Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine
This paper is the extension of investigations of the RF engine designed for orientation and stabilization of the spacecrafts orbit, and it is undertaken for measuring of plasma parameters of RF discharge in the ionization resonator chamber. The experiments were performed at the frequency of 80 MHz o...
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| Published in: | Вопросы атомной науки и техники |
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| Date: | 2003 |
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Національний науковий центр «Харківський фізико-технічний інститут» НАН України
2003
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| Cite this: | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine / V.S. Vdovin, B.V. Zajtzev, A.F. Kobetz, B.I. Rudiak, V.A. Bomko, M.S. Lesnykh, V.G. Zhuravlev, V.M. Rashkovan, L.A. Bazyma, V.A. Basteev, V.I. Belokon // Вопросы атомной науки и техники. — 2003. — № 1. — С. 150-152. — Бібліогр.: 2 назв. — англ. |
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Digital Library of Periodicals of National Academy of Sciences of Ukraine| _version_ | 1859845668589273088 |
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| author | Vdovin, V.S. Zajtzev, B.V. Kobetz, A.F. Rudiak, B.I. Bomko, V.A. Lesnykh, M.S. Zhuravlev, V.G. Rashkovan, V.M. Bazyma, L.A. Basteev, V.A. Belokon, V.I. |
| author_facet | Vdovin, V.S. Zajtzev, B.V. Kobetz, A.F. Rudiak, B.I. Bomko, V.A. Lesnykh, M.S. Zhuravlev, V.G. Rashkovan, V.M. Bazyma, L.A. Basteev, V.A. Belokon, V.I. |
| citation_txt | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine / V.S. Vdovin, B.V. Zajtzev, A.F. Kobetz, B.I. Rudiak, V.A. Bomko, M.S. Lesnykh, V.G. Zhuravlev, V.M. Rashkovan, L.A. Bazyma, V.A. Basteev, V.I. Belokon // Вопросы атомной науки и техники. — 2003. — № 1. — С. 150-152. — Бібліогр.: 2 назв. — англ. |
| collection | DSpace DC |
| container_title | Вопросы атомной науки и техники |
| description | This paper is the extension of investigations of the RF engine designed for orientation and stabilization of the spacecrafts orbit, and it is undertaken for measuring of plasma parameters of RF discharge in the ionization resonator chamber. The experiments were performed at the frequency of 80 MHz on the model engine, in which a length of coaxial line with shortening capacities at the ends was used as the ionization resonator chamber. As the result of the experiments, conditions of the RF discharge ignition in the resonator chamber are studied; dependencies of plasma density and temperature versus applied power and working body pressure are obtained for various gases. The measurements of the thrust were performed at the special-purpose test bench. The data obtained allow making a conclusion that further investigations in this direction hold much promise.
Представлена робота продовжує дослідження НВЧ – двигуна, призначеного для орієнтації та стабілізації орбіти космічних апаратів, й виконана з метою виміряти параметри плазми НВЧ – розряду в іонізаційній камері – резонаторі двигуна. Експерименти проводились з частотою 80 МГц на макеті двигуна, в якому в якості іонізаційної камери використовувався відрізок коаксиальної лінії зі скорочуваючими ємностями на кінцях. В експериментах вивчені умови запалювання НВЧ – розряду в камері–резонаторі, отримані залежності густини та температури плазми від прикладеної потужності та тиску робочого тіла для різних газів. На спеціалізованому випробному стенді були проведені вимірювання тяги. Отримані результати дозволяють зробити висновок про перспективність подальших досліджень у цьому напрямку.
Настоящая работа является продолжением исследований СВЧ – двигателя предназначенного для ориентации и стабилизации орбиты космических аппаратов и предпринята с целью измерения параметров плазмы СВЧ – разряда в ионизационной камере – резонаторе двигателя. Эксперименты проводились на частоте 80 МГц на макете двигателя, в котором в качестве ионизационной камеры – резонатора использовался отрезок коаксиальной линии с укорачивающими емкостями на концах. В экспериментах изучены условия зажигания СВЧ разряда в камере - резонаторе, получены зависимости плотности и температуры плазмы от приложенной мощности и давления рабочего тела для различных газов. На специализированном испытательном стенде были проведены измерения тяги. Полученные данные позволяют сделать вывод о перспективности дальнейших исследований в этом направлении.
