Saccoccia G.
European electric propulsion activities and programms / G. Saccoccia
// International electric propulsion conference. Proceedings of the 26th International electric propulsion conference. - Papers IEPC-99-001 to IPEC-99-126. - [1999]. - Vol. 1. - P.8-18. - Bibliogr.:p.17-18 (20 i.).

Аннотация: Electric propulsion for spacecraft is recognised in Europe as one of the technology areas where investments are solicited and necessary to enchance the competitiveness of the European industry in the space sector. A number of initiatives in this field aims to the development and space validation of new electric propulsion systems and to a fast implementation of electric propulsion on-board new spacecraft. European industry and Space Agencies in Europe are setting up collaborations to accelerate this process, through the availability of qualified and reliable electric propulsion systems. This paper presents an overview of the current European development in this field and the main programmes under preparation, which involve the use of electric propulsion systems.

Curran F.M.
Electric propulsion activities in U.S. indastry / F.M. Curran
// International electric propulsion conference. Proceedings of the 26th International electric propulsion conference. - Papers IEPC-99-001 to IPEC-99-126. - [1999]. - Vol. 1. - P.1-7.

Аннотация: The commercial development of electric propulsion in the United States continues to expand as the 21st century approaches. The use of long-accepted resistojet has continued and expanded to orbit insertion application. Arcjets are now firmly entrenched as workhorse devices for north-south stationkeeping.

Руководство по эксплуатации с листом утверждения : МВАУ.441586.004.000 РЭ, МВАУ.441586.004.000 РЭ ЛУ
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда винтового электрического двигателя S62Z08. - 2025. - 24 л. : ил.

Рабочая конструкторская документация : МВАУ.441586.004.000
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда винтового электрического двигателя S62Z08. - 2025. - 30 л. : ил., табл.

Паспорт с листом утверждения : МВАУ.441586.004.000 ПС, МВАУ.441586.004.000 ПС ЛУ
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда винтового электрического двигателя S62Z08. - 2025. - 5 л. : табл.

Руководство по эксплуатации с листом утверждения : МВАУ.441586.003.000 РЭ, МВАУ.441586.003.000 РЭ ЛУ
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда электрического двигателя тормозного S72Z07. - 2025. - 29 л. : ил.

Рабочая конструкторская документация : МВАУ.441586.003.000
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда электрического двигателя тормозного S72Z07. - 2025. - [34] л. : ил.

Паспорт с листом утверждения : МВАУ.441586.003.000 ПС, МВАУ.441586.003.000 ПС ЛУ
// Изготовление и сборка опытных образцов рам стендов МВАУ.441586.001.000, МВАУ.441586.002.000, МВАУ.441586.003.000, МВАУ.441586.004.000, шифр "Рамы стендов МСУ Р-265" : Каркас стенда электрического двигателя тормозного S72Z07. - 2025. - 5 л. : табл.

Plasma contactor development for space station / M.J. Patterson, J. Hamley, C. Sarmiento [et al.]
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 2216-2227. - Bibliogr.:p.2226 (25 i.).

Аннотация: Plasma contactor have been baselined for Space Station to control the electrical potentials of surfaces to eleminate/mitigate damaging interactions with the space environment. The system represents a dual-use technology which is a direct outgrowth of the NASA electric propulsion program and in particular the technology development effort on ion thruster system. The plasma contactor subsystems include the plasma contactor unit, a power electronics unit, and an expellant management unit.

High speed ion source for space experiment application / V.G. Grigorian, S.A. Kalitin, V.A. Obukhov, M.M. Shalamov
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 2211-2215.

Аннотация: Kaufman ion source operating with the mixture of hydrogen and heavy inert gas (xenon, krypton) has been investigated. Heavy gas has been fed through a hollow cathode enough to keep a discharge current at a level necessary to obtain ion hydrogen current in the beam up to 1 A.

Edwards L.
The effect of propellant selection on the performance of space missions using the UK-25 inert gas ion thruster / L. Edwards, S.B. Gabriel
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 2190-2197. - Bibliogr.:p.2197 (21 i.).

Аннотация: Ion propulsion system have potential for application in many space missions, where the high specific impulse available can offer substantial improvements in mission performance over conventional chemical propulsion systems.

Anode layer thrusters, state-of-the art and perspectives / V.I. Garkusha, E.A. Lyapin, A.V. Semyenkin, S.O. Tverdokhlebov
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 2120-2124. - Bibliogr.:p.2124 (6 i.).

