In-orbit results of Delfi-n3Xt: Lessons learned and move forward

Guo, Jian; Bouwmeester, J.; Gill, Eberhard

doi:10.1016/j.actaastro.2015.12.003

Cited by 34 publications

(22 citation statements)

References 3 publications

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“…Delfi-Next was a triple unit CubeSat with a size of 10 cm x 10 cm x 34 cm. It had an active attitude determination and control subsystem, and a high-speed S-band transmitter communicating over a distributed linear bus with the rest of the spacecraft subsystems [33].…”

Section: A Satellites Operation Scenariosmentioning

confidence: 99%

Effects of Saturation for High-Throughput Satellite Buses

Carvajal-Godínez

Guo

Gill

2020

IEEE Trans. Aerosp. Electron. Syst.

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Bus saturation is deemed as one of the primary causes of delays in the data propagation between spacecraft components. However, the conditions under which bus congestion can affect measurements variability were not well characterized before. This work presents a bus saturation model and a set of experiments to characterize the bus performance of satellite missions for different traffic load, data rate, and synchronization periods. The results showed an increase of measurements variance of up to 18% caused by bus saturation. Additionally, an algorithm was proposed to reduce data delay by controlling saturation on the communication channel at operational level.

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Section: A Satellites Operation Scenariosmentioning

confidence: 99%

Effects of Saturation for High-Throughput Satellite Buses

Carvajal-Godínez

Guo

Gill

2020

IEEE Trans. Aerosp. Electron. Syst.

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“…Nowadays, it is also becoming more and more relevant to the design and study of microfluidic devices intended for several applications. The first microsystem device for microfluidic application, an integrated cooling system for electronic circuits with a power density of 790 W/cm 2 , dates back to the 80's [13]. This system allowed small electronic devices, producing high temperature when in operation, to keep working at better efficiency.…”

Section: Introductionmentioning

confidence: 99%

“…From the thruster point of view, the thrust ℑ increases with the mass flow rateṁ and the flow exit velocity u e , see equation (2), whereas the specific impulse I sp tends to slightly decrease with the mass flow rate, equation (3). When the heat transfer from the channel walls to the fluid increases, the exit velocity and the exit pressure P e increase, and, consequently, the thrust and specific impulse increase too.…”

Section: Introductionmentioning

confidence: 99%

“…However, in order to reduce mass and cost, typically nanosatellites (i.e., satellites with a mass between 1 and 10 kg) are still designed without any propulsion capabilities, and only very recently micro-propulsion systems have started to be developed and demonstrated in flight. Thus, their mission lifetime and performance are severely limited [1,2]. Nano-satellites are typically used in Low-Earth Orbit (LEO), where some specific missions might require a capable propulsion system to enable, for instance, formation flying, orbit change and/or station keeping of constellations.…”

Section: Introductionmentioning

confidence: 99%

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Analysis of Nonisothermal Rarefied Gas Flow in Diverging Microchannels for Low-Pressure Microresistojets

Guerrieri

Cervone

Gill

2016

Journal of Heat Transfer

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Heat transfer and fluid flow through different microchannel geometries in the transitional regime (rarefied flow) are analysed by means of Direct Simulation Monte Carlo simulations. Four types of three-dimensional microchannels, intended to be used as expansion slots in micro-resistojet concepts, are investigated using Nitrogen as working fluid. The main purpose is to understand the impact of the channel geometry on the exit velocity and the transmission coefficient, parameters which are well known to affect directly the thruster performance. Although this analysis can be applied in principle to several possible microfluidics scenarios, particular focus is given to its application in the field of space propulsion for micro-, nano-and pico-satellites, for which the requirements ask for low thrust levels from some µN to a few mN and moderate specific impulse, as well as a low power consumption in the order of a few W. Analysis shows that the thrust produced by one single microchannel can be increased by about 480% with a careful selection of the channel geometry, decreasing at the same time the specific impulse by just 5%, with a power consumption decrease of more than 66.7%.

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“…Delfi-n3Xt, a 3U Cubesat by Delft University of Technology verified a cold gas propulsion system in which the propellant is stored in a solid phase, operated in a blow down mode with continuously decreasing thrust level [62].…”

Section: B Small Satellite Case Ep: Hall Thrustermentioning

confidence: 99%

Space Propulsion Technology for Small Spacecraft

2018

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Abstract-As small satellites become more popular and capable, strategies to provide in-space propulsion increase in importance. Applications range from orbital changes and maintenance, attitude control and desaturation of reaction wheels to drag compensation and de-orbit at spacecraft end-of-life. Space propulsion can be enabled by chemical or electric means, each having different performance and scalability properties. The purpose of this review is to describe the working principles of space propulsion technologies proposed so far for small spacecraft. Given the size, mass, power and operational constraints of small satellites, not all types of propulsion can be used and very few have seen actual implementation in space. Emphasis is given in those strategies that have the potential of miniaturization to be used in all classes of vehicles, down to the popular 1-liter, 1 kg CubeSats and smaller.

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In-orbit results of Delfi-n3Xt: Lessons learned and move forward

Cited by 34 publications

References 3 publications

Effects of Saturation for High-Throughput Satellite Buses

Effects of Saturation for High-Throughput Satellite Buses

Analysis of Nonisothermal Rarefied Gas Flow in Diverging Microchannels for Low-Pressure Microresistojets

Space Propulsion Technology for Small Spacecraft

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