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| first_indexed | 2025-12-07T15:38:47Z |
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INVESTIGATION OF PARAMETERS OF THE WORKING SUBSTANCE -
LOW TEMPERATURE PLASMA IN THE IONIZATION RESONATOR
CHAMBER OF THE RF REACTIVE ENGINE
V.S. Vdovin, B.V. Zajtzev, A.F. Kobetz, B.I. Rudiak, V.A. Bomko, M.S. Lesnykh, V.G. Zhuravlev,
V.M.Rashkovan*, L.A. Bazyma*, V.A. Basteev*,V.I. Belokon*
NSC "Kharkov Institute of Physics and Technology”;
*Kharkov Aero-Space University
This paper is the extension of investigations of the RF engine designed for orientation and stabilization of the
spacecrafts orbit, and it is undertaken for measuring of plasma parameters of RF discharge in the ionization resonator
chamber. The experiments were performed at the frequency of 80 MHz on the model engine, in which a length of
coaxial line with shortening capacities at the ends was used as the ionization resonator chamber. As the result of the
experiments, conditions of the RF discharge ignition in the resonator chamber are studied; dependencies of plasma
density and temperature versus applied power and working body pressure are obtained for various gases. The
measurements of the thrust were performed at the special-purpose test bench. The data obtained allow making a
conclusion that further investigations in this direction hold much promise.
PACS: 52.75.-d
SETTING UP THE PROBLEM
Presently, in connection with intensive development of
telecommunication systems and global Internet system the
question about creation of reliable communication satellites
with long-term operating life arose. One of the main factors
defining operating life of these satellites is the operating
resource of low thrust engines, which are used for correction
and stabilization of satellites’ orbits. As a rule, electro reactive
engines of different types with plasma exhaust velocity of the
order of 103 – 105 m/s are used as low thrust engines.
Engines for orbit correction and stabilization, as well as any
other space engines, must possess high flight efficiency over
the all range of specific pulses of interest for the given
application; must have, if possible, a simple reliable
construction and minimum sizes and weight. The operating
resource of electro reactive engines is determined mainly with
the processes occurring near the surfaces and inside solid
bodies interacting with active plasma. Erosion electrodes,
insulators, and other constructional elements, which are
bombarded with accelerated particles, decrease the operating
life of the engine [1]. To increase operating life resource it is
necessary to take measures for thermo insulation of plasma
that forced us to provide several power supply sources for
engines, and high voltage sources among them.
These drawbacks are less specific for RF reactive engines
for which specific pulse increases due to heating of the
working substance through RF energy transfer from an
external source. Energy from the external source is
transformed into thermal ion energy, and the latter –“gas
dynamically” is transformed into energy of accelerated motion
of the working substance. That is, energy from the external
source first is transmitted to electrons. Therefore, in the gas
discharge chamber it is necessary to form the conditions for
transfer of energy from electrons to ions by means of electron-
ion interactions.
With estimation of these conditions it is necessary to take
into consideration, that most efficient transfer of RF energy
from an external source to plasma electrons occurs on
frequencies ω much less than frequencies of elastic
interactions υm, but higher than electron plasma frequency ωp,
and the most probable way of energy transfer to ions is elastic
interaction between electrons and ions. At a single elastic
interaction electron transfer a small part of its energy ε, of the
order of electron mass m to ion mass M ratio, gained in the
electric field. Consequently, to transfer all amount of energy a
large number of interactions, of the order of M/m, is
necessary. Thus, ratio of characteristic sizes of the gas
discharge chamber L to the electron free path λei should be no
less than M/m. Taking into account, that λei=1/n.σei, where n
is ion density, and σei is electron elastic cross section on ions,
we would obtain the estimation of the lower limit for density
n ≥ M/mL.σei
With the characteristic sizes L – 10cm, and electron
temperature Te – (1-10)eV the plasma density should be
no less than (1014 – 1016)cm-3. From the other hand, the
plasma density should be so that during the time between
collisions electron would compensate the energy loss, i.
e., the product λei.e.Eeff, where e is electron charge, Eef –
effective value of electric field, should be of the order of
m/M . ε , the value of energy transferred by electron. From
that we would obtain the upper limit of density.
n ≤ eEeff/σei
. M/m . ε
When the electric field strength Eeff is of the order of
100V/cm and electron energy ε is about (1-10)eV, plasma
density should not exceed (1015 - 1017)cm-3. Thus,
“thermal” acceleration of ions is possible in a rather
narrow range of densities.