Аннотация: The paper discusses anode layer thruster (ALT) application for fulfillment contemporary anf future missions. It is shown that all of them can be performed with so type thruster.

Theoretical and experimental analysis of stationary plasma thruster operation / D. Valentian, J.P. Bugeat, R. Tchuyan [et al.]
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 2112-2119.

Аннотация: In order to evaluate the potential of SPT, a systematic investigation was started two years ago. One of the most important points was the analysis of the thermal behaviour of the thruster.

Curran F.M.
Hydrogen arcjet technology stage / F.M. Curran, L. Caveny
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1989-1997. - Bibliogr.:p.1995-1997 (57 i.).

Аннотация: Over the past several years, the Ballistic Missile Defense Organization's Office of Innovative Science and Technology has sponsored a multi-faceted research programm aimed at the development of high power hydrogen arcjet systems for Earth-space missions such as orbit raising. BMDO'S program funded a number of efforts in undustry, university, and government laboratories to study critical issues such as performance, life, power processing, propellant storage and delivery, and spacecraft integration. While the BMDO hydrogen arcjet program has been terminated, it resulted in numerous advancements now being incorporated into on-going Air Force, industry, and NASA programs. This paper summarizes the progress made in the area of hydrogen arcjet systems under the BMDO programm.

Bloomer J.H.
Liquid space orbital theory of manned starflight with earthly application / J.H. Bloomer
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1924-1933. - Bibliogr.:p.1932-1933 (30 i.).

Аннотация: Key discovery is Ta Li's 1960 variational treatment of liquid-hydrogen physical and surface chemistry in Apollo Spacecraft Second-Stage fuel tanks. Li's results-comprising the foundation of "zero- gravity capillary epihydrostatics", after the term coined in 1960 by his collegue, fellow North American Aviation scientist Elliot Benedikt- led to author's 1965 precise synthetic/analytic formulation of "liquid-space optics".

Seaworth G.
Effect of volume considerations on the design of an electric orbital transfer vehicle / G. Seaworth, T. Miller
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1878-1888. - This work was in large part supported by the United States Air Force under the Operational Solar Electric Orbital Transfer Vehicle Concept Design Study (Contract No.F04701-90-C-0091). - Bibliogr.:p.18888 (10 i.).

Аннотация: The concept of a Solar Electric Orbital Transfer Vehicle (SEOTV) has been shown to be an attractive option for decreasing the cost of payload delivery to high energy orbits, particularly when using a hydrogen arcjet propulsion system.

Centaur-derived propellant supply system for a solar electric orbit tranfser vehicle / J.R. Schuster, J.R. LeMay, E.P. Morss, G.E. Williams
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1846-1860. - Bibliogr.:p.1859 (6 i.).

Аннотация: A study has been done of the propellant storage and supply system for hydrogen arcjet-propelled Solar Electric Orbit Transfer Vehicle (SEOTV) intended to carry satellite payloads from low Earth orbit (LEO) to geosynchronous Earth orbit (GEO).

Operational requirements for cost effective payload delivery with solar electric propulsion / K.P. Zondervan, A.K. Chan, C.A. Feuchter, W.B. Smith
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1835-1845. - Bibliogr.:p.1845 (5 i.).

Аннотация: The characterisics and cost of solar electric propulsion (EP) systems as a replacement for today's chemical propulsion (CP) systems have been examined for a 5-satellite geostationary constellation. Three applications were investigated: hold (orbital maintenance), move (on-orbit maneuver), and lift (orbit raising).

Miller T.
Mission factors affecting cost optimization of solar electric orbital transfer vehicle / T. Miller, G. Seaworth
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1825-1828. - Analyses and results presented herein were made possible with funding from the U.S.Air Force under contract F04701-90-C-0091. - Bibliogr.:p.1828 (12 i.).

Аннотация: Several mission and system pasrameters affect cost and design optimizaion of a Solar Electric Orbital Transfer Vehicle (SEOTV). Total launch services costs, specific launch costs, beginning-of-life power, specific impulse, and propellant mass are the parameters used to aid in the cost-optimal design of the SEOTV.

Development of ion thruster system for interplanetary mission / H. Kuninaka, K. Kitaoka, Y. Ishikawa [et al.]
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-177 THROUGH IPEC 93-251. - [1993]. - Vol. 3. - P. 1805-1809.

Аннотация: Institute of space and astronautical science has developed the ion thruster system for interplanetary mission.It is characteriized to generate simultaneously both plasmas in a plasma source and a neutralizer by a single microwave generator without thermo-emissive electrodes.