Íàöèîíàëüíûé
àýðîêîñìè÷åñêèé óíèâåðñèòåò èì. Í.Å. Æóêîâñêîãî “Õàðüêîâñêèé àâèàöèîííûé
èíñòèòóò”
ISSN
1727-7337. À²ÀÖ²ÉÍÎ-ÊÎÑ̲×ÍÀ ÒÅÕͲÊÀ ² ÒÅÕÍÎËÎòß. – 2014. – ¹ 8
(115). – 191 ñ.
ISSN
1727-7337. ÀÂÈÀÖÈÎÍÍÎ-ÊÎÑÌÈ×ÅÑÊÀß ÒÅÕÍÈÊÀ È ÒÅÕÍÎËÎÃÈß. – 2014. – ¹ 8 (115). –
191 ñ.
ISSN
1727-7337. AEROSPACE TECHNIC AND TECHNOLOGY. – 2014. – ¹ 8 (115). – 191 ñ.
Ìàòåðèàëû, ñîäåðæàùèåñÿ â æóðíàëå,
îïóáëèêîâàíû
ïî ðåøåíèþ XIX ìåæäóíàðîäíîãî êîíãðåññà äâèãàòåëåñòðîèòåëåé
ÑÒÀÒÜè (articleS)
Àâòîðû |
Íàçâàíèå ñòàòüè (article title) |
Ñòðàíèöû (pages) |
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English |
Óêðà¿íñüêà
ìîâà |
Ðóññêèé
ÿçûê |
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Òåõíîëîãèÿ ïðîèçâîäñòâà ëåòàòåëüíûõ àïïàðàòîâ |
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Ìîçãîâîé Â. Ô., |
UNIFICATION OF
OPERATING PROGRAMS OF PROCESSING DETAILS TURBINE ENGINE ON FIVE-COORDINATE
MACHINE CNC |
ÓͲԲÊÀÖ²ß ÊÅÐÓÞ×ÈÕ ÏÐÎÃÐÀÌ ÎÁÐÎÁÊÈ
ÄÅÒÀËÅÉ ÃÒÄ ÍÀ Ï’ßÒÈÊÎÎÐÄÈÍÀÒÍÈÕ ÂÅÐÑÒÀÒÀÕ Ç ×ÏÊ |
ÓÍÈÔÈÊÀÖÈß
ÓÏÐÀÂËßÞÙÈÕ ÏÐÎÃÐÀÌÌ ÎÁÐÀÁÎÒÊÈ ÄÅÒÀËÅÉ ÃÒÄ ÍÀ ÏßÒÈÊÎÎÐÄÈÍÀÒÍÛÕ ÑÒÀÍÊÀÕ Ñ ×ÏÓ |
6–11 |
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Êàëèíè÷åíêî Í. Þ., |
THE THERMAL
MODEL OF ESTIMATION THERMAL FIELDS BELOW NEAR-SURFACES OF PARTS WHICH
MACHINED BY PLANETARY GRINDING TECHNOLOGY |
ÒÅÏËÎÔ²ÇÈ×ÍÀ ÌÎÄÅËÜ ÐÎÇÐÀÕÓÍÊÓ
ÒÅÌÏÅÐÀÒÓÐÍÈÕ ÏÎË²Â Ó ÏÐÈÏÎÂÅÐÕÍÅÂÈÕ ØÀÐÀÕ ÄÅÒÀËÅÉ ÎÁÐÎÁËÞÂÀÍÈÕ ÇÀ
ÒÅÕÍÎËÎòªÞ ÏËÀÍÅÒÀÐÍÎÃÎ ØË²ÔÓÂÀÍÍß |
12–17 |
