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Development of method of testing a set of screen-exhaust devices in the helicopter Mi-8MSB-B

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... For conducting experimental studies, the SED set was installed on the Mi-8MSB-B helicopter, Fig. 2. At the stage of flight tests, we experimentally determined the characteristics of IR radiation of the helicopter with a SED kit to assess the degree of reduction in the strength of IR radiation of the engine output devices. The methodology for conducting these studies is given in [16]. ...
... The ranges of input data within which the results are obtained are adequate and can be reproduced, leading to the claimed effects and characteristics of SED. Experimental studies were carried out according to the methodology given in [16]. The tests were carried out in accordance with the tactical and technical characteristics of the SED set under the given conditions of influence of external factors of a natural nature, as well as under the given modes of operation of the test object. ...
... The tests were carried out in accordance with the tactical and technical characteristics of the SED set under the given conditions of influence of external factors of a natural nature, as well as under the given modes of operation of the test object. Work [16] reports available and standard means of on-board measurement of information and their characteristics used in research. ...
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  • M I Arkhipov
  • P I Hrekov
Kulyk, M. S., Arkhipov, M. I., Hrekov, P. I. et. al; Kulyk, M. S. (Ed.) (2013). Dozvukovi hazovi ezhektory ekranno-vykhlopnykh prystroiv HTD. Kyiv: Nats.avia un-t, 142.
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  • O M Sheliakin
  • O P Borysiuk
  • I V Shein
Sheliakin, O. M., Borysiuk, O. P., Shein, I. V. (2016). Obgruntuvannia alhorytmychnykh zavdan suchasnykh analitychnykh zasobiv bortovoho kompleksu oborony litalnykh aparativ. Kharkivskyi Universytet Povitrianykh Syl, 46-50.
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  • K I Kapitanchuk
  • P I Hrekov
  • M P Andriishyn
  • N M Andriishyn
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