Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Results of reliability design and technological analysis of the nose fairing pusher

Published: 23.05.2023

Authors: Pokhabov Yu.P., Kaverin V.A., Belov M.V., Ermilova D.S., Saparbaeva E.R.

Published in issue: #5(137)/2023

DOI: 10.18698/2308-6033-2023-5-2273

Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft

The paper considers results of test application of the reliability design and technological analysis (RDTA) for the nose fairing pusher of the aerial vehicle. The methodology procedures allow the designer to justify his decisions from the early stages of the life cycle making it possible to timely identify possible causes of the potential failures and take the necessary measures to eliminate or mitigate their consequences. The methodology is intended mainly to analyze the highly responsible unique products; however, it is not yet widely used in the rocket and space technology due to its novelty, and the regulatory framework is missing. To test the methodology, one of the mechanisms for the aerial vehicle one-time response was selected, i. e. the nose fairing pusher, which went through a full cycle of analytical and experimental verification according to the organization standards, and was approved for operation. Despite positive results of the pusher regular testing, the analysis revealed structural elements in it that required measures to improve reliability. An important result of the RDTA application was that the designers did not perceive results of the analysis as criticism, which is typical, for example, when using the FMEA procedures, but regarded them as an integral part of the design work. Despite the received specific recommendations to improve the pusher reliability, it turned out that the RDTA methodology needs further development and improvement for using by a wide range of designers and specialists, and it is also necessary to develop guidelines or standards for application in the standard organization developments.

[1] Space Vehicle Mechanisms: Elements of Successful Design. Edited by P.L. Conley. NJ, John Wiley & Sons, 1998, 794 р.
[2] Spacecraft Structures and Mechanisms: From Concept to Launch. Edited by T.P. Sarafin. NJ, Springer, 1995, 868 p.
[3] Fowler R.M., Howell L.L., Magleby S.P. Compliant space mechanisms: a new frontier for compliant mechanisms. Mechanical Sciences, 2011, no. 2, pp. 205–215.
[4] Bezruchko K.V., Gaydukov V.F., Gubin S.V., Dranovskii V.I., Karpov Ya.S., Turkin I.B. Solnechnyye batarei avtomaticheskikh kosmicheskikh apparatov (komponovka na KA, konstruktsiya uzlov, proektirovochnye raschety) [Solar panels for automatic spacecraft (spacecraft layout, assembly design, design calculations)]. Kharkiv, KhAI Publ., 2011, 276 p.
[5] Efremov G.A., Kiselev A.I., Leonov A.G., Kharlamov I.V. Yarkiy sled krylatogo «meteorita» [A bright trail of the winged meteorite]. Moscow, Bedretdinov i Ko Publ., 2012, 248 p.
[6] Pokhabov Yu.P. Teoriya i praktika obespecheniya nadezhnosti mekhanicheskikh ustroystv odnorazovogo srabatyvaniya [Theory and practice of ensuring the need for mechanical devices of one-time response]. Krasnoyarsk, SFU Publ., 2018, 338 p.
[7] Kolobov A.Yu., Dikun E.V. Intervalnye otsenki bezotkaznosti edinichnykh kosmicheskikh apparatov [Interval estimates of the reliability of individual spacecraft]. Nadezhnost — Dependability, 2017, vol. 17, no. 4, pp. 23–26.
[8] Isaev S.V. Takoy FMEA nam ne nuzhen! (problemy pri vnedrenii i “detskie oshibki” [We don’t need such an FMEA! (Problems during implementation and “childish” errors)]. Metody menedzhmenta kachestva — Methods of Quality Management, 2008, no. 3, pp. 30–32.
[9] Pokhabov Yu.P. Konstruktorsko-tekhnologicheskiy analiz nadezhnosti [Design and technological analysis of reliability]. Krasnoyarsk, SFU Publ., 2022. Available at: (accessed February 20, 2023).
[10] Shestakov S.A., Zemskov V.A., Goryaev A.N. Ustroystvo razdeleniya i sbrosa golovnogo obtekatelya rakety-nositelya [The device for separating and dropping the head fairing of the launch vehicle]. Patent 2568965 Russian Federation, MPC B 64G 1/64, F42B 15/36. Published November 20, 2015, bull. no. 32.