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Ñîðîêèí Â. Ô., |
STABILIZATION OF CONTOUR FEEDRATE FOR
THE SPLINE INTERPOLATOR CNC SYSTEM BY HIGH PROCESSING SPEED CRITERION |
ÑÒÀÁ²Ë²ÇÀÖ²ß ÊÎÍÒÓÐÍί
ØÂÈÄÊÎÑÒ²  ÑÏËÀÉÍÎÂÎÌÓ ²ÍÒÅÐÏÎËßÒÎв ÑÈÑÒÅÌÈ ×ÏÓ ÇÀ ÊÐÈÒÅвªÌ
ÂÈÑÎÊί ØÂÈÄÊÎIJ¯ |
18–24 |
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Ïåòðèê È. À., |
PROPERTIES
INCREASEMENT OF WELDING JOINTS OF ROTOR PARTS MADE OF TITANIUM ALLOYS |
ϲÄÂÈÙÅÍÍß ÂËÀÑÒÈÂÎÑÒÅÉ ÇÂÀÐÍÈÕ Ç¢ªÄÍÀÍÜ ÐÎÒÎÐÍÈÕ ÄÅÒÀËÅÉ ²Ç
ÒÈÒÀÍÎÂÈÕ ÑÏËÀ² |
ÏÎÂÛØÅÍÈÅ ÑÂÎÉÑÒÂ
ÑÂÀÐÍÛÕ ÑÎÅÄÈÍÅÍÈÉ ÐÎÒÎÐÍÛÕ ÄÅÒÀËÅÉ ÈÇ ÒÈÒÀÍÎÂÛÕ ÑÏËÀÂÎÂ |
25–29 |
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Ïðîåêòèðîâàíèå àýðîêîñìè÷åñêèõ ëåòàòåëüíûõ
àïïàðàòîâ |
||||||
Ëîñü À. Â. |
CRITERIA OF
EFFECTIVE APPLICATION OF ANTIFRICTIONAL COATINGS IN MOVABLE ULTIMATE AND SKEW
LOADED AIRCRAFT UNITS |
ÊÐÈÒÅв¯ ÅÔÅÊÒÈÂÍÎÑÒ² ÇÀÑÒÎÑÓÂÀÍÍß
ÀÍÒÈÔвÊÖIÉÍÈÕ ÏÎÊÐÈÒÒ²Â
 ÐÓÕÎÌÈÕ ÃÐÀÍÈ×ÍÎ ÒÀ ÊÎÑÎÑÈÌÅÒÐÈ×ÍÎ ÍÀÂÀÍÒÀÆÅÍÈÕ ÂÓÇËÀÕ Ë²ÒÀÊÎÂÈÕ
ÀÃÐÅÃÀҲ |
30–36 |
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Àýðîäèíàìèêà, äèíàìèêà, áàëëèñòèêà è
óïðàâëåíèå ïîëåòîì ëåòàòåëüíûõ àïïàðàòîâ |
||||||
Êîòîâ À. Â., |
AERODYNAMIC
IMPROVEMENT OF RADIAL VANED DIFFUSER OF COMPRESSOR CENTRIFUGAL STAGE |
ÀÅÐÎÄÈÍÀ̲×ÍÅ ÂÄÎÑÊÎÍÀËÅÍÍß
ÐÀIJÀËÜÍÎÃÎ ËÎÏÀÒÊÎÂÎÃÎ ÄÈÔÓÇÎÐÀ ²ÄÖÅÍÒÐÎÂÎÃÎ ÑÒÓÏÅÍß ÊÎÌÏÐÅÑÎÐÀ |
37–43 |
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Äâèãàòåëè è ýíåðãîóñòàíîâêè àýðîêîñìè÷åñêèõ
ëåòàòåëüíûõ àïïàðàòîâ |
