and reverse channel flow, which substantially impacts the MEMS VLMs performance and limits their applicability
Summary
The reduction in the launch and space mission costs is one of the main objectives of the space industry. The high enthalpy vapor is expanded through a micronozzle Nowadays, they represent one of the most promising solutions for secondary propulsion able to provide nominal thrust levels in the range (0.5–2) mN [4] and specific impulse above 100 s (see Table 1), as required for the attitude control and the pointing systems of miniaturized spacecrafts [5]. They represent one of the most promising solutions for secondary propulsion able to provide nominal thrust levels in the range (0.5–2) mN [4] and specific impulse above 100 s (see Table 1), as required for the attitude control and the pointing systems of miniaturized spacecrafts [5] This combines with additional advantages, such as a high compactness and low mass, high integration capability, high reliability, and fast response, as underlined in [4]. We review the research focused on passive and active control of the boiling instabilities, based on VLM geometry optimization and active heating strategies, respectively
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