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17. Modeling of Solid Rocket Motor Starting Process

Authors:

Tikhaya M. V.1, Bucharsky V. L.2, Orekhov K. M.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2016 (1); 105-109

Language: Russian

Annotation: In this article was examined starting process of solid rockets motor (SRM) and built computational model of parameters SRM at the time of starting. A result from this model shows acceptable concordance with experimental data and calculations by standard methods

Key words:

Bibliography:

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17.1.2016 Modeling of Solid Rocket Motor Starting Process
17.1.2016 Modeling of Solid Rocket Motor Starting Process
17.1.2016 Modeling of Solid Rocket Motor Starting Process
]]> 11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation https://journal.yuzhnoye.com/content_2016_1/annot_11_1_2016-en/ Tue, 23 May 2023 13:06:36 +0000 https://journal.yuzhnoye.com/?page_id=27621
, Moroz V. , Tikhaya M. 2016 (1); 68-75 Language: Russian Annotation: The factors are considered that have an impact on the value and behavior of SRM flow rate and thrust characteristics after stage separation (in the leg of deep decay). The dependences are proposed for design evaluation of SRM intra-ballistic and flow rate/thrust characteristics. P., Moroz V. G., Tikhaya M. P., Moroz V. G., Tikhaya M. quot;Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation", Космическая техника. Missile armaments, vol. P., Moroz V. G., Tikhaya M. P., Moroz V. G., Tikhaya M. P., Moroz V. G., Tikhaya M. P., Moroz V. G., Tikhaya M. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX на сайт ДП «КБ «Південне»
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11. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation

Authors:

Ushkin M. P., Moroz V. G., Tikhaya M. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 68-75

Language: Russian

Annotation: The factors are considered that have an impact on the value and behavior of SRM flow rate and thrust characteristics after stage separation (in the leg of deep decay). It is shown that thrust behavior in the leg of deep decay is determined by two main processes: afterburning of solid propellant charge residues within the first 3-5 s and mass input of internal thermal protection coating destruction products within the following several tenths of second. The dependences are proposed for design evaluation of SRM intra-ballistic and flow rate/thrust characteristics.

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11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
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