||||||
Ïîïóãà À. È., |
SHAPING A
REASONABLE APPEARANCE OF ENGINE - ENGINE NACELLE - AIRCRAFT PYLON SYSTEM BY
USING
COMPUTATIONAL MODELING |
ÔÎÐÌÓÂÀÍÍß ÐÀÖ²ÎÍÀËÜÍÎÃÎ
ÎÁ˲ÊÓ ÑÈÑÒÅÌÈ ÄÂÈÃÓÍ - ÌÎÒÎÃÎÍÄÎËÀ - ˲ÒÀÊÎÂÈÉ Ï²ËÎÍ Ç ÂÈÊÎÐÈÑÒÀÍÍßÌ
×ÈÑÅËÜÍÎÃÎ ÌÎÄÅËÞÂÀÍÍß |
44–49 |
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Êîðîáêî Â. Â., |
FEATURES
START THERMOACOUSTIC ENGINE UNDER CONDITIONS USING LOW-TEMPERATURE THERMAL
ENERGY SOURCE |
ÎÑÎÁÅÍÍÎÑÒÈ
ÇÀÏÓÑÊÀ ÒÅÐÌÎÀÊÓÑÒÈ×ÅÑÊÈÕ ÄÂÈÃÀÒÅËÅÉ
 ÓÑËÎÂÈßÕ ÈÑÏÎËÜÇÎÂÀÍÈß ÍÈÇÊÎÒÅÌÏÅÐÀÒÓÐÍÛÕ ÈÑÒÎ×ÍÈÊΠÒÅÏËÎÂÎÉ ÝÍÅÐÃÈÈ |
50–54 |
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Ìàìåäîâ Á. Ø. |
ÒÍÅ SINGLE THEORY
OF CONTINUOS FLOW PROPULSION. NEW DESTINATION AND WORK PRINCIPAL OF
"ZERO" TURBO-JET COMPRESSORE LOW PRESSURE STEP |
ªÄÈÍÀ ÒÅÎÐ²ß ÐÓØ²¯Â. ÍÎÂÅ ÏÐÈÇÍÀ×ÅÍÍß
ÒÀ ÏÐÈÍÖÈÏ ÐÎÁÎÒÈ "ÍÓËÜÎÂί" ÑÒÓÏÅͲ ÊÎÌÏÐÅÑÎÐÀ ÍÈÇÜÊÎÃÎ ÒÈÑÊÓ
ÒÓÐÁÎÐÅÀÊÒÈÂÍÈÕ ÄÂÈÃÓͲ |
55–60 |
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Ãîðÿ÷êèí Å. Ñ., |
WORKFLOW MODELING
OF THREE STAGE LOW PRESSURE COMPRESSOR OF GAS TURBINE ENGINE |
ÌÎÄÅËÞÂÀÍÍß ÐÎÁÎ×ÎÃÎ ÏÐÎÖÅÑÓ
ÒÐÜÎÕÑÒÓÏÅÍÅÂÎÃÎ ÊÎÌÏÐÅÑÎÐÀ ÍÈÇÜÊÎÃÎ ÒÈÑÊÓ ÃÀÇÎÒÓÐÁ²ÍÍÎÃÎ ÄÂÈÃÓÍÀ |
61–65 |
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Ãðèãîðüåâ Â. À., |
METHODS OF GENERALIZATION AND REPRESENTATION
CHARACHTERISTICS OF AVIATION GAS TURBINES |
ÌÅÒÎÄÈ ÓÇÀÃÀËÜÍÅÍÍß
ÒÀ ÏÎÄÀÍÍß ÕÀÐÀÊÒÅÐÈÑÒÈÊ ÒÓÐÁ²Í
À²ÀÖ²ÉÍÈÕ ÃÒÄ |
ÌÅÒÎÄÛ ÎÁÎÁÙÅÍÈß
È ÏÐÅÄÑÒÀÂËÅÍÈÅ ÕÀÐÀÊÒÅÐÈÑÒÈÊ ÒÓÐÁÈÍ ÀÂÈÀÖÈÎÍÍÛÕ ÃÒÄ |
