Orbit transfer in a resistive medium with a variable thrust hall thruster

Y. Raitses; M. Guelman; J. Ashkenazy; G. Appelbaum

Orbit transfer in a resistive medium with a variable thrust hall thruster

Y. Raitses
, M. Guelman
, J. Ashkenazy
, G. Appelbaum

Research output: Contribution to conference › Paper › peer-review

Abstract

The performance capabilities of an experimental Hall thruster obtained experimentally for both variable and constant thrust modes at low power levels enable to implement orbit transfer under the influence of air drag with small satellites. For this purpose, the measured thruster performance was employed in calculations of transfer trajectories. As a result, by applying optimal thrust acceleration control the required propellant mass for a given LEO transfer was reduced by 15-17% as compared to that required for spacecraft operation with a constant thrust to power ratio. For this purpose, a Hall thruster with a movable anode is needed. In addition, the operation of an array of thrusters enables to increase a factor of variations of the thrust acceleration during the flight time.

Original language	English (US)
State	Published - 1998
Externally published	Yes
Event	34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 - Cleveland, United States Duration: Jul 13 1998 → Jul 15 1998

Other

Other	34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
Country/Territory	United States
City	Cleveland
Period	7/13/98 → 7/15/98

All Science Journal Classification (ASJC) codes

Energy Engineering and Power Technology
Electrical and Electronic Engineering
Mechanical Engineering
Control and Systems Engineering
Aerospace Engineering

Cite this

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title = "Orbit transfer in a resistive medium with a variable thrust hall thruster",

abstract = "The performance capabilities of an experimental Hall thruster obtained experimentally for both variable and constant thrust modes at low power levels enable to implement orbit transfer under the influence of air drag with small satellites. For this purpose, the measured thruster performance was employed in calculations of transfer trajectories. As a result, by applying optimal thrust acceleration control the required propellant mass for a given LEO transfer was reduced by 15-17\% as compared to that required for spacecraft operation with a constant thrust to power ratio. For this purpose, a Hall thruster with a movable anode is needed. In addition, the operation of an array of thrusters enables to increase a factor of variations of the thrust acceleration during the flight time.",

author = "Y. Raitses and M. Guelman and J. Ashkenazy and G. Appelbaum",

note = "Publisher Copyright: {\textcopyright} 1998 by the American Institute of Aeronautics and Astronautics Inc. All rights reserved.; 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 ; Conference date: 13-07-1998 Through 15-07-1998",

year = "1998",

language = "English (US)",

}

TY - CONF

T1 - Orbit transfer in a resistive medium with a variable thrust hall thruster

AU - Raitses, Y.

AU - Guelman, M.

AU - Ashkenazy, J.

AU - Appelbaum, G.

PY - 1998

Y1 - 1998

N2 - The performance capabilities of an experimental Hall thruster obtained experimentally for both variable and constant thrust modes at low power levels enable to implement orbit transfer under the influence of air drag with small satellites. For this purpose, the measured thruster performance was employed in calculations of transfer trajectories. As a result, by applying optimal thrust acceleration control the required propellant mass for a given LEO transfer was reduced by 15-17% as compared to that required for spacecraft operation with a constant thrust to power ratio. For this purpose, a Hall thruster with a movable anode is needed. In addition, the operation of an array of thrusters enables to increase a factor of variations of the thrust acceleration during the flight time.

AB - The performance capabilities of an experimental Hall thruster obtained experimentally for both variable and constant thrust modes at low power levels enable to implement orbit transfer under the influence of air drag with small satellites. For this purpose, the measured thruster performance was employed in calculations of transfer trajectories. As a result, by applying optimal thrust acceleration control the required propellant mass for a given LEO transfer was reduced by 15-17% as compared to that required for spacecraft operation with a constant thrust to power ratio. For this purpose, a Hall thruster with a movable anode is needed. In addition, the operation of an array of thrusters enables to increase a factor of variations of the thrust acceleration during the flight time.

UR - https://www.scopus.com/pages/publications/84963804071

UR - https://www.scopus.com/pages/publications/84963804071#tab=citedBy

M3 - Paper

AN - SCOPUS:84963804071

T2 - 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998

Y2 - 13 July 1998 through 15 July 1998

ER -

Orbit transfer in a resistive medium with a variable thrust hall thruster

Abstract

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All Science Journal Classification (ASJC) codes

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