Analysis of Nanosatellite Formation Establishment and Maintenance Using Electric Propulsion

Edlerman, Eviatar; Kronhaus, Igal

doi:10.2514/1.a33632

Cited by 9 publications

(2 citation statements)

References 19 publications

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“…Micro-and nano-satellites require precise, controllable, and continuous thrust output in order to achieve orbit change [4], attitude control [5], and rapid maneuvering [6]. Laser micro-thrust technology is an important type of propulsion technology.…”

Section: Introductionmentioning

confidence: 99%

Development of a Laser Micro-Thruster and On-Orbit Testing

Ye,

Wang,

Chang

et al. 2023

Aerospace

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Laser micro-thrust technology is a type of propulsion that uses a laser beam to ablate a propellant such as a metal or plastic. The ablated material is expelled out the back of the spacecraft, generating thrust. The technology has the advantages of high control precision, high thrust–power ratios, and excellent performances, and it has played an important role in the field of micro-propulsion. In this study, a solid propellant laser micro-thruster was developed and then applied for the attitude control of satellites during on-orbit tests. The micro-thruster had a volume of 0.5 U, a weight of 440 g, and a thrust range of 10 μN–0.6 mN. The propellant, 87% glycidyl azide polymer (GAP) + 10% ammonium perchlorate (AP) + 3% carbon nano-powder, was supplied via a double-layer belt, and the average power was less than 10 W. We present the development of the laser micro-thruster, as well as the results regarding the thruster propulsion performance. The thruster was launched into orbit on 27 February 2022 with the Chuangxin Leishen Satellite developed by Spacety. The on-orbit test of the thruster for satellite attitude control was carried out. The thruster was successfully fired in space and played an obvious role in the attitude control of the satellite. The experimental results show that the thrust is about 315 μN.

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Section: Introductionmentioning

confidence: 99%

Development of a Laser Micro-Thruster and On-Orbit Testing

Ye,

Wang,

Chang

et al. 2023

Aerospace

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“…As novel air vehicles to operate missions of earth orbit or space exploration, micro-/nano-satellites possess the merits of being small and light with convenient fabrication, low costs, etc [1]. The diversified tasks of micro-/nano-satellites require accurate, controlled and continuous thrust output in order for satellites to transfer orbits [2], adjust attitude [3] and rapidly maneuver [4], etc. For micro-satellites, propulsion systems with small volume, high integration and widely adjustable thrust are the most fundamental cores in practical engineering.…”

Section: Introductionmentioning

confidence: 99%

Impacts of laser pulse width and target thickness on laser micro-propulsion performance

Wang¹,

Du²,

Du³

et al. 2022

Plasma Sci. Technol.

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In order to optimize laser ablation performance of a micro-thruster with 1U dimensions, which employs a micro semiconductor laser, the impacts of pulse width and glycidyl azide polymer (GAP) thickness on thrust performance was researched. The results showed that with a GAP thickness of 200 μm, the single-pulse impulse (I) increased gradually with the increase in the laser pulse width from 50 to 800 μs, while the specific impulse (Isp), impulse coupling coefficient (Cm), and ablation efficiency (η) all reached optimal values with a 200 μs pulse width. It’s worth noting that the optimal pulse width is exactly the ignition delay time. Both Cm and η peaked with the pulse width of 200 μs, reaching 242.22 μN/W and 35.4%, respectively. With the increase in the GAP thickness, the I and the Cm increased gradually. The GAP of different thickness corresponded to different optimal laser pulse width. Under a certain laser pulse width, the optimal GAP thickness should be the most vertical thickness of the ablation pit, and the various propulsion performance parameters at this time were also optimal. With the current laser parameters, the optimal GAP thickness was approximately 150 μm, the Isp was approximately 322.22 s, and the η was approximately 34.94%.

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On the selection of propellants for cold/warm gas propulsion systems

Martínez¹,

Lafleur

2023

Acta Astronautica

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Analysis of Nanosatellite Formation Establishment and Maintenance Using Electric Propulsion

Cited by 9 publications

References 19 publications

Development of a Laser Micro-Thruster and On-Orbit Testing

Development of a Laser Micro-Thruster and On-Orbit Testing

Impacts of laser pulse width and target thickness on laser micro-propulsion performance

On the selection of propellants for cold/warm gas propulsion systems

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