66–72 |
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Àáäóëèí Ì. Ç., |
PRINCIPLES OF
WORKING PROCEDURE ORGANIZATION OF COMBUSTION CHAMBERS |
ÏÐÈÍÖÈÏÈ ÎÐÃÀͲÇÀÖ²¯ ÐÎÁÎ×ÎÃÎ ÏÐÎÖÅÑÓ
ÊÀÌÅÐ ÇÃÎÐßÍÍß |
73–78 |
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Êðàâ÷åíêî È. Ô., |
MATHEMATICAL MODELS OF ENERGETIC EFFECTIVENESS FOR COMBUSTION CHAMBER
UNIT OF GAS TURBINE ENGINE |
ÌÀÒÅÌÀÒÈ×Ͳ ÌÎÄÅ˲ ÏÀÐÀÌÅÒвÂ
ÅÍÅÐÃÅÒÈ×Íί ÅÔÅÊÒÈÂÍÎÑÒ² ÐÎÁÎÒÈ ÊÀÌÅÐÈ ÇÃÎÐßÍÍß ÃÒÄ |
ÌÀÒÅÌÀÒÈ×ÅÑÊÈÅ
ÌÎÄÅËÈ ÏÀÐÀÌÅÒÐΠÝÍÅÐÃÅÒÈ×ÅÑÊÎÉ ÝÔÔÅÊÒÈÂÍÎÑÒÈ ÐÀÁÎÒÛ ÊÀÌÅÐÛ ÑÃÎÐÀÍÈß ÃÒÄ |
79–83 |
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Ñåðáèí Ñ. È., |
SUPPRESSING
METHODS OF THE PULSATION BURNING IN GASEOUS FUELS GAS TURBINE COMBASTION
CHAMBER |
ÌÅÒÎÄÈ ÇÍÈÆÅÍÍß ²ÍÒÅÍÑÈÂÍÎÑÒ²
ÏÓËÜÑÀÖ²ÉÍÎÃÎ ÃÎвÍÍß Â ÊÀÌÅв ÇÃÎÐßÍÍß ÃÒÄ, ÙÎ ÏÐÀÖÞª ÍÀ ÃÀÇÎÏÎIJÁÍÎÌÓ
ÏÀËȲ |
84–88 |
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Äîëìàòîâ Ä. À., |
SINGLE
HYDROCARBON DROP COMBUSTION IN THE PRESENCE OF STATIONARY ARC |
ÌÀÒÅÌÀÒÈ×ÍÅ ÌÎÄÅËÞÂÀÍÍß ÃÎвÍÍß
ÃÅÒÅÐÎÃÅÍÍί ÑÓ̲ز ÏÐÈ ÄÎÄÀÒÊÎÂ²É ÑÒÈÌÓËßÖ²¯ |
ÌÀÒÅÌÀÒÈ×ÅÑÊÎÅ
ÌÎÄÅËÈÐÎÂÀÍÈÅ ÃÎÐÅÍÈß ÃÅÒÅÐÎÃÅÍÍÎÉ ÑÌÅÑÈ ÏÐÈ ÄÎÏÎËÍÈÒÅËÜÍÎÉ ÑÒÈÌÓËßÖÈÈ |
89–93 |
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Õàëàòîâ À. À., |
UNEVENNESS OF DOUBLE JET FILM COOLING |
ÍÅвÂÍÎ̲ÐͲÑÒÜ ÄÂÎÑÒÐÓÌÅÍÅÂÎÃÎ
Ï˲ÂÊÎÂÎÃÎ ÎÕÎËÎÄÆÅÍÍß |
94–99 |
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Íàçèí Â. È. |
