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In-orbit micro-propulsion demonstrator for PICO-satellite applications. / Pallichadath, V.; Turmaine, L.; Melaika, A.; Gelmi, S.; Ramisa, M. Vilella; Rijlaarsdam, D.; Silva, M. A.C.; Guerrieri, D. C.; Uludag, M. S.; Zandbergen, B.; Cervone, A.

In: Acta Astronautica, Vol. 165, 01.12.2019, p. 414-423.

Research output: Contribution to journalArticleScientificpeer-review

Harvard

Pallichadath, V, Turmaine, L, Melaika, A, Gelmi, S, Ramisa, MV, Rijlaarsdam, D, Silva, MAC, Guerrieri, DC, Uludag, MS, Zandbergen, B & Cervone, A 2019, 'In-orbit micro-propulsion demonstrator for PICO-satellite applications' Acta Astronautica, vol. 165, pp. 414-423. https://doi.org/10.1016/j.actaastro.2019.09.004

APA

Pallichadath, V., Turmaine, L., Melaika, A., Gelmi, S., Ramisa, M. V., Rijlaarsdam, D., ... Cervone, A. (2019). In-orbit micro-propulsion demonstrator for PICO-satellite applications. Acta Astronautica, 165, 414-423. https://doi.org/10.1016/j.actaastro.2019.09.004

Vancouver

Pallichadath V, Turmaine L, Melaika A, Gelmi S, Ramisa MV, Rijlaarsdam D et al. In-orbit micro-propulsion demonstrator for PICO-satellite applications. Acta Astronautica. 2019 Dec 1;165:414-423. https://doi.org/10.1016/j.actaastro.2019.09.004

Author

Pallichadath, V. ; Turmaine, L. ; Melaika, A. ; Gelmi, S. ; Ramisa, M. Vilella ; Rijlaarsdam, D. ; Silva, M. A.C. ; Guerrieri, D. C. ; Uludag, M. S. ; Zandbergen, B. ; Cervone, A. / In-orbit micro-propulsion demonstrator for PICO-satellite applications. In: Acta Astronautica. 2019 ; Vol. 165. pp. 414-423.

BibTeX

@article{6ec8da167dbd434f96eebdfcaf8af870,
title = "In-orbit micro-propulsion demonstrator for PICO-satellite applications",
abstract = "Delft University of Technology is currently developing the pico-satellite platform Delfi-PQ, based on the PocketQube standard, in pursuit of a new generation of satellites with lower cost, flexibility and short development time. A technology demonstration payload expected to fly in one of the first Delfi-PQ satellites is a dual thruster micro-propulsion system based on the use of water as propellant. Two different micro-resistojet concepts will be demonstrated in the same satellite flight: one based on vaporization, heating and expansion in a nozzle of pressurized liquid water (Vaporizing Liquid Micro-resistojet); the other based on heating and acceleration in slots with simple geometry of molecules of vapour under transitional or free molecular flow regime (Low Pressure Micro-resistojet). The demonstrator is based on a common propellant storage for the two micro-propulsion concepts, based on the use of the capillarity properties of water in a small diameter tube connected to the two separate MEMS thruster chips with their own dedicated valves. This paper describes the requirements and design of the complete micro-propulsion demonstrator as well as its expected operational envelope for in-orbit functional testing, based on the currently validated performance characteristics of the two thrusters.",
keywords = "cubesats, MEMS, Micro-propulsion, Micro-resistojet, PocketQube",
author = "V. Pallichadath and L. Turmaine and A. Melaika and S. Gelmi and Ramisa, {M. Vilella} and D. Rijlaarsdam and Silva, {M. A.C.} and Guerrieri, {D. C.} and Uludag, {M. S.} and B. Zandbergen and A. Cervone",
year = "2019",
month = "12",
day = "1",
doi = "10.1016/j.actaastro.2019.09.004",
language = "English",
volume = "165",
pages = "414--423",
journal = "Acta Astronautica",
issn = "0094-5765",
publisher = "Elsevier",

}

RIS

TY - JOUR

T1 - In-orbit micro-propulsion demonstrator for PICO-satellite applications

AU - Pallichadath, V.

AU - Turmaine, L.

AU - Melaika, A.

AU - Gelmi, S.

AU - Ramisa, M. Vilella

AU - Rijlaarsdam, D.

AU - Silva, M. A.C.

AU - Guerrieri, D. C.

AU - Uludag, M. S.

AU - Zandbergen, B.

AU - Cervone, A.

PY - 2019/12/1

Y1 - 2019/12/1

N2 - Delft University of Technology is currently developing the pico-satellite platform Delfi-PQ, based on the PocketQube standard, in pursuit of a new generation of satellites with lower cost, flexibility and short development time. A technology demonstration payload expected to fly in one of the first Delfi-PQ satellites is a dual thruster micro-propulsion system based on the use of water as propellant. Two different micro-resistojet concepts will be demonstrated in the same satellite flight: one based on vaporization, heating and expansion in a nozzle of pressurized liquid water (Vaporizing Liquid Micro-resistojet); the other based on heating and acceleration in slots with simple geometry of molecules of vapour under transitional or free molecular flow regime (Low Pressure Micro-resistojet). The demonstrator is based on a common propellant storage for the two micro-propulsion concepts, based on the use of the capillarity properties of water in a small diameter tube connected to the two separate MEMS thruster chips with their own dedicated valves. This paper describes the requirements and design of the complete micro-propulsion demonstrator as well as its expected operational envelope for in-orbit functional testing, based on the currently validated performance characteristics of the two thrusters.

AB - Delft University of Technology is currently developing the pico-satellite platform Delfi-PQ, based on the PocketQube standard, in pursuit of a new generation of satellites with lower cost, flexibility and short development time. A technology demonstration payload expected to fly in one of the first Delfi-PQ satellites is a dual thruster micro-propulsion system based on the use of water as propellant. Two different micro-resistojet concepts will be demonstrated in the same satellite flight: one based on vaporization, heating and expansion in a nozzle of pressurized liquid water (Vaporizing Liquid Micro-resistojet); the other based on heating and acceleration in slots with simple geometry of molecules of vapour under transitional or free molecular flow regime (Low Pressure Micro-resistojet). The demonstrator is based on a common propellant storage for the two micro-propulsion concepts, based on the use of the capillarity properties of water in a small diameter tube connected to the two separate MEMS thruster chips with their own dedicated valves. This paper describes the requirements and design of the complete micro-propulsion demonstrator as well as its expected operational envelope for in-orbit functional testing, based on the currently validated performance characteristics of the two thrusters.

KW - cubesats

KW - MEMS

KW - Micro-propulsion

KW - Micro-resistojet

KW - PocketQube

UR - http://www.scopus.com/inward/record.url?scp=85072989198&partnerID=8YFLogxK

U2 - 10.1016/j.actaastro.2019.09.004

DO - 10.1016/j.actaastro.2019.09.004

M3 - Article

VL - 165

SP - 414

EP - 423

JO - Acta Astronautica

T2 - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

ER -

ID: 61609839