The status of electric propulsion development and applications in Russia

Koroteev, A. S.; Gorshkov, O. A.; Акимов, В. Н.; Sinitsin, A. A.; Murashko, V.; Arkhipov, B. A.; Vinogradov, V. N.

doi:10.1016/s0094-5765(02)00279-5

Cited by 6 publications

(1 citation statement)

References 6 publications

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“…Nowadays, low-power bipropellant liquid rocket engines as well as electrical propulsion (EP), including Hall-e¨ect thrusters and ion thrusters Progress in Propulsion Physics 1 (2009) 411-424 DOI: 10.1051/eucass/200901411 © Owned by the authors, published by EDP Sciences, 2009 are applied as a part of SC station- keeping propulsion system of geostationary SC. Application of EP with the spe-ci¦c impulse of 15001700 s reduces the amount of propellant needed to execute power-consuming (especially, inclination control) maneuvers of GEO station keeping by a factor of approximately 5 6 relative to low-thrust liquid propulsion [2] with the speci¦c impulse of ∼ 300 s. Hall-e¨ect EP, mainly, SPT-100 with the power of 1.35 kW and the speci¦c impulse of 1500 s, developed by EDB ¤Fakel¥ are applied on Russian geostationary space platforms, and by foreign SC-producing companies: Alcatel and Astrium in Europe, as well as Lockheed Martin Astrospace in USA. Boeing Satellite Space company applies ion thrusters XIPS-13 with the power of 0.65 kW and XIPS-25 with the power of 2.34.5 kW and the speci¦c impulse of 32003800 s, respectively.…”

Section: Introductionmentioning

confidence: 99%

Development of KM-5 Hall effect thruster and its flight testing onboard GEO spacecraft “Express-A4”

Акимов¹,

Baidakov²,

Galayko³

et al. 2009

Progress in Propulsion Physics

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The paper presents the outcomes of development of Keldysh Research Center (KeRC) KM-5 Hall e¨ect thruster and experience obtained from the in-orbit exploiting of the thruster onboard Reshetnev£s Scienti¦c and Production Association of Applied Mechanics (NPO PM) ¤Express-A4¥ GEO communication spacecraft (SC). KM-5 is a multimode thruster with operational power range from 1 to 2.5 kW in contrast to other thrusters applied in space missions. It has high thrust characteristics. It makes possible solution of orbit raising tasks to geostationary orbit (GEO) for medium and heavy weight SC in addition to tasks of station keeping for geostationary SC already being solved by Hall-e¨ect thrusters. Furthermore, a thruster with such performance can be an e©cient choice as a main engine for small interplanetary probes.

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Section: Introductionmentioning

confidence: 99%

Development of KM-5 Hall effect thruster and its flight testing onboard GEO spacecraft “Express-A4”

Акимов¹,

Baidakov²,

Galayko³

et al. 2009

Progress in Propulsion Physics

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Reduced Desensitization Formulation for Optimal Control Problems

Jawaharlal Ayyanathan,

Taheri

2024

J Astronaut Sci

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Solutions to nonlinear optimal control problems (OCPs) exhibit dispersions under model uncertainties and it is desirable to generate optimal solutions that exhibit less sensitivity to model uncertainties. We propose a novel solution desensitization method dubbed “Reduced Desensitization Formulation (RDF)” by leveraging non-uniqueness of the solution of the costate differential equations when a hybrid indirect-direct optimization method is used. A key property of the RDF method is a significant reduction in the number of differential equations needed for generating desensitized solutions. This feature facilitates the generation of open-loop desensitized trajectories and makes the methodology applicable to OCPs with a larger number of uncertain parameters. To demonstrate the utility of the RDF method, three important classes of trajectory optimization problems are considered with uncertainty in the thrust magnitude of the propulsion system: (1) minimum-fuel low-thrust interplanetary rendezvous maneuvers, (2) low-thrust orbit-raising maneuvers, and (3) minimum-fuel high-thrust rocket-landing problems. For the considered problems with bang-bang control profiles, an analysis is presented on the change in the number of control switches between sensitive and desensitized optimal solutions. Numerical results demonstrate desensitization of the considered performance indices with respect to the thrust magnitude of the propulsion system.

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Mapped adjoint control transformation method for low-thrust trajectory design

Ayyanathan

Taheri

2022

Acta Astronautica

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The status of electric propulsion development and applications in Russia

Cited by 6 publications

References 6 publications

Development of KM-5 Hall effect thruster and its flight testing onboard GEO spacecraft “Express-A4”

Development of KM-5 Hall effect thruster and its flight testing onboard GEO spacecraft “Express-A4”

Reduced Desensitization Formulation for Optimal Control Problems

Mapped adjoint control transformation method for low-thrust trajectory design

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