STAND, PILOT PLANT AND METHOD OF EXPERIMENTAL RESEARCHES OF
HYDROSTATODYNAMIC
BEARINGS OF THE
DOUBLED TYPE |
ÑÒÅÍÄ, ÄÎÑ˲ÄÍÀ ÓÑÒÀÍÎÂÊÀ ² ÌÅÒÎÄÈÊÀ
ÄÎÑ˲ÄÍÈÕ ÄÎÑË²ÄÆÅÍÜ Ã²ÄÐÎÑÒÀÒÎÄÈÍÀ̲×ÍÈÕ Ï²ÄØÈÏÍÈʲ ÇÄÂΪÍÎÃÎ ÒÈÏÓ |
100–103 |
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Íàçàðåíêî Þ. Á., |
PARAMETRIC RESONANCE
LOW PRESSURE TURBINE ROTOR WITH THE APPEARANCE OF A GAP ON THE LANDING GIRDLE
SOCK AND SHAFT LPT |
ÏÀÐÀÌÅÒÐÈ×ÍÈÉ
ÐÅÇÎÍÀÍÑ ÐÎÒÎÐÓ ÒÓÐÁIÍÈ ÍÈÇÜÊÎÃÎ
ÒÈÑÊÓ Ó ÂÈÏÀÄÊÓ ÊÎËÈ ª ÇÀÇÎÐ ÏÎÑÀÄÊÎÂÈÕ ÏÎßÑÊI ÍÎÑÊÀ ÍÀ ÂÀËI ÒÍÒ |
104–107 |
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Ïàíàðèí Â. Å., |
PLASMA COATING OF THE EUTEKTIC ALLOY QUASITHREEFOLD
SYSTEM FE-TIB2-CRB2 |
ÏËÀÇÌÎÂÅ ÏÎÊÐÈÒÒß Ç ÅÂÒÅÊÒÈ×ÍÎÃÎ ÑÏËÀÂÓ
ÊÂÀDzÏÎÒвÉÍί ÑÈÑÒÅÌÈ FE-TIÂ2-CRÂ2 |
ÏËÀÇÌÅÍÍÎÅ
ÏÎÊÐÛÒÈÅ ÈÇ ÝÂÒÅÊÒÈ×ÅÑÊÎÃÎ ÑÏËÀÂÀ ÊÂÀÇÈÒÐÎÉÍÎÉ ÑÈÑÒÅÌÛ FE-TIB2-CRB2 |
108–112 |
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Ñàëî Ì. Ï., |
FUEL
PERFORMANCE IMPROVEMENT METHOD OF LPS STAGES |
ÌÅÒÎÄ Ï²ÄÂÈÙÅÍÍß ÅÊÑÏËÓÀÒÀÖ²ÉÍÈÕ
ÕÀÐÀÊÒÅÐÈÑÒÈÊ ÏÀËÈÂÀ ÄËß ÏÐÄ ÊÎÑ̲×ÍÈÕ ÑÒÓÏÅͲ |
ÌÅÒÎÄ ÏÎÂÛØÅÍÈß ÝÊÑÏËÓÀÒÀÖÈÎÍÍÛÕ
ÕÀÐÀÊÒÅÐÈÑÒÈÊ ÒÎÏËÈÂÀ ÄËß ÆÐÄ ÊÎÑÌÈ×ÅÑÊÈÕ ÑÒÓÏÅÍÅÉ |
113–119 |
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Ëàçóòêèí Ã. Â., |
DEVELOPMENT OF ALGORITHM DESIGN
UNLOADING AND SHOCKPROOF DEVICES METAL RUBBER DAMPERS |
ÐÎÇÐÎÁÊÀ ÀËÃÎÐÈÒÌÓ ÏÐÎÅÊÒÓÂÀÍÍß ÐÎÇÂÀÍÒÀÆÓÂÀËÜÍÈÕ
² ÏÐÎÒÈÓÄÀÐÍÈÕ ÏÐÈÑÒÐί ÄËß ÌÅÒÀËÎÃÓÌÎÂÈÕ Â²ÁÐβÇÎËßÒÎв |
120–125 |
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Åðìàêîâ À. È., |