(1014 – 1016) cm-3 ≤ n ≤ (1015 – 1017) cm-3 .
With these densities, for heating plasma electromagnetic waves
are most effective with frequencies ω>109 Hz. In this frequency
range cavities of different types are used, in which accumulation
of RF energy occurs. However, application of cavities as a base
for construction of the engine ionization chamber is under
question. In the cavity adjusted to a certain frequency, after
ignition of the discharge additional conductivity arises that leads
to alteration of self-resonance frequency and its Q-factor. Power
absorbed with plasma depends both on the value of
mismatching, and on adjusting in frequency. Thus, for
optimization of engine efficiency it is necessary to tune the RF-
generator additionally or to regulate the parameters of the engine
itself with each start-up. That would complicate the construction
and, as a result, would increase the cost of thrust. Another
150 Problems of Atomic Science and Technology. 2003. № 1. Series: Plasma Physics (9). P. 150-152
problem is associated with creation of compact and light
generators of sufficient thrust in this frequency range.
The goal of the present work is continuation of studies
connected with development of a compact RF frequency engine
for stabilization and correction of the orbit, which could operate
in the frequency range of (107 - 108) Hz with operating life no
less than 15 years.
THE EXPERIMENTAL INSTALLATION AND
MEASURING PROCEDURES
A number of trial experiments [2] allowed us to optimize the
engine model construction add to choose measuring procedures.
To carry out studies two model engines were manufactured.
One of the module, 50cm in length and 10cm in diameter
operated on the frequency of 80 MHz and was meant for
investigation of parameters of discharge in the chamber. The
second one, somewhat smaller in sizes, operated on the
frequency of 120 MHz and was adapted for arrangement of a
thrust meter in the operating volume of the test bench. The
choice of frequency range was due to availability of a large base
of semiconductor elements operating in this range that makes it
possible to create compact generators of the required power. As
a base for ionization cavity chamber construction was chosen a
section of coaxial line with the wave resistance of 75 Ω (Fig.1).
Fig.1. Scheme of ionization cavity chamber
One of the ends of the coaxial line was open and was a
shortening capacitance with a nozzle. The other end of the
chamber was provided with a conical transition to a coaxial line
of a smaller diameter ended RF socket with wave resistance of
75 Ω, through which power from RF generator was supplied to
resonator chamber. In such construction the maximum electric
field strength always lies at the open end of the cavity. After
ignition when resistance and frequency of the cavity change,
maximum of the current moves along the coaxial line.
However, if the value of the shortening capacity and dimensions
of the cavity chamber are chosen to be so that maximum current
in the “empty” cavity and after ignition of the discharge lies
inside the construction, then into the ionization chamber there
always be an area, that is a quarter wave cavity for the given
generator frequency. Thus, after ignition of the discharge, the
“automatic” adjusting of the ionization chamber into resonance
mode occurs.
The models were supplied with systems of vacuum pumping,
of gas injection, electric probes, vacuum electrostatic sockets,
and they were placed in the vacuum chamber with the residual
pressure of 10-5mm Hg. The models of the engines and the
vacuum chamber were pumped off to the residual pressure, and
then with a gas injection valve the pressure required for the
experiments is established, the RF generator were switched on,
and after that the necessary measurements were performed. The
consumption of the working substance was not controlled when
measuring the plasma parameters.
The power applied to the discharge was controlled at the RF
socket of the module upon the difference in energies of incident
and reflected waves. The energies of the incident and reflected
waves were determined with power gauge. The voltage of the
discharge ignition was measured with a special voltmeter. It was
assumed that on frequencies of 108 Hz connections a probe of
the voltmeter having the wave resistance of 75 Ω, large input
resistance and low input capacitance does not affect the
distribution of the electric field along the coaxial line of the
module.
The plasma density and temperature were measured upon
volt-current characteristics of the electric probe. The
measurements of the thrust were performed at the special-
purpose test bench at the Kharkov Aero-Space University
“KhAU”. The test bench was intended for integrated
investigations of electro rocket engines and engine installations
on their base.
