Sneegas S.
Space surveillance track and autonomous reposition (SSTAR) experiment / S. Sneegas, R. Vondra, R. Rosenthal
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.507-524.

Аннотация: SSTAR will demonstrate technologies, sysbsystems and operations suitable for DOD, civilian, and commercial applications.

Friesbee R.H.
Power processing units for high powered nuclear electric propulsion with MPD thruster / R.H. Friesbee, Das R.S.L., S. Krauthamer
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1,P.-500-506. - Bibliogr.:p.506 (7 i.).

Аннотация: This paper summarizes an evaluation of power processing units (PPUs) for nuclear electric propulsion (NEP) vehicles using advanced magnetoplasmadynamic (MPD) thrusters.

Kaufman D.A.
Plume characteristics of an ECR plasma thruster / D.A. Kaufman, D.G. Goodwin
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.355-360.

Аннотация: The electron cyclotron resonance (ECR) thruster is proposed electrodeless space electric propulsion device with some interesting and little understood physics.

Barabanov N.
Plasma flow intvestigation in MPD-thruster / N. Barabanov
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.704-709. - Bibliogr.:p.709 (12 i.).

Аннотация: Plasma flow in self field MPD thruster is studied. There is a high current end-fire thruster, in which propellant is fed through the cathode. Theoretical model consist of the quasi one-dimensional magnetohydrodynamic equation. A comparison between theoretical and experimental distribution of magnetic induction is performed.

Sutton A.M.
Overview of the Air Force ESEX flight experiment / A.M. Sutton
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.549-553. - Библиогр.:p.552-553 (11 i.).

Аннотация: In the post cold war,the United States Air Force is challenged by the need for increased maneuverability of the U.S. space assest, and the need to reduce launch cost. These needs have spawned the Electric Propulsion Space Experiments.

LaPointe M.
Numerical simulation of cylindrical self-field MPD thrusters with multiple propellanats / M. LaPointe
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.673-686. - Bibliogr.:p.684-686 (40 i.).

Аннотация: A two-dimensional, two-temperature, single fluid MHD code was used to predict the performance of cylindrical, self-field MPD thrusters operated woith argon, lithium, and hydrogen propellants.

Numerical fluid simulation of an MPD thruster with real geometry / G. Galdo, E.Y. Choueri, A.G. Kelly, R.G. Jahn
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.654-662. - This work is supported by the Air Force Office of Scientific Research under contract AFOSR-91-0162 and the National Aeronautics and Space Administration under contract NASA-954997. - Bibliogr.:p.661 (18 i.).

Аннотация: A two-fluid, two-dimensional numerical model for axially symmetric arbitrary-geometry MPD thruster flows including anomalous transport has been developed and used to study the flow in a Full-Scale Benchmark Thruster (FSBT) with argon propellant and under realistic conditions.

Maurer M.
Nonlinear development of space charge instability in MPD-thruster flows / M. Maurer, H.J. Kaeppeler
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.636-643. - This work was sponsored by Deutcshe Agenture fur Raumfahrtangelegenheiten (DARA) under contract number 50 TA 9008. - Bibliogr.:p.642-643 (14 i.).

Аннотация: In the first part of this paper a review of the investigation of instabilities in multicomponent non-equilibrium MPD thruster flows is given, carried out at IRIS and MAN Technologies AG. Also latest results obtained from nonlinear development of the space charge instability are presented showing that the nonlinear development of the current density actually leads to strong oscilatory behaviour depending on the time development of the linear states, particularly on the local value of the electric field strength and thus on the values of the relative gradients. Finally the connection between the specific impulse and development of the space charge instability will be discussed.

Herber G.
NEPSTP-an international testbet for xenon electric propulsion / G. Herber, G. Gameron, L. Caveny
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1,P.-525-536.

Аннотация: The nuclear electric propulsion space test propramm (NEPSTP) is a BMDO sponsored technology demonstration of a Russian space nuclear reactor (TOPAS 2) and an international complement of xenon electric thrusters. The mission is described along with some of the design accomplishments to date.

Development of an MPD thruster system for the EPEX space test / K. Toki, Y. Shimizu, K. Kuriki [et al.]
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.554-561. - Библиогр.:p.561 (6 i.).

Аннотация: The EPEX (Electrical Propulsion Experiment) is a space test of an MPD propulsion system on-board the Space Flyer Unit Mission One (SPU-1) scheduled in February 1995. This will be virtually the first test for the use of MPD arcjet as a thruster system with satisfactory electrical power of 4300 W.

Development of a power electronics unit for the space station plasma contactor / J. Hamley, G. Hill, M. J. Patterson [et al.]
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.488-499.

Аннотация: A hollow cathode plasma contactor has been baselined as a charge control device for Space Station (SS) to prevent deleterios interactions of coated structural components with the ambient plasma. NASA Lewis Research Center Work Package 4 initiated the development of a plasma contactor system comprised as a Power Electronics Unit (PEU), an Expellant ManagementUnit (EMU), a command and data interface, and a Plasma Contactor Unit (PCU).A breadboard PEU was designed and fabricated, and contained a cathode heater and discharge power supply, which were required to operate the PCU, a control and auxiliary power converter, an EMU interface, a command and telemetry interface, and a controller.

Messerschmid E.W.
Development and utilization objectives of a low-power arjet for the P3-D (OSCAR) satellite / E.W. Messerschmid, D.M. Zube, L. Kurtz
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1,P.-538-548. - Библиогр.:p.548 (12 i.).

