Space Propulsion Technology for Small Spacecraft

Krejci, David; Lozano, Paulo

doi:10.1109/jproc.2017.2778747

Cited by 110 publications

(56 citation statements)

References 65 publications

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“…In addition, the magnitude of the acceleration vector is assumed to vary between f min 3 × 10 −5 m∕s 2 and f max 3 × 10 −4 m∕s 2 . Considering a mass of 100 kg for both spacecraft, the preceding acceleration values are compatible with different classes of lowthrust propulsion system, ranging from Hall-effect propulsion system to radio-frequency ion thrusters [35,36]. Moreover, the deputy onboard thrusters are oriented in such a way to guarantee a thrust along both directions of all axes of RTN reference frame.…”

Section: Minimum-fuel Reconfiguration Maneuver Strategy Via Mixed-mentioning

confidence: 99%

Minimum-Fuel Control Strategy for Spacecraft Formation Reconfiguration via Finite-Time Maneuvers

Mauro

Spiller

Carnà

et al. 2019

Journal of Guidance, Control, and Dynamics

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This paper addresses the minimum-fuel spacecraft formation reconfiguration maneuver in J 2 perturbed nearcircular orbits. In this study, only the deputy is assumed to be maneuverable and capable of providing a piecewise constant control thrust. The optimal control problem is formulated as a mixed-integer linear programming problem. To make the proposed strategy compliant with the requirements deriving from a realistic flight scenario, the collision avoidance and the maneuvering time constraints dictated by mission operations are included in the mathematical formulation. A linear dynamics model based on relative orbit elements parameterization and its associated closedform solution are used to impose the boundary conditions, avoiding the dynamics integration within the optimization process. Several examples are shown to demonstrate the effectiveness of the proposed approach.

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Section: Minimum-fuel Reconfiguration Maneuver Strategy Via Mixed-mentioning

confidence: 99%

Minimum-Fuel Control Strategy for Spacecraft Formation Reconfiguration via Finite-Time Maneuvers

Mauro

Spiller

Carnà

et al. 2019

Journal of Guidance, Control, and Dynamics

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“…4, 2021 order of input power is sufficient for use in small spacecraft. 35) It can be assumed that the green glow observed before ignition is the emission of magnesium oxide (MgO). 36) The appearances of combustion shown in Fig.…”

Section: Magnesium-wire Combustionmentioning

confidence: 99%

Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft

Akiyama

Nishii

Mannami

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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High thrust propulsion systems that can be used in small spacecraft are urgently needed to expand the use of small spacecraft. This study proposes a hybrid thruster for small spacecraft using wire-shaped magnesium as a fuel and water as an oxidizer. "Hybrid thruster" means that the in-space propulsion system generates thrust using a chemical reaction between a solid fuel and a vapor oxidizer, such as those utilized for hybrid rockets. Both magnesium and water are very safe, highly available, and very storable. To assess the feasibility of a hybrid thruster, we carried out experiments utilizing magnesium-wire combustion in water vapor at a pressure lower than the atmosphere, and estimated the input power for ignition, ignitability, and the average magnesium mass consumption rate. Then, propulsion performances were calculated using the experimental results, which show there is an input power of 2-3 W, with higher ignitability and a lower average mass consumption rate for thinner magnesium wires. The calculated specific impulse achieved its maximum at 323 s, with a mass mixture ratio of 1.25. At that mass mixture ratio, the calculated thrust using magnesium wires having diameters of 0.5 mm and 0.8 mm was 49.8 mN and 68.5 mN, respectively. Additionally, the applicability of the hybrid thruster was shown through a case study considering an existing deep-space misson.

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“…Satellites (Sweeting, 2018), (Miyazaki, 2018), (Nambu et al, 2019), (Bedington et al, 2016), (Parco et al, 2013), (Herrera Arroyave et al, 2015), (Burgos González, 2016), (Mozombite Frisancho, 2012), (Islam et al, 2019), (Ramadhan et al, 2019) Measurement (Pető, 2013), (Bulut et al, 2013), (Colin, 2015), , (Mendieta Daza et al, 2017), (Buitrago et al, 2019) Design (Kizilkaya et al, 2017), (Colín et al, 2016), (González-Llorente et al, 2012), (Santiago Flores et al, 2016), (Mancilla Cerezo et al, 2019), (Mafra de Carvalho et al, 2013), Testing (Ostaszewski Michałand Dzierzek & Magnuszewski, 2018), (Colin, 2016), (Krejci & Lozano, 2018), (Friend et al, 2016), (Hernandez, 2012), (Mendoza et al, 2015) Applications (Çabuloglu et al, 2011), (Lee et al, 2017), , (Anchino et al, 2019) Martino, 2013), (Pablo et al, 2014) Others (Davoli et al, 2019), (Madry et al, 2018) A characteristic that cannot be omit-ted to carry out the review of small satellites is the year of publication of the documents, with the purpose of differentiating the increasing research in this field. Therefore, the documents were discriminated by year of publication, in order to differentiate the largest number of documents in the last 5 years.…”

Section: Reference Documentsmentioning

confidence: 99%

A review of the current state of Pico and Nanosatellites: some applications in Latin America and other regions of the world

Soto

Figueredo

Cañón³

et al. 2020

GRAINE

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Small satellites have been a fundamental factor in the constant growth of space technologies from 60 years ago. Since the space war began during the Cold War, thousands of satellites have been put into low orbit to carry out radio frequency applications, analysis and sending satellite images of the earth, joint research tasks for space exploration on artificial satellites, as well as missions in other astronomical bodies. By 2019, more than 50 countries around the world have put into orbit at least 1 small satellite, which accounts for the persistent work to increase the applications of these devices and the need make known the potential of these elements for research and for technological applications. Due to this, the present article was based on the documentary search to carry out a review of the current state of small satellites, and especially of nano and pico satellites. The research defined 3 phases for the writing of this document: choice of databases and search engines according to the research area, use of selection algorithms using logical discrimination chains and, finally, extensive analysis of the chosen documents for the writing of the article. All the information was presented through statistical graphs with detailed information from years of publication, language, region, terms, and areas the greatest research of small satellites. It was found that CubeSat and CanSat are the types of nano and pico satellite with the greatest predilection for research by universities and technological institutions, given its low cost and in most cases its easy implementation.

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Space Propulsion Technology for Small Spacecraft

Cited by 110 publications

References 65 publications

Minimum-Fuel Control Strategy for Spacecraft Formation Reconfiguration via Finite-Time Maneuvers

Minimum-Fuel Control Strategy for Spacecraft Formation Reconfiguration via Finite-Time Maneuvers

Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft

A review of the current state of Pico and Nanosatellites: some applications in Latin America and other regions of the world

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