The basis of the test bench is a device for measuring the
thrust placed in the vacuum chamber with the operating volume
of 10 m3 and with the limit residual pressure of 4.5.10-6 mm Hg
and the pumping rate of 40 m3/s. The test bench is provided
with automated system for control processing and displaying of
the data. The mechanical part of the device for measuring the
thrust is a beam fixed on three thread stems. The electric part of
the device is fabricated on the technical base of “MicroDAT”.
Connect with the complex for the data processing and
displaying is performed with a RS–232 interface. The test bench
provides the thrust measuring in the range from 0 to 6500 mg
with the scaled error of 0.5%.
THE RESULTS OF THE MEASUREMENTS
As the working bodies hydrogen, helium and nitrogen were
used. The measurements were performed in the pressure range
(10 – 10-2)mm Hg. The power supplied to the modules was
altered from 30 to 500 W. In the Fig.2 the typical
dependencies of the ignition voltage on the pressure in the
ionization chamber are given.
Fig. 2. The typical dependencies of the ignition voltage
on the pressure. (▲-hydrogen,■-helium,•-nitrogen)
The ignition voltage in the pressure range of 5.10-1mm Hg
has a minimum near 170V and, practically, does not
depend on the sort of the gas.
The electron temperature within the experimental error is the
same over the all range of pressure, up to 5mm Hg, does not
depend on the sort of the gas, slightly rises with the supplied
power and comprises 3 – 4 eV. The typical dependencies
density versus pressure for different supplied energies is
shown in the Fig.3. The electron density is almost proportional
to the pressure op the operating gas and practically does not
depend on the value of the supplied power. The value of the
151
0.01 0.10 1.00 10.00
P, mm Hg
V ef
f,
v
102
103
thrust after the discharge ignition rose by 25 – 33% with
change of the supplied power from 100W to 250W and was
equal to 70 – 80 mg.
Fig. 3.The typical dependencies density versus pressure:
(• - 100W, ▲- 150W, ■ – 200W)
DISCUSSION OF THE RESULTS
Within the typical range of value of external parameters,
plasma in the ionization chamber is under affects of standing
electromagnetic wave with the frequency υE less than
frequency of elastic collisions υm. So, it is a case of low
frequency (υm > ω), though discharge occurs on high
frequencies ω. The electron free path and their amplitude of
oscillations in the RF field are less than the chamber
dimensions. The electron motion is completely diffuse in
nature, and the main process of energy transfer to ions is
elastic interaction between electrons and ions. Estimations
show that practically over the all range of the external
parameters, the time of electron energy leveling off is one or
two order less then the time of energy transfer to ions. That is,
electron distribution in energies is Maxwellian. The shape of
volt-current characteristics of the probe testifies that indirectly.
The theory of the electric probe accounting collisions still has
not completely obvious simplifying assumptions.
Nevertheless, obtained values of density and temperature can
be interpreted as typical for RF discharges with drifting
electron motion and discharge currents of several tens of
milliampers.
The main differences of the investigated discharge from the
typical are: slight dependence of electron density and pressure
on the value of supplied power, and independence of ignition
voltage on the sort of gas.
Apparently, the first difference can be explained by
blowing through the discharge of a neutral gas. On the stream
of the gas the discharge is stabilized at the less values of
density and temperature, and a part of energy supplied to
plasma is expended on raise of the thrust. The raise in the
thrust with increasing supplied power confirms this
assumption.
The second difference is associated with peculiarities of the
cavity chamber construction. In the area of the cone shortening
capacitance the chamber has alternating cross section, thus the
distance between electrodes changes, and the discharge can be
ignited at the optimum values of pressure p and value of the
discharge gap d.
CONCLUSIONS
The experiments carried out on the model engine, where a
section of the coaxial line of the proper sizes with shortening
capacitances of proper values was used as an ionization cavity
chamber, show that in such construction discharge is possible
on frequencies about 108 Hz. Direct measurements of thrust
confirmed efficiency of transformation of energy from
external source in internal energy of the working substance.
The simplicity of the construction and possibility to create
compact generators of sufficient power in the used frequency
range give us assurance in good prospects of future
investigations in the given direction.
REFERENCES
1. N.V.Belan,V.P.Kim, A.I.Orlansky, V.B.Tikhonov.
Stationary plasma jet. Kharkov air-space university, 1989
(in Russian).
