Formation of schematic solutions for separation systems of ultrasmall-lift launch vehicles based on architectural modeling and classification of their schematic features

Miniaturization, the growth of the range and quantity of payloads, and increasingly stringent requirements for the timing and accuracy of their placement in orbit have recently led to the intensive development of transport systems based on small-lift and ultrasmall-lift launch vehicles abroad. At the same time, domestic experience and methodological support for the development of small-lift and ultrasmall-lift launch vehicles are virtually nonexistent. Their components are developed using proven designs and calculation methods for medium/heavy-lift launch vehicles, scaling and adapting them, which, when disconnected from the current design context, leads to ineffective solutions. To address this issue, this paper, using the example of the payload fairing separation system of small-lift and ultrasmall-lift launch vehicles, formulates and proposes a method for solving two problems. The first aims to link the external and internal design phases using the Arcadia model-based architectural design methodology in order to develop a formal mechanism for translating high-level requirements for the launch vehicle as a whole to specific requirements for the separation systems. The second objective aims to develop a tool for generating possible design options for the implementation of the separation systems. This work proposes a new S classifier based on the separation systems’ schematic features. The resulting result is planned to be further developed into applied models while maintaining their connection with the conceptual models of higher-level design for the fairing separation system of small-lift and ultrasmall-lift launch vehicles.
EDN: AWLSOG, https://elibrary/awlsog

References

[1] Kulu E. Small launchers — 2023 industry survey and market analysis. 74TH IAC, 2023. URL: https://www.researchgate.net/publication/374557499_Small_Launchers_-_2023_Industry_Survey_and_Market_Analysis (accessed: 15.02.2026).

[2] Frolov K.V. Mashinostroenie. T. IV-22. Kn. 1. Raschet i konstruirovanie mashin [Mechanical engineering. Vol. IV-22. Book 1. Calculation and design of machines]. Moscow, Mashinostroenie Publ., 2012. 924 p. (In Russ.).

[3] Li Y.H., Wang J.C., Xiong S.H. et al. Numerical study of separation characteristics of piston-type explosive bolt. Shock Vib., 2019, vol. 2019, art. 092796, doi: https://doi.org/10.1155/2019/2092796

[4] Mishin V.P., ed. Osnovy proektirovaniya letatelnykh apparatov (transportnye sistemy) [Fundamentals of aircraft design (transport systems).]. Moscow, Mashinostroenie Publ., 1985. 360 p. (In Russ.).

[5] Kondratyev A.V., Chumak A.A., Stenile K.D. Sravnenie sistem krepleniya i otdeleniya sovremennykh kompozitnykh golovnykh obtekateley raket-nositeley [Comparison of attachment and separation systems for modern composite payloads of launch vehicles]. V: Voprosy proektirovaniya i proizvodstva konstruktsiy letatelnykh apparatov [In: Issues of aircraft design and production]. Kharkov, KhAI Publ., 2012, pp. 165–177. (In Russ.).

[6] Olenin I.G. Razrabotka ugleplastikovoy sterzhnevoy sistemy razdeleniya prodolnogo styka golovnykh obtekateley. Diss. kand. tekh. nauk [Development of a carbon-fiber rod system for separating the longitudinal joint of payloads. Kand. tech. sci. diss.]. Moscow, 2001. 106 p. (In Russ.).

[7] Sanchez A., Halter U., Gerngross T. RUAG’s approach to develop a modular low shock separation and jettison system. 8TH EUCASS, 2019, doi: https://doi.org/10.13009/EUCASS2019-745

[8] Karl C., Esteves J., Faber J. et al. Development of low-shock separation systems for payload fairings. 10?? EUCASS – 9?? CEAS, 2023, doi: https://doi.org/10.13009/EUCASS2023-395

[9] Grabin B.V., Davydov O.I., Zhikharev V.I. Osnovy konstruirovaniya raket-nositeley kosmicheskikh apparatov [Fundamentals of designing spacecraft launch vehicles]. Moscow, Mashinostroenie Publ., 1991. 415 p. (In Russ.).

[10] Paukov D.I. [Modern approaches to designing spacecraft systems]. Aviatsiya i kosmonavtika. Tez. 23-ey Mezhd. konf. [Aviation and Cosmonautics. Abs. 23rd Int. Conf.]. Moscow, Pero Publ., 2024, pp. 209–210. (In Russ.).

[11] Kolesnikov K.S., Kokushkin V.V., Borzykh S.V. et al. Raschet i proektirovanie sistem razdeleniya stupeney raket [Calculation and design of rocket stage separation systems]. Moscow, Bauman MSTU Publ., 2006. 376 p. (In Russ.).

[12] Kruglov G.E. Analiticheskoe proektirovanie mekhanicheskikh system [Analytical design of mechanical systems]. Samara, SGAU im. S.P. Koroleva Publ., 2001. 131 p. (In Russ.).

[13] Oh C., Sun B., Park Y. et al. Payload fairing separation analysis using constraint force equation. Int. Conf. on Control, Automation and Systems, 2010. URL: https://www.researchgate.net/publication/251976569_Payload_fairing_separation_analysis_using_constraint_force_equation (accessed: 10.02.2026).