Аннотация: The international radio amateur organization AMSAT will launch their P3-D satellite weighing 400 kg into a highly elliptical 16h orbit in April 1996 with the second prototype launch of the ARIANE V rocket. On this satellite, for the firs time, the orbit control will be performed by an arcjet system. This system, dubbed ATOS for arcjet thruster on OSCAR satellite, is run with ammonia as propellant at a power of 700 W. The paper describes the utilization and technological objectives of satellite, the planned orbit and the orbit control srategy and the arcjet propulsion sysem. An account of the development status as of September 1993 will be given.

Goodfellow K.D.
Design and development of 3 to 10 kW ammonia arcjet / K.D. Goodfellow, J.E. Polk
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.710-723. - Bibliogr.:p.721-723 (10 i.).

Аннотация: An ammonia arjet capable of throttling between 3 to 10 kW and producing a specific impulse of 600 s is required for the SSTAR flight experiment. Testing was performed to evaluate the performance of two nozzle configuration on ammonia arjet performance over this power range.

Shoji T.
Analytical study on nonequilibrium flows in self-field MPD thruster / T. Shoji, K. Ogiwara, I. Kimura
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - P.663-672.

Аннотация: A numerical simulation of one-dimensional flows in self-field magnetoplasmadynamic (MPD) thrusters is performed taking thermal and ioniization nonequilibrium state into account. The model used includes the electron energy and ionization rate equations and is referred to as a two-temperature model.

Hickman J.M.
TPOPIX: a solar electric propulsion flight experiment / J.M. Hickman, G.B. Hillard
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - C.583-589. - Bibliogr:p.588-589 (17 i).

Аннотация: The Transfer Orbit Plasma Interaction Experiment (TROPIX) is a proposed scientific experiment and flight demonstration of a solar electric propulsion vehicle.Its mission goals are to significantly increase our knowledge of Earth's magnetosphere and its assosiated plasma environment and to demonstrate an operational solar electric upper stage (SEUS) for small launch vehicles.

Bartoli C.
Space-borne astrnomical gravity-wave interferometer mission (SAGITTARIUS): the field emission electric propulsion (FEEP) option / C. Bartoli, J. Gonzalez, G. Saccoccia
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - С.185-191. - Библиогр.: с.191 (13 назв.).

Аннотация: The international gravity waves scientific community has presented thr SAGITTARIUS mission in parallel to NASA and ESA during this year 1993. This mission has as main goal the first direct detection of gravitational waves from galactic binary stars and the opening of the Low Frequency (LF) graviatational wave window on the universe. The SAGITTARIUS mission will be formed by six spacecraft,located in a circular earth orbit at an altitude of 600000 km and linked by laser beams. A laser tracking signal will be generated in each of the respective and spacecraft where will be actively transponded back to the sentral spacecraft.

Wagner H.P.
Space charge instability, current chopping and anomalous transport in stationary MPD thruster flows / H.P. Wagner, M. Auweter-Kurtz, E.W. Messerschmid
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - C.626-635. - This work was in part supported by the Deutsche Forschungsgemeinschaft under the grants Me 951/1-1 and Me 951/1-2, and by the Luxemburg Ministere de I'Education Nationale under the grant BFR92/103. - Bibliogr.: p.634-635 (13 i).

Аннотация: A systematic investigation of instability in multicomponent non-equilibrium MPD thruster flows is in progress at the IRS since 1987.One of the main objects of study is the onset of performance-limiting instabilities in MPD thruster.

Hamley J.
Power electronics development for the SPT-100 thruster / J. Hamley, G. Hill, J. Sankovic
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - С.405-415. - Библиогр.: с.409 (13 назв.).

Аннотация: Russian electric propulsion technologies has recently become available in the world market. Of significant interest in the Stationary Plasma Thruster, (SPT) which has a significant flight heritage in the former Soviet space programm.The SPT has performance levels of up to 1600 seconds of specific impulse at a thrust efficciency of 0,50.Studies have shown that this level of performance is well suited for stationkeeping applications, and the SPT-100, whith a 1,35 kW input power level is presently being evaluated for use on Western commercial satellites. Under a program sponsored by the Innovative Science and Technology Division of the Ballistic Missile Defence Organization, a team of U.S. electric propulsion specialists observed the operation of the SPT-100 in Russia.

Bloomfield H.S.
Potential NASA early flight nuclear electric propulsion missions / H.S. Bloomfield
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - C.598-604. - Bibliogr.: p.604 (5 i).

Аннотация: This paper reports the results of a recent NASA study to define and characterize the "fast-track" space nuclear power and propulsion system technology options that could provide NASA with safe, evolutionary, early and low cost space flight demonstration miissions. The goal of the study was to characterize missions that could use these "fast-track" technologise to provide demonstration of nuclear reactor powered spacecraft in a near-term mission application that has value to NASA science and/or exploration program.

Kaufman D.A.
Plume characteristics of an ECR plasma thruster / D.A. Kaufman, D.G. Goodwin
// International electric propulsion conference. Proceedings of the 23rd International electric propulsion conference. - Papers IEPC-93-001 THROUGH IPEC 93-087. - [1993]. - Vol. 1. - С.355-360. - Библиогр.: с.360 (6 назв.).

Аннотация: The Electric Cyclotron Resonance thruster is a proposed electrodeless space electric propulsion device with some interesting and little understood physics.