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Title: Amplitude-frequency characteristic of ion rocket thruster PIT-50

Abstract

The achievements in the spacecraft power propulsion systems allow to pass for realization of long time missions as terrestrial as outer planets. For the terrestrial flights the spacecraft stabilization is become more important and sometimes should be as less as possible. In another words it is necessary to provide high accuracy of spacecraft orbit correction and position stabilization. The missions to outer planets become more effective if it is possible to change the electric rocket thrusters (ERT) parameters during the flight. It is the necessity to compensate random actions onto the spacecraft. The last circumstance deals with the necessity of reducing the microaccelerations. In this case it is appeared a principle new problems for the system of several ERT controlling -- the decomposition of orbital perturbation on separate components, which should correspond to the operation of concrete thruster in concrete time with prescribed value of thrust. The last several years at MA1 the activity was concentrated on to investigating of small size ERT of different type: plasma-ion, stationary plasma and colloidal. It is rational to use these thrusters onboard relatively low weight and cheap spacecrafts, masses of which are about 100 -- 1500 kg. Usually these satellites have solar batterysmore » with output power 0.5--15 kW. The ERT with thrust level from 10{sup {minus}3}N up to 10{sup {minus}2}N can compensate for the satellite's random microaccelerations in the range 10{sup {minus}4}--lO{sup {minus}6} m/s{sup 2}. It opens new possibilities for different technological experiments. The results of investigation of amplitude-frequency characteristic of ion rocket thruster with 50 mm in diameter (PIT-50), developed at MAI, are given in this report. The experimental results show that thrust value can be controlled in frequency's range 50--600 Hz without changing the gas discharge chamber operation mode. In order to increase the measurements accuracy method of multi-parametric filtration was used. It allowed increasing the registration accuracy of average parameters on l0--15%. In some cases this method was successfully used for registration of quick changed parameters too.« less

Authors:
; ; ;
Publication Date:
Research Org.:
Moscow State Aviation Institute (RU)
OSTI Identifier:
20000330
Resource Type:
Conference
Resource Relation:
Conference: 33rd Intersociety Energy Conversion Engineering Conference, Colorado Springs, CO (US), 08/02/1998--08/06/1998; Other Information: 1 CD-ROM. Operating system required: Windows 3.x; Windows95/NT; Macintosh; UNIX. All systems need 2X CD-ROM drive., PBD: 1998; Related Information: In: Proceedings of the 33. intersociety energy conversion engineering conference, by Anghaie, S. [ed.], [2800] pages.
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; SPACE VEHICLES; PROPULSION SYSTEMS; ION THRUSTERS; AMPLITUDES; PLASMA; CONTROL; ORIENTATION; DESIGN; FREQUENCY CONTROL

Citation Formats

Evdokimov, K V, Latyshev, L A, Izmaylov, A A, and Polovtsev, E E. Amplitude-frequency characteristic of ion rocket thruster PIT-50. United States: N. p., 1998. Web.
Evdokimov, K V, Latyshev, L A, Izmaylov, A A, & Polovtsev, E E. Amplitude-frequency characteristic of ion rocket thruster PIT-50. United States.
Evdokimov, K V, Latyshev, L A, Izmaylov, A A, and Polovtsev, E E. Wed . "Amplitude-frequency characteristic of ion rocket thruster PIT-50". United States.
@article{osti_20000330,
title = {Amplitude-frequency characteristic of ion rocket thruster PIT-50},
author = {Evdokimov, K V and Latyshev, L A and Izmaylov, A A and Polovtsev, E E},
abstractNote = {The achievements in the spacecraft power propulsion systems allow to pass for realization of long time missions as terrestrial as outer planets. For the terrestrial flights the spacecraft stabilization is become more important and sometimes should be as less as possible. In another words it is necessary to provide high accuracy of spacecraft orbit correction and position stabilization. The missions to outer planets become more effective if it is possible to change the electric rocket thrusters (ERT) parameters during the flight. It is the necessity to compensate random actions onto the spacecraft. The last circumstance deals with the necessity of reducing the microaccelerations. In this case it is appeared a principle new problems for the system of several ERT controlling -- the decomposition of orbital perturbation on separate components, which should correspond to the operation of concrete thruster in concrete time with prescribed value of thrust. The last several years at MA1 the activity was concentrated on to investigating of small size ERT of different type: plasma-ion, stationary plasma and colloidal. It is rational to use these thrusters onboard relatively low weight and cheap spacecrafts, masses of which are about 100 -- 1500 kg. Usually these satellites have solar batterys with output power 0.5--15 kW. The ERT with thrust level from 10{sup {minus}3}N up to 10{sup {minus}2}N can compensate for the satellite's random microaccelerations in the range 10{sup {minus}4}--lO{sup {minus}6} m/s{sup 2}. It opens new possibilities for different technological experiments. The results of investigation of amplitude-frequency characteristic of ion rocket thruster with 50 mm in diameter (PIT-50), developed at MAI, are given in this report. The experimental results show that thrust value can be controlled in frequency's range 50--600 Hz without changing the gas discharge chamber operation mode. In order to increase the measurements accuracy method of multi-parametric filtration was used. It allowed increasing the registration accuracy of average parameters on l0--15%. In some cases this method was successfully used for registration of quick changed parameters too.},
doi = {},
url = {https://www.osti.gov/biblio/20000330}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1998},
month = {7}
}

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