2. B.V. Zajtzev, V.A. Bomko, J.P. Masalov, A.F. Kobetz,
V.M. Rashkovan, B.I. Rudiak.. RF plasma reactive engine//
Problems of atomic science and technology. №4(78),2000,
p.180-181.
ДОСЛІДЖЕННЯ ПАРАМЕТРІВ РОБОЧОГО ТІЛА – НИЗЬКОТЕМПЕРАТУРНОЇ ПЛАЗМИ В
ІОНІЗАЦІЙНІЙ КАМЕРІ-РЕЗОНАТОРІ ВИСОКОЧАСТОТНОГО РЕАКТИВНОГО ДВИГУНА
С.О. Вдовін, Б.В. Зайцев, А.О. Бомко, А.Ф. Кобець, Б.І. Рудяк, М.С. Лесних, В.Г. Журавльов,
В.М. Рашкован, Л. О. Базима, О.В. Бастєєв, В.І. Белоконь
Представлена робота продовжує дослідження НВЧ – двигуна, призначеного для орієнтації та стабілізації орбіти космічних
апаратів, й виконана з метою виміряти параметри плазми НВЧ – розряду в іонізаційній камері – резонаторі двигуна.
Експерименти проводились з частотою 80 МГц на макеті двигуна, в якому в якості іонізаційної камери використовувався
відрізок коаксиальної лінії зі скорочуваючими ємностями на кінцях. В експериментах вивчені умови запалювання НВЧ –
розряду в камері–резонаторі, отримані залежності густини та температури плазми від прикладеної потужності та тиску
робочого тіла для різних газів. На спеціалізованому випробному стенді були проведені вимірювання тяги. Отримані
результати дозволяють зробити висновок про перспективність подальших досліджень у цьому напрямку.
ИССЛЕДОВАНИЕ ПАРАМЕТРОВ РАБОЧЕГО ТЕЛА - НИЗКОТЕМПЕРАТУРНОЙ ПЛАЗМЫ В
ИОНИЗАЦИОННОЙ КАМЕРЕ – РЕЗОНАТОРЕ ВЫСОКОЧАСТОТНОГО РЕАКТИВНОГО ДВИГАТЕЛЯ
С.А. Вдовин, Б.В. Зайцев, В.А. Бомко, А.Ф. Кобец, Б.И. Рудяк, М.С. Лесных, В.Г. Журавлев, В.М. Рашкован,
Л.А. Базыма, А.В. Бастеев, В.И. Белоконь
Настоящая работа является продолжением исследований СВЧ – двигателя предназначенного для ориентации и
стабилизации орбиты космических аппаратов и предпринята с целью измерения параметров плазмы СВЧ – разряда в
ионизационной камере – резонаторе двигателя. Эксперименты проводились на частоте 80 МГц на макете двигателя, в
котором в качестве ионизационной камеры – резонатора использовался отрезок коаксиальной линии с
укорачивающими емкостями на концах. В экспериментах изучены условия зажигания СВЧ разряда в камере -
резонаторе, получены зависимости плотности и температуры плазмы от приложенной мощности и давления рабочего
152
0.01 0.10 1.00 10.00
P, mm Hg
n,
sm
-3
1010
109
1011
1012
тела для различных газов. На специализированном испытательном стенде были проведены измерения тяги.
Полученные данные позволяют сделать вывод о перспективности дальнейших исследований в этом направлении.
