Search Results for “superelastic deformation” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Wed, 06 Nov 2024 11:41:22 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “superelastic deformation” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses https://journal.yuzhnoye.com/content_2023_1-en/annot_8_1_2023-en/ Fri, 12 May 2023 16:11:05 +0000 https://test8.yuzhnoye.com/?page_id=26992
Unlike metal showing two types of deformation (elastic and plastic), rubber can exhibit three types of deformation (elastic, superelastic and plastic). In the process of interface design, we took into account two types of deformations (elastic and superelastic ones). Key words: orifice of the launch vehicle , corrugated rubber hose , lock/release assembly , superelastic deformation , leaktightness Bibliography: 1. orifice of the launch vehicle , corrugated rubber hose , lock/release assembly , superelastic deformation , leaktightness .
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8. Specificity of developing pyrobolts with low impact and vibration impulse responses

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 70-76

DOI: https://doi.org/10.33136/stma2023.01.070

Language: Ukrainian

Annotation: One of the systems in the integrated launch vehicle responsible for prelaunch processing and launch is a ground thermal conditioning system, which supplies the low-pressure air into the launch vehicle’s “dry” compartments. Thermal conditioning system is mated with the launch vehicle, using the mating interfaces, proper functioning of which enhances reliability of the ground support equipment, the launch vehicle and the entire space launch system. The article describes key requirements to the interfaces of the thermal conditioning system and the drawbacks of the existing designs. The article proposes a new design concept of the interface that connects the pipeline of the ground thermal conditioning system to the orifice of the launch vehicle using the corrugated rubber hose composed of three basic parts, attached with the help of a metal lock/release assembly. The proposed solution provides reliable leaktightness, ease of operation, providing multiple connections to the launch vehicle, including at various angles, and automatic disconnection by rocket motion or manual removal in case of launch abort. Using rubber as a high-elasticity structural material to manufacture the hoses, enabled minimization of efforts required to disconnect the interface from the launch vehicle. In its high-elasticity state, rubber can absorb and dissipate mechanical energy within a wide range of temperatures, which prevents transmission of engine vibrations to the ground thermal conditioning system. The article presents key properties of rubber used as a structural material and its peculiarities to be considered during design of similar products. Unlike metal showing two types of deformation (elastic and plastic), rubber can exhibit three types of deformation (elastic, superelastic and plastic). In the process of interface design, we took into account two types of deformations (elastic and superelastic ones). Experimental studies of the interface showed its full compliance with technical specification.

Key words: orifice of the launch vehicle, corrugated rubber hose, lock/release assembly, superelastic deformation, leaktightness

Bibliography:
1. Pat. Ukrainy na korycnu model «Pirobolt» №138414. Shevtsov E.I., Voloshin V.V., Samoilenko I.D. Onofrienko V.I., Bezkorsiy D.M. MPK F42B 15/36, F42В 15/38, B64G 1/22 zayavnik ta patentovlasnik KB «Pivdenne». Byul. №22, 2019 r.
2. Galuzeviy standart «Pyrozamky. Metodika rozrakhunku» OST 92-9594-82, 24 ark.
3. Duplischeva O.M., Kononets P.I., Lisoviy A.M., Maschenko A.M., Mikhailov K.F., kand. tekhn. nauk Porubaimekh V.I., Sviridov V.M. Znizhennya vibroimpulsnykh navantazhen, scho vynykaut pid chas spratsyuvannya pyromechanismu. Kosmichna technika. Raketne ozbroennya: Zb. nauk.-techn. st. 2009. Vyp. 2. Dnipro: DP «KB «Pivdenne». 100 ark.
4. Bement L. J. and Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification, NASA, NASA Technical Memorandum 110172, 1995.
5. Yanhua Li, Yuan Li, Xiaogan Li, Yuquan Wen, Huina Mu and Zhiliang Li. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt, Shock and Vibration Vol. 2017, Article ID 3846236, 9 p. https://doi.org/10.1155/2017/3846236
6. Yanhua Li, Jingcheng Wang, Shihui Xiong, Li Cheng, Yuquan Wen, and Zhiliang Li Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt, Shock and Vibration, Vol. 2019, Article ID 2092796, 18 p. https://doi.org/10.1155/2019/2092796
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8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses

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