Zobrazeno 1 - 3
of 3
pro vyhledávání: '"D. M. Yagodnikov"'
Publikováno v:
Aèrokosmičeskij Naučnyj Žurnal, Vol 1, Iss 05, Pp 12-25 (2015)
Aèrokosmičeskij Naučnyj Žurnal, Vol 1, Iss 05, Pp 12-25 (2016)
Aèrokosmičeskij Naučnyj Žurnal, Vol 1, Iss 05, Pp 12-25 (2016)
This article deals with the problems of creating a reducing gas generator of the liquid rocket engine (LRE) of upper stage using advanced fuel components, namely oxygen + liquid natural gas. Relevance of the work is justified by the need to create an
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=dedup_wf_001::a2b3e7b72a362e1eef0f4322be648317
http://aerospace.elpub.ru/jour/article/view/25
http://aerospace.elpub.ru/jour/article/view/25
Autor:
D. M. Yagodnikov, A. A. Dorofeev
Publikováno v:
Nauka i Obrazovanie, Vol 0, Iss 5, Pp 29-40 (2016)
The paper studies the emerging hallmarks and the characteristics of a two-parameter chemical non-equilibrium structure of the combustion products of liquid propellants as applied to the low-thrust liquid propellant engines (LT LPE) operating in the a
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::c77428a66266b50dff36c79b63516336
https://doi.org/10.7463/0516.0841540
https://doi.org/10.7463/0516.0841540
Publikováno v:
Nauka i Obrazovanie, Vol 0, Iss 10, Pp 161-170 (2015)
To ensure a high specific impulse of the LRE (liquid-propellant engine) chamber it is necessary to have optimally organized combustion of the fuel components. This can be ensured by choosing the optimum geometry of gas-dynamic contour of the LRE comb
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::b3bfeeae6df84b72ab1440c96b34e9d2
https://doi.org/10.7463/1015.0813334
https://doi.org/10.7463/1015.0813334