The use of liquefied gases in small satellite propulsion systems

Gibbon, D.; Paul, Malcolm; Smith, Peter; McLellan, Roland

doi:10.2514/6.2001-3246

Cited by 8 publications

(3 citation statements)

References 1 publication

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“…Butane was chosen due to its relatively high storage density of 0.54 g/cm 3 , making it a more suitable choice for smaller satellites with size constraints. The total wet mass of the spacecraft was 6.5 kg, and the mass of the propulsion system was 450 g including the propellant [14]. The propellant was stored in a 1.1 m coiled titanium tubing (65 cm 3 storage volume), depicted in Figure 3, instead of a conventional tank in order to fit within a central triangular allocated space, have a more even mass distribution along the tube without needing a pressure vessel, and utilize low-cost standard tubing material.…”

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%

“…The valve was supplied by Polyflex Aerospace Ltd. The butane propulsion system provided a total mission ∆V of 2 m/s and achieved an I sp of 43 s [14]. The achieved specific impulse was lower than the theorical value of 70 s due to liquid propellant being expelled at the start instead of gas, which reduced the efficiency of the system.…”

Section: Propellantmentioning

confidence: 99%

Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

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“…A successful low pressure cold gas system, demonstrated in the confines of the was raised to 127 s and produced a thrust of 125 mN [27]. The N 2 O resistojet was flown as a technology demonstrator for orbital maneuvers and produced a total of 10.4 m/s ∆V.…”

Section: Small Spacecraft Propulsion Optionsmentioning

confidence: 99%

Refrigerant-Based Propulsion System for Small Spacecraft

Seubert¹

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The MR SAT spacecraft under development at UMR requires a propulsion system that can be utilized to perform orbital maneuvers and three-axis attitude control to complete its mission objective of conducting spacecraft formation flight. This thesis documents the research, analysis design and development of the cold gas propulsion system that was integrated in the MR SAT spacecraft. The basis of design and safety requirements stemmed from the AFRL University Nanosat Program competition, in which the UMR SAT project placed third out of eleven schools from across the nation. The MR SAT propulsion system was a primary feature as it implements a refrigerant (R-134a) propellant that has never been flown in space. As detailed in this thesis, through engineering modeling and laboratory testing R-134a is demonstrated to be a feasible propellant for small spacecraft. As the R-134a is stored as a saturated liquid in the tank, it was necessary to analyze the thermodynamic properties of the refrigerant and investigate phase changes for its use as a propellant. Also documented is the hardware selected and the integration into the MR SAT spacecraft, along with the laboratory testing that has been conducted. R-134a offers good performance characteristics and this thesis can be used as a design template by other small spacecraft developers who require a safe and inexpensive propulsion system. v

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In orbit performance of butane propulsion system

Amri

Gibbon

2012

Advances in Space Research

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The use of liquefied gases in small satellite propulsion systems

Cited by 8 publications

References 1 publication

Propulsion Technologies for CubeSats: Review

Propulsion Technologies for CubeSats: Review

Refrigerant-Based Propulsion System for Small Spacecraft

In orbit performance of butane propulsion system

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