153
NSC "Kharkov Institute of Physics and Technology”;
Setting up the problem
The experimental installation and measuring procedures
Fig.1. Scheme of ionization cavity chamber
The results of the measurements
Discussion of the results
Conclusions
References
|
| id | nasplib_isofts_kiev_ua-123456789-110613 |
| institution | Digital Library of Periodicals of National Academy of Sciences of Ukraine |
| issn | 1562-6016 |
| language | English |
| last_indexed | 2025-12-07T15:38:47Z |
| publishDate | 2003 |
| publisher | Національний науковий центр «Харківський фізико-технічний інститут» НАН України |
| record_format | dspace |
| spelling | Vdovin, V.S. Zajtzev, B.V. Kobetz, A.F. Rudiak, B.I. Bomko, V.A. Lesnykh, M.S. Zhuravlev, V.G. Rashkovan, V.M. Bazyma, L.A. Basteev, V.A. Belokon, V.I. 2017-01-05T18:53:58Z 2017-01-05T18:53:58Z 2003 Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine / V.S. Vdovin, B.V. Zajtzev, A.F. Kobetz, B.I. Rudiak, V.A. Bomko, M.S. Lesnykh, V.G. Zhuravlev, V.M. Rashkovan, L.A. Bazyma, V.A. Basteev, V.I. Belokon // Вопросы атомной науки и техники. — 2003. — № 1. — С. 150-152. — Бібліогр.: 2 назв. — англ. 1562-6016 PACS: 52.75.-d https://nasplib.isofts.kiev.ua/handle/123456789/110613 This paper is the extension of investigations of the RF engine designed for orientation and stabilization of the spacecrafts orbit, and it is undertaken for measuring of plasma parameters of RF discharge in the ionization resonator chamber. The experiments were performed at the frequency of 80 MHz on the model engine, in which a length of coaxial line with shortening capacities at the ends was used as the ionization resonator chamber. As the result of the experiments, conditions of the RF discharge ignition in the resonator chamber are studied; dependencies of plasma density and temperature versus applied power and working body pressure are obtained for various gases. The measurements of the thrust were performed at the special-purpose test bench. The data obtained allow making a conclusion that further investigations in this direction hold much promise. Представлена робота продовжує дослідження НВЧ – двигуна, призначеного для орієнтації та стабілізації орбіти космічних апаратів, й виконана з метою виміряти параметри плазми НВЧ – розряду в іонізаційній камері – резонаторі двигуна. Експерименти проводились з частотою 80 МГц на макеті двигуна, в якому в якості іонізаційної камери використовувався відрізок коаксиальної лінії зі скорочуваючими ємностями на кінцях. В експериментах вивчені умови запалювання НВЧ – розряду в камері–резонаторі, отримані залежності густини та температури плазми від прикладеної потужності та тиску робочого тіла для різних газів. На спеціалізованому випробному стенді були проведені вимірювання тяги. Отримані результати дозволяють зробити висновок про перспективність подальших досліджень у цьому напрямку. Настоящая работа является продолжением исследований СВЧ – двигателя предназначенного для ориентации и стабилизации орбиты космических аппаратов и предпринята с целью измерения параметров плазмы СВЧ – разряда в ионизационной камере – резонаторе двигателя. Эксперименты проводились на частоте 80 МГц на макете двигателя, в котором в качестве ионизационной камеры – резонатора использовался отрезок коаксиальной линии с укорачивающими емкостями на концах. В экспериментах изучены условия зажигания СВЧ разряда в камере - резонаторе, получены зависимости плотности и температуры плазмы от приложенной мощности и давления рабочего тела для различных газов. На специализированном испытательном стенде были проведены измерения тяги. Полученные данные позволяют сделать вывод о перспективности дальнейших исследований в этом направлении. en Національний науковий центр «Харківський фізико-технічний інститут» НАН України Вопросы атомной науки и техники Low temperature plasma and plasma technologies Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine Дослідження параметрів робочого тіла – низькотемпературної плазми в іонізаційній камері-резонаторі високочастотного реактивного двигуна Исследование параметров рабочего тела - низкотемпературной плазмы в ионизационной камере – резонаторе высокочастотного реактивного двигателя Article published earlier |
| spellingShingle | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine Vdovin, V.S. Zajtzev, B.V. Kobetz, A.F. Rudiak, B.I. Bomko, V.A. Lesnykh, M.S. Zhuravlev, V.G. Rashkovan, V.M. Bazyma, L.A. Basteev, V.A. Belokon, V.I. Low temperature plasma and plasma technologies |
| title | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine |
| title_alt | Дослідження параметрів робочого тіла – низькотемпературної плазми в іонізаційній камері-резонаторі високочастотного реактивного двигуна Исследование параметров рабочего тела - низкотемпературной плазмы в ионизационной камере – резонаторе высокочастотного реактивного двигателя |
| title_full | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine |
| title_fullStr | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine |
| title_full_unstemmed | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine |
| title_short | Investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the RF reactive engine |
| title_sort | investigation of parameters of the working substance - low temperature plasma in the ionization resonator chamber of the rf reactive engine |
| topic | Low temperature plasma and plasma technologies |
| topic_facet | Low temperature plasma and plasma technologies |
| url | https://nasplib.isofts.kiev.ua/handle/123456789/110613 |
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