In-orbit micro-propulsion demonstrator for PICO-satellite applications

Pallichadath, Vidhya; Turmaine, Leon; Melaika, Antanas; Gelmi, S.; Ramisa, M. Vilella; Rijlaarsdam, David; Silva, M.A.C.; Guerrieri, Daduí Cordeiro; Uludağ, Mehmet Şevket; Zandbergen, B.T.C.; Cervone, Angelo

doi:10.1016/j.actaastro.2019.09.004

Cited by 14 publications

(7 citation statements)

References 9 publications

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“…Finally, green micro-resistojets were being developed in recent years at the Delft University of Technology to operate on liquid water as fuel and to provide thrust in the range of millinewtons in different propulsion applications for micro, nano, and picosatellitesnamely CubeSats and PocketQubes [93]. Cervone et al [94,95] designed two micro-resistojet thrusters, the Vaporizing Liquid Micro-resistojet (VLM), which is based on vaporization and heating of pressurized liquid water, and then expansion in a nozzle. The other thruster is the Low Pressure Micro-resistojet (LPM), which is based on heating and acceleration of the water vapor molecules, in simple geometry slots, under a transitional or free molecular flow regime.…”

Section: Green Monopropellants In Multi-mode Propulsionmentioning

confidence: 99%

“…Combined Chemical-Electric Propulsion (CCEP): (a) a multi-mode configuration of a chemical catalytically decomposed monopropellant system alongside an electric Liquid Pulsed Plasma Thruster (LPPT) both sharing the same Green Electric Monopropellant (GEM) developed by Digital Solid-State Propulsion (DSSP) Aerospace; (b) is a CCEP dual propulsion system, the chemical system is burning FLP-106 while the electric propulsion system is separately fueled by iodine. (c) A pico-satellite multi-mode electrothermal propulsion system consisting of two micro-resistojets, Vaporizing Liquid Micro-resistojet (VLM) and Low Pressure Micro-resistojet (LPM), both fueled by liquid water as green monopropellant that is provided by a shared storage tank of rolled small diameter tube relying on the capillary action phenomenon[95].…”

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confidence: 99%

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Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

2021

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Section: Green Monopropellants In Multi-mode Propulsionmentioning

confidence: 99%

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confidence: 99%

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

2021

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“…Similarly, Cen and Xu [17] first fabricated a MEMS-based VLM created by parallel microchannels (see Figure 4a) and described the establishment of flow boiling instabilities in relation to the measured performance. More recently, at TU Delft (the Netherlands), Silva et al [18] developed a VLM with integrated molybdenum heaters (see Figure 4b) and temperature sensing using water as a propellant; later, Pallichadath et al [19] described its integration on the first demonstrator of dual-mode water-propelled micro-resistojets operating in a wide range of feeding pressure for in-orbit pico-satellite applications. The launch into orbit of their PocketQube platform Delfi-PQ equipped with the VLM as a secondary propulsion system confirmed that the VLM technology reached the technology readiness level (TRL) of four.…”

Section: Figurementioning

confidence: 99%

MEMS Vaporazing Liquid Microthruster: A Comprehensive Review

et al. 2021

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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.

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“…Water is another candidate for condensable propellants and has unique affinities for small spacecraft [21][22][23][24][25]. The primary benefit of water is its inexhaustible abundance on Earth.…”

Section: Introductionmentioning

confidence: 99%

Demonstration and experimental characteristics of a water-vapor Hall thruster

et al. 2023

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Water is an attractive candidate for condensable propellants owing to its availability, handleability, and sustainability. This study proposes the use of water vapor as a propellant for a low-power Hall thruster, and experimentally demonstrates the feasibility of this proposal. Based on the performance estimation from the plume diagnostics, a thrust-to-power ratio of 19 mN/kW, specific impulse of 550–860 s, and anode efficiency of 5–8 % were obtained at an anode power of 233–358 W. From further efficiency analysis, the mass utilization efficiency of water was found to be the most deteriorated among the internal efficiencies compared to the conventional xenon propellant, which was consistent with the expectations from a small discharge current oscillation, large beam divergence, and increase in low-energy ions. Moreover, additional power loss via reactions unique to polyatomic molecules was indicated by evaluation of the ionization cost. In this experiment, the mass utilization efficiency was improved with an increase in the anode voltage from 200 to 240 V without degradation of the power utilization. This suggests that operating at a higher voltage is more suitable for a water-vapor Hall thruster.

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In-orbit micro-propulsion demonstrator for PICO-satellite applications

Cited by 14 publications

References 9 publications

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

MEMS Vaporazing Liquid Microthruster: A Comprehensive Review

Demonstration and experimental characteristics of a water-vapor Hall thruster

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