In orbit performance of butane propulsion system

Amri, R.; Gibbon, D.

doi:10.1016/j.asr.2011.11.021

Cited by 15 publications

(5 citation statements)

References 6 publications

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“…The heater element is coiled onto a central bobbin to increase contact between the propellant flow and heater as shown in Figure 6. SSTL developed a low-power resistojet system for its earth observation constellation called the Disaster Monitoring Constellation (DMC) [60]. A low-power butane resistojet thruster, referred to as T15, was developed for the ALSAT-1 that launched in 2002.…”

Section: Resistojetmentioning

confidence: 99%

“…The resistojet thruster vaporizes the propellant to ensure none of the liquid phase propellent is expelled through the nozzle. This is accomplished through several design choices: keeping liquid away from tank exits via surface tension provided by aluminum mesh tank inserts, a line heater coiled around the tank outlet pipe and vent valve feed pipe to prevent condensation, and an integral heater to vaporize any residual liquid and enhance mass flow rate through the thruster body [60]. All heating elements have a warm-up time of around 10 min during each thrust operation.…”

Section: Resistojetmentioning

confidence: 99%

“…The water micro-resistojet has a total mass of 188 g. The thruster needed to be pre-heated to around 473.15 K before each thrust operation. Even though the experiment encountered an early water depletion issue, the first firing was successfully performed and indicated the feasibility of water resistojet systems for SSTL developed a low-power resistojet system for its earth observation constellation called the Disaster Monitoring Constellation (DMC) [60]. A low-power butane resistojet thruster, referred to as T15, was developed for the ALSAT-1 that launched in 2002.…”

Section: Resistojetmentioning

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: Resistojetmentioning

confidence: 99%

Section: Resistojetmentioning

confidence: 99%

Section: Resistojetmentioning

confidence: 99%

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Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

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“…The current state of the art xenon resistojet has shown specific impulse (ISP) with xenon propellant up to 48 s utilised for small spacecraft below 500 kg [1][2][3]. Such performance can result in either propellant mass savings or increased capability with respect to cold gas thrusters [4].…”

Section: Introductionmentioning

confidence: 99%

“…1 shows a schematics of the first heat exchanger design reported in [4] (overall length of 8 mm and maximum diameter of 16.5 mm), which consists of a monolithic thin-wall concentric exchanger, which also serves as a resistive heater and regenerative heat recuperator, where the inner cylinder (1) also integrates a converging-diverging nozzle. The gas flows from the outer channel (1) and recirculates around the heat exchanger until it reaches channel (4), which terminates in the nozzle inlet. The four concentric cylinders are connected in series forming an electrical resistance to which power is applied.…”

Section: Introductionmentioning

confidence: 99%

Validation of an additively manufactured resistojet through experimental and computational analysis

Romei

Grubisic

2020

Acta Astronautica

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This paper presents the first proof of concept validation of the STAR thruster prototype. The device contains an innovative multifunctional monolithic heat exchanger, enabled by metal additive manufacturing processes. A 316L stainless steel printed thruster is characterized through a combination of dry heating and wet firing tests. This includes verification testing with argon in both cold and hot firing mode, at a range of electrical power inputs. Thrust measurements range from 9.7 mN ± 0.16 mN to 29.8 mN ± 0.16 mN, with a maximum measured specific impulse of 80.11 ± 1.49 s. Thrust performance is measured using a highprecision balance, and liquid-metal power transfer terminals to eliminate thermal drift. Highly coupled multiphysics computational models provide validation of the electro-thermal and thermo-fluidic characteristics of the prototype, including a prediction of the maximum propellant stagnation temperature and structural temperature, which were 649°C and 854°C.

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Steady‐state behavior of liquid fuel hydrazine decomposition in packed bed

Hou

Wang

et al. 2014

AIChE Journal

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A general theoretical model is presented to analyze the steady‐state decomposition process of liquid monopropellants in packed beds for thruster systems. Additionally, an experiment studying the decomposition of liquid hydrazine in a packed bed is used to validate this model. The liquid droplet evaporation rate is determined through calculating the gas‐liquid mass transfer for the mixture temperatures lower than the liquid propellant boiling point and solving the gas‐liquid or liquid‐solid heat transfer equations at the temperature exceeding the boiling point. The process of liquid propellant decomposition in packed beds are simulated based on the Naive–Stokes equation for the mixture model integrated with the developed liquid evaporation rate, in which both the heterogeneous catalytic reaction coupled with the diffusion of reactants in the pore of catalyst, and the homogenous decomposition reactions are considered. The calculated results for the axial distribution of the temperature are in good agreement with the experimental data. © 2014 American Institute of Chemical Engineers AIChE J, 61: 1064–1080, 2015

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In orbit performance of butane propulsion system

Cited by 15 publications

References 6 publications

Propulsion Technologies for CubeSats: Review

Propulsion Technologies for CubeSats: Review

Validation of an additively manufactured resistojet through experimental and computational analysis

Steady‐state behavior of liquid fuel hydrazine decomposition in packed bed

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