RESEARCH OF INFLUENCE OF VIBRATION
CONNECTEDNESS OF BLADES TO EIGENMODE OF MISTUNED BLADE DISK |
ÀÍÀË²Ç ÂÏËÈÂÓ ÂÅËÈ×ÈÍÈ ÇÂ'ßÇÀÍÎÑÒ²
ÊÎËÈÂÀÍÜ ËÎÏÀÒÎÊ ÍÀ ÐÎÇËÀÄ ÂËÀÑÍÈÕ ÔÎÐÌ ÊÎËÈÂÀÍÜ ÐÎÁÎ×ÈÕ ÊÎËÅÑ, ßʲ
²ÄÕÈËßÞÒÜÑß Â²Ä ÑÒÐÎÃί ÑÈÌÅÒв¯ |
126–130 |
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Êàáàííèê Ñ. Í., |
ALGORITHM FOR IMPLEMENTING THE
EXPRESS-EVALUATION METHOD TO PREDICT THE STABILITY OF COMPRESSOR BLADING
AGAINST SUBSONIC FLUTTER |
ÀËÃÎÐÈÒÌ ÐÅÀ˲ÇÀÖ²¯ ÌÅÒÎÄÓ
ÅÊÑÏÐÅÑ-ÎÖ²ÍÊÈ ÏÐÎÃÍÎÇÓÂÀÍÍß ÑÒ²ÉÊÎÑÒ² ÄÎ ÄÎÇÂÓÊÎÂÎÃÎ ÐÅØ²ÒÊÎÂÎÃÎ ÔËÀÒÅÐÓ
ËÎÏÀÒÊÎÂÈÕ Â²Íֲ ÊÎÌÏÐÅÑÎв |
131–137 |
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Äîâãàíü Ä. Â., |
EFFECT OF RETAINING
PRESSURE TO THE NATURAL FREQUENCIES OF GTE BLADES |
ÂÏËÈ ÂÅËÈ×ÈÍÈ ÇÀÒÈÑÍÅÍÍß ÐÎÁÎ×ÈÕ
ËÎÏÀÒÎÊ ÃÒÄ ÍÀ ×ÀÑÒÎÒÓ ¯Õ ÂËÀÑÍÈÕ ÊÎËÈÂÀÍÜ |
ÂËÈßÍÈÅ ÂÅËÈ×ÈÍÛ
ÇÀÆÀÒÈß ÐÀÁÎ×ÈÕ ËÎÏÀÒÎÊ ÃÒÄ ÍÀ ×ÀÑÒÎÒÓ ÈÕ ÑÎÁÑÒÂÅÍÍÛÕ ÊÎËÅÁÀÍÈÉ |
138–141 |
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Ãîðáåíêî À. Í. |
INFLUENCE OF INERTIAL ANISOTROPY ON THE FORCED OSCILLATIONS OF
UNBALANCED GYROSCOPIC ROTOR |
ÂÏËÈ ²ÍÅÐÖ²ÉÍί ÀͲÇÎÒÐÎϲ¯ ÍÀ
ÂÈÌÓØÅͲ ÊÎËÈÂÀÍÍß ÍÅÂвÂÍÎÂÀÆÅÍÎÃΠòÐÎÑÊÎϲ×ÍÎÃÎ ÐÎÒÎÐÀ |
ÂËÈßÍÈÅ ÈÍÅÐÖÈÎÍÍÎÉ
ÀÍÈÇÎÒÐÎÏÈÈ ÍÀ ÂÛÍÓÆÄÅÍÍÛÅ ÊÎËÅÁÀÍÈß ÍÅÓÐÀÂÍÎÂÅØÅÍÍÎÃÎ ÃÈÐÎÑÊÎÏÈ×ÅÑÊÎÃÎ
ÐÎÒÎÐÀ |
142–147 |
||
Øóëüæåíêî Í. Ã., |
CALCULATION
METHOD FOR TRANSIENT PROCESS IN 3D AXISYMMETRIC CONSTRUCTIONS UNDER IMPULSE LOADING
|
ÌÅÒÎÄÈÊÀ ÐÎÇÐÀÕÓÍÊÓ ÏÅÐÅÕ²ÄÍÈÕ ÏÐÎÖÅѲÂ
