Design and In-orbit Demonstration of REGULUS, an Iodine electric propulsion system

被引：40

作者：

Bellomo, Nicolas ^{[1
]}

Magarotto, Mirko ^{[2
]}

Manente, Marco ^{[1
]}

Trezzolani, Fabio ^{[1
]}

Mantellato, Riccardo ^{[1
]}

Cappellini, Lorenzo ^{[1
]}

Paulon, Devis ^{[1
]}

Selmo, Antonio ^{[1
]}

Scalzi, Davide ^{[1
]}

Minute, Marco ^{[3
]}

Duzzi, Matteo ^{[1
]}

Barbato, Alessandro ^{[1
]}

Schiavon, Alessandro ^{[1
]}

Di Fede, Simone ^{[3
]}

Souhair, Nabil ^{[4
]}

De Carlo, Paola ^{[2
]}

Barato, Francesco ^{[2
]}

Milza, Fabiana ^{[1
]}

Toson, Elena ^{[1
]}

Pavarin, Daniele ^{[1
,2
,3
]}

机构：

[1] Technol Prop & Innovat SpA, Padua, Italy

[2] Univ Padua, Dept Ind Engn, Padua, Italy

[3] Univ Padua, Ctr Studies & Act Space Giuseppe Colombo, Padua, Italy

[4] Univ Bologna, Dept Ind Engn, Forli, Italy

来源：

CEAS SPACE JOURNAL | 2022年 / 14卷 / 01期

关键词：

CubeSat propulsion; REGULUS; Iodine propellant; Plume analysis; In-orbit Demonstration; PLASMA ANTENNAS;

D O I：

10.1007/s12567-021-00374-4

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

REGULUS is an Iodine-based electric propulsion system. It has been designed and manufactured at the Italian company Technology for Propulsion and Innovation SpA (T4i). REGULUS integrates the Magnetically Enhanced Plasma Thruster (MEPT) and its subsystems, namely electronics, fluidic, and thermo-structural in a volume of 1.5 U. The mass envelope is 2.5 kg, including propellant. REGULUS targets CubeSat platforms larger than 6 U and CubeSat carriers. A thrust T = 0.60 mN and a specific impulse I-sp = 600 s are achieved with an input power of P = 50 W; the nominal total impulse is I-tot = 3000 Ns. REGULUS has been integrated on-board of the UniSat-7 satellite and its In-orbit Demonstration (IoD) is currently ongoing. The principal topics addressed in this work are: (i) design of REGULUS, (ii) comparison of the propulsive performance obtained operating the MEPT with different propellants, namely Xenon and Iodine, (iii) qualification and acceptance tests, (iv) plume analysis, (v) the IoD.

引用

页码：79 / 90

页数：12

共 50 条

[31] Critical Technology Breadboarding for the PARIS In-Orbit Demonstration Mission
Martin-Neira, M.
[J]. 2012 9TH EUROPEAN RADAR CONFERENCE (EURAD), 2012, : 373 - 376
[32] Critical Technology Breadboarding for the PARIS In-Orbit Demonstration Mission
Martin-Neira, M.
[J]. 2012 42ND EUROPEAN MICROWAVE CONFERENCE (EUMC), 2012, : 699 - 702
[33] Ground demonstration system based on in-orbit assembly oriented manipulator flexible force control
乔冠宇
Gao Huibin
Peng Cheng
Gu Yingying
Xu Zhenbang
Xu Boqian
[J]. High Technology Letters, 2017, 23 (03) : 271 - 278
[34] USE OF ELECTRIC PROPULSION FOR ORBIT TRANSFER
GODWIN, RC
[J]. ASTRONAUTICA ACTA, 1969, 14 (04): : 357 - &
[35] Propulsion system design of a hybrid electric vehicle
Uygan, Ismail Meric Can
Hartavi, Ahu Ece
Guevenc, Levent
Sezer, Volkan
Acarman, Tankut
[J]. INTERNATIONAL JOURNAL OF VEHICLE DESIGN, 2010, 52 (1-4) : 96 - 118
[36] Design of ship electric propulsion simulation system
Guo, Y
Zheng, HY
Wang, BL
Shen, AD
[J]. Proceedings of 2005 International Conference on Machine Learning and Cybernetics, Vols 1-9, 2005, : 1059 - 1063
[37] Propulsion system design of a battery electric vehicle
Rahman, Khwaja
Jurkovic, Sinisa
Hawkins, Shawn
Tarnowsky, Steven
Savagian, Peter
[J]. IEEE Electrification Magazine, 2014, 2 (02): : 14 - 24
[38] Thermal Design and In-orbit Performance of ANUSAT
Kumar, S. Rajesha
Barve, S. G.
Narayana, K. Badari
[J]. JOURNAL OF SPACECRAFT TECHNOLOGY, 2010, 20 (02): : 37 - 46
[39] Propulsion system design of electric and hybrid vehicles
Ehsani, M
Rahman, KM
Toliyat, HA
[J]. IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, 1997, 44 (01) : 19 - 27
[40] DESIGN CONSIDERATION FOR A NUCLEAR ELECTRIC PROPULSION SYSTEM
PHILLIPS, WM
PAWLIK, EV
[J]. ASTRONAUTICS & AERONAUTICS, 1978, 16 (12): : B21 - B21

← 1 2 3 4 5 →