Fabrication and Testing of the Cold Gas Propulsion System Flight Unit for the Adelis-SAMSON Nano-Satellites

Zaberchik, Michael; Lev, Dan; Edlerman, Eviatar; Kaidar, Avner

doi:10.3390/aerospace6080091

Cited by 6 publications

(5 citation statements)

References 9 publications

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“…A cold gas propulsion system was developed to maintain formation flying of three nanosatellites flown in the Adelis Space Autonomous Mission for Swarming and Geolocating Nanosatellites (Adelis-SAMSON) mission in 2021 [47]. The mission was developed by the Asher Space Research Institute at Technion.…”

Section: Propellantmentioning

confidence: 99%

“…The mission was developed by the Asher Space Research Institute at Technion. The propulsion system consists of four 20 mN thrusters that use Krypton as the propellant [48]. The system has a rated specific impulse of 34 s. Krypton was found to be the most suitable propellant for the mission due to its density, meeting the mission volume constraint and ∆V requirement.…”

Section: Propellantmentioning

confidence: 99%

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Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

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This paper explores the wide-ranging topography of micro-propulsion systems that have been flown in different small satellite missions. CubeSats, known for their compact size and affordability, have gained popularity in the realm of space exploration. However, their limited propulsion capabilities have often been a constraint in achieving certain mission objectives. In response to this challenge, space propulsion experts have developed a wide spectrum of miniaturized propulsion systems tailored to CubeSats, each offering distinct advantages. This literature review provides a comprehensive analysis of these micro-propulsion systems, categorizing them into distinct families based on their primary energy sources. The review provides informative graphs illustrating propulsion performance metrics, serving as beneficial resources for mission planners and satellite designers when selecting the most suitable propulsion system for a particular mission requirement.

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Section: Propellantmentioning

confidence: 99%

Section: Propellantmentioning

confidence: 99%

Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

View full text Add to dashboard Cite

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“…It is impossible to specify an exact value which is fitted with a cold gas propulsion system. Adelis-SAMSON carries 468 gr of Krypton at 160 bar and 30 • C. This ensures a total impulse of >150 Ns [32]. In comparison, the hot gas propulsion system develops a total impulse of 172 Ns with nitrogen at 450 • C and 27 bar, heated from 25 • C and 20 bar.…”

Section: Part B-hot Gas Propulsionmentioning

confidence: 99%

On a New Type of Combined Solar–Thermal/Cold Gas Propulsion System Used for LEO Satellite’s Attitude Control

et al. 2020

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This paper presents the development, construction and testing of a new type of solar–thermal propulsion system which can be used for low earth orbit (LEO) satellites. Currently, the vast majority of LEO satellites are fitted with a cold gas propulsion system. Although such a propulsion system is preferred, the service duration of an LEO satellite is limited by the amount of cold gas they carry onboard. In the case of the new type of solar–thermal propulsion system proposed in this paper, the cold gas is first transferred from the main tank in a cylindrical service tank/buffer tank which is placed in the focal line of a concave mirror. After the gas is heated by the solar light focused on the service tank by the concave mirror, it expands by opening the appropriate solenoid valve for the satellite’s attitude control. In this way the service duration of LEO satellite on orbit can increase by 2.5 times compared with a classic cold gas propulsion system. This is due to the propellant’s internal energy increase by the focused solar light. This paper also presents the results achieved by carrying out tests for the hot gas propulsion system in a controlled environment.

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“…The concept and mathematical models were established and verified with experiment results. Michael Zaberchik [24] designed, qualified, and integrated the cold gas propulsion system, which applied to the Adelis-SAMSON nano-satellite. Marotta Ireland's Mechanical Pressure Regulator (MPR) was developed for the Xenon Feed System on the Alphabus Platform, which could be easily modified for use in both chemical propulsion systems and cold gas propulsion systems [25].…”

Section: Introductionmentioning

confidence: 99%

Parametric Analysis of the I-Stage Structure for a Dual-Stage Gas Pressure Reducing Regulator

et al. 2020

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Gas pressure regulator is an essential component using for the pressurized system in the aircraft. In our paper, we aim to analyze the impact of structural parameters on output pressure for the I-stage structure of a dual-stage gas pressure reducing regulator. Initially, a numerical simulation of the regulator was established and verified by a comparison of dynamic response from the deflation start of the vessel to the deflation complete. Moreover, parametric analysis of the I-stage structure for the regulator was examined to determine the primary and secondary variables and interdependencies with the Box-Behnken design method applied. Furthermore, a multi-objective optimization based on regression analysis was adopted by using the MOGA-II algorithm method, and a Pareto frontier was obtained. Results indicate that the spool mass, the leakage area of spool seal, and their interaction are the significant factors on overshoot. The overshoot presents a trend of decrease first and then increase with the mass and leakage area increase. The spool mass, the mainspring stiffness, the leakage area of spool seal, and their interactions are influential factors on stability. The stability improves with the spool mass decrease, and other factors increase. Besides, the feedback hole area has a small effect on stability. Moreover, the Pareto of the optimization indicates that the performance of the I-stage structure would be optimal when the spool mass is 23.94 g, the feedback hole area is 89.94 mm 2 , the mainspring stiffness is 166.76N/mm, and the leakage area of spool seal is 0.06 mm 2 .

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Fabrication and Testing of the Cold Gas Propulsion System Flight Unit for the Adelis-SAMSON Nano-Satellites

Cited by 6 publications

References 9 publications

Propulsion Technologies for CubeSats: Review

Propulsion Technologies for CubeSats: Review

On a New Type of Combined Solar–Thermal/Cold Gas Propulsion System Used for LEO Satellite’s Attitude Control

Parametric Analysis of the I-Stage Structure for a Dual-Stage Gas Pressure Reducing Regulator

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