 ÒÐÈÂÈ̲ÐÍÈÕ ÎÑÅÑÈÌÅÒÐÈ×ÍÈÕ ÊÎÍÑÒÐÓÊÖ²ßÕ ÏÐÈ ²ÌÏÓËÜÑÍÎÌÓ ÍÀÂÀÍÒÀÆÅÍͲ |
148–151 |
|||
Âîðîáüåâ Þ. Ñ., |
FORCED VIBRATIONS OF COMPRESSOR STAGES OF GAS TURBINE ENGINE IN THE
FLOW |
ÂÈÌÓØÅͲ
ÊÎËÈÂÀÍÍß ÑÒÓÏÅÍß ÊÎÌÏÐÅÑÎÐÀ ÃÒÄ Â ÏÎÒÎÖ² |
152–155 |
|||
Öàãëîâ À. È., |
MECHANISMS
OF PLASMA ACCELERATION IN HELIÑON PLASMA THRUSTER |
ÌÅÕÀͲÇÌÈ ÏÐÈÑÊÎÐÅÍÍß ÏËÀÇÌÈ Ó
ÃÅ˲ÊÎÍÍÎÌÓ ÅÐÄ |
156–159 |
|||
Èíôîðìàöèîííûå òåõíîëîãèè |
||||||
Èãóìåíöåâ Å. À., |
CHARGED
GYROSCOPE MOVEMENT MODEL |
ÌÎÄÅËÜ ÐÓÕÓ ÇÀÐßÄÆÅÍÎÃΠòÐÎÑÊÎÏÓ |
160–164 |
|||
Ëþá÷åíêî Â. Â. |
SYSTEM DATA VISUALIZATION IN AUTOMATED CONTROL SYSTEMS |
ÑÈÑÒÅÌÀ
²ÇÓÀ˲ÇÀÖ²¯ ÄÀÍÈÕ Â ÀÂÒÎÌÀÒÈÇÎÂÀÍ²É ÑÈÑÒÅ̲ ÓÏÐÀÂ˲ÍÍß |
ÑÈÑÒÅÌÀ ÂÈÇÓÀËÈÇÀÖÈÈ
ÄÀÍÍÛÕ Â ÀÂÒÎÌÀÒÈÇÈÐÎÂÀÍÍÛÕ
ÑÈÑÒÅÌÀÕ ÓÏÐÀÂËÅÍÈß |
165–168 |
||
Ìèðãîðîä Â. Ô., |
OPTIMAL CONTROL
BY PIECE-LINEAR DYNAMIC SYSTEMS |
ÎÏÒÈÌÀËÜÍÅ ÓÏÐÀÂ˲ÍÍß
ÊÓÑÎ×ÍÎ-˲ͲÉÍÈÌÈ ÄÈÍÀ̲×ÍÈÌÈ ÑÈÑÒÅÌÀÌÈ |
ÎÏÒÈÌÀËÜÍÎÅ
ÓÏÐÀÂËÅÍÈÅ ÊÓÑÎ×ÍÎ-ËÈÍÅÉÍÛÌÈ ÄÈÍÀÌÈ×ÅÑÊÈÌÈ ÑÈÑÒÅÌÀÌÈ |
169–173 |
||
Òðåòüÿê Â. Â. |
POSSIBILITIES
AND REALIZATION OF OBJECTIVE APPROACH FOR DECISION OF INVENTION TASKS WITH
THE USE OF MODEL RECEPTIONS OF REMOVAL OF CONTRADICTIONS |
ÐÎÇÐÎÁÊÀ
Ó×ÁÎÂÎÃÎ ÏÐÎÃÐÀÌÍÎÃÎ ÊÎÌÏËÅÊÑÓ ÄËß ÂÈвØÅÍÍß ÂÈÍÀÕ²ÄÍÈÖÜÊÈÕ ÇÀÂÄÀÍÜ ÌÅÒÎÄÎÌ ÁÅÇÏÐÎÒÎÒÈÏÍÎÃÎ ÏÐÎÅÊÒÓÂÀÍÍß Â ÎÁËÀÑÒ²
²ÌÏÓËÜÑÍÈÕ ÒÅÕÍÎËÎÃ²É |
174–178 |
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Èíôîðìàöèîííûå òåõíîëîãèè â óïðàâëåíèè
ïðåäïðèÿòèÿìè, ïðîãðàììàìè è ïðîåêòàìè |
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Øîñòàê È. Â., |
APPROACH TO COMPLEX AUTOMATION NATIONAL FORESIGHT PROJECTS |
ϲÄÕ²Ä ÄÎ ÊÎÌÏËÅÊÑÍί ÀÂÒÎÌÀÒÈÇÀÖ²¯ ÍÀÖ²ÎÍÀËÜÍÈÕ ÔÎÐÑÀÉÒ - ÏÐÎÅÊҲ |
ÏÎÄÕÎÄ Ê
ÊÎÌÏËÅÊÑÍÎÉ ÀÂÒÎÌÀÒÈÇÀÖÈÈ ÍÀÖÈÎÍÀËÜÍÛÕ ÔÎÐÑÀÉÒ-ÏÐÎÅÊÒÎÂ |
179–188 |
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190 |
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Óâàæàåìûå ÷èòàòåëè!
Íàó÷íî-òåõíè÷åñêèé
æóðíàë «Àâèàöèîííî-êîñìè÷åñêàÿ òåõíèêà è òåõíîëîãèÿ»
– âõîäèò â óòâåðæäåííûé ÃÀÊ Ïåðå÷åíü íàó÷íûõ ïðîôåññèîíàëüíûõ èçäàíèé
Óêðàèíû, â êîòîðûõ ìîãóò ïóáëèêîâàòüñÿ ðåçóëüòàòû äèññåðòàöèîííûõ ðàáîò íà
ñîèñêàíèå ó÷åíûõ ñòåïåíåé äîêòîðà è êàíäèäàòà íàóê (ñì. ïîñòàíîâëåíèå ïðåçèäèóìà ÂÀÊ Óêðàèíû ¹1-05/4 îò 14.10.2009 ã.);
– ñîõðàíÿåòñÿ â îáùåãîñóäàðñòâåííîé ðåôåðàòèâíîé áàçå
äàííûõ «Óêðà¿í³êà íàóêîâà» è ïóáëèêóåòñÿ â ñîîòâåòñòâóþùèõ òåìàòè÷åñêèõ ñåðèÿõ
óêðàèíñêîãî ðåôåðàòèâíîãî æóðíàëà «Äæåðåëî» (ñâîáîäíûé îí-ëàéíîâûé
äîñòóï ê ðåñóðñàì íà Web-ñåðâåðå http://www.nbuv.gov.ua)
(Óêðàèíà),
– ñîõðàíÿåòñÿ â ðåôåðàòèâíîé áàçå äàííûõ Âñåðîññèéñêîãî èíñòèòóòà
íàó÷íîé è òåõíè÷åñêîé èíôîðìàöèè (ÂÈÍÈÒÈ)
Ðîññèéñêîé àêàäåìèè íàóê è ïóáëèêóåòñÿ â ñîîòâåòñòâóþùèõ òåìàòè÷åñêèõ ñåðèÿõ ÐÆ
(ñâîáîäíûé îí-ëàéíîâûé äîñòóï ê ðåñóðñàì íà Web-ñåðâåðå http://www.viniti.ru) (Ðîññèéñêàÿ Ôåäåðàöèÿ),
– âêëþ÷åí â ìåæäóíàðîäíûå
áèáëèîìåòðè÷åñêèå è íàóêîìåòðè÷åñêèå áàçû äàííûõ: íàó÷íîé ýëåêòðîííîé
áèáëèîòåêè eLIBRARY.RU (Ðîññèéñêàÿ
Ôåäåðàöèÿ); Index Copernicus (Ïîëüøà); Google Scholar.