[14] Wang H., Hong J., Meng D. et al. Numerical simulation of the effect of elastic deformation on the fairing separation process. J. Phys.: Conf. Ser., 2023, vol. 2599, art. 012007, doi: https://doi.org/10.1088/1742-6596/2599/1/012007

[15] Tayefi M., Ebrahimi M. Design and analysis of separation systems based on an optimization approach. 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2009, doi: https://doi.org/10.2514/6.2009-436

[16] Borisov V.D. [Problems of designing mechanical separation systems for ultra-light launch vehicles and solutions using digital prototyping methods]. Aviatsiya i kosmonavtika. Tez. 23-ey Mezhd. konf. [Aviation and Cosmonautics. Abs. 23rd Int. Conf.]. Moscow, Pero Publ., 2024, pp. 182–183. (In Russ.).

[17] Lin J., Wang X., Zhao Z. et al. Modeling and experimental study on dynamics of a gas-driven split nut device. Research Square Preprint, 2022, doi: https://doi.org/10.21203/rs.3.rs-2095904/v1

[18] Hold down & release mechanism (HDRM). nyuad-space.github.io: website. URL: https://nyuad-space.github.io/projects/hdrm/ (accessed: 10.02.2026).

[19] Lee M.S., Jo J.U., Tak W.J. et al. Shape memory alloy (SMA) based non-explosive separation actuator (NEA) with a redundant function. Int. J. Precis. Eng. Manuf., 2011, vol. 12, no. 3, pp. 569–572, doi: https://doi.org/10.1007/s12541-011-0072-1

[20] Tibbitts S. High output paraffin actuators: utilization in aerospace mechanisms. The 22nd Aerospace Mechanisms Symposium. NASA, Langley Research Center, 1988. 22 p.

[21] Augustijn J., Grimminck M., Bongers E. et al. Development of nonexplosive low shock (NELS) holddown and release system. 16th European Space Mechanisms and Tribology Symposium, 2015. URL: https://www.esmats.eu/esmatspapers/pastpapers/pdfs/2015/augustijn.pdf (accessed: 10.02.2026).

[22] Lee J., Han J.H. Separation and release devices for aeronautical and astronautical systems: a review. Int. J. Aeronaut. Space Sci., 2025, vol. 26, no. 1, pp. 131–161, doi: https://doi.org/10.1007/s42405-024-00802-9

[23] Kurguzov A.V., Ermakov V.Yu., Tufan A. et al. Conceptual approach to the ball-type locking device application without pyrotechnics in the launch vehicle separation systems. Vestnik MAI [Aerospace MAI Journal], 2024, vol. 31, no. 4, pp. 55–64. URL: https://vestnikmai.ru/publications.php?ID=183584 (In Russ.).

[24] TiNi Frangibolt Actuator. URL: https://www.ebad.com/wp-content/uploads/2021/03/TiNi_Frangibolt_Actuator_released_11-29-21.pdf (accessed: 10.02.2026).

[25] Non-explosively actuated release mechanisms and cell bypass switches. URL: https://cms.nacsemi.com/Images/FeaturedProducts/Eaton_Non-Explosive%20Actuators.pdf (accessed: 02.02.2026).

[26] Pan X., Zhang Y., Lu Y. et al. A reusable SMA actuated non-explosive lock-release mechanism for space application. Int. J. Smart Nano Mater., 2020, vol. 11, no. 1, pp. 65–77, doi: https://doi.org/10.1080/19475411.2019.1711462

[27] Hwang D.-H., Lee J., Han J.-H. et al. Numerical analysis and simplified mathematical modeling of separation mechanism for the ball-type separation bolt. J. Korean Soc. Propuls. Eng., 2016, vol. 20, no. 3, pp. 63–70, doi: https://doi.org/10.6108/kspe.2016.20.3.063

[28] Swaminathan R., Sarojini D., Hwang J. Integrating MBSE and MDO through an extended requirements-functional-logical-physical (RFLP) framework. AIAA AVIATION Forum, 2023, art. 3908, doi: https://doi.org/10.2514/6.2023-3908

[29] Kleiner S., Kramer C. Model based design with systems engineering based on RFLP using V6. In: Smart product engineering. Springer, 2013, pp. 93–102, doi: https://doi.org/10.1007/978-3-642-30817-8_10

[30] Sukhomlin V.A., Romanov V.Yu., Gapanovich D.A. Vvedenie v modelno-orientirovannuyu sistemnuyu i programmnuyu inzheneriyu (MBSSE) [Introduction to model-based systems and software engineering (MBSSE)]. Moscow, MAKS Press Publ., 2024. 672 p. (In Russ.).

[31] Roques P. Systems architecture modeling with the arcadia method. Elsevier, 2017. 292 p.

[32] Gorbachev Ya.G., Platunov A.E., Pinkevich V.Yu. et al. Kiberfizicheskie sistemy. Metody vysokourovnevogo proektirovaniya [Cyber-physical systems. High-level design methods]. Sankt-Peterburg, Un-t ITMO Publ., 2022. 48 p. (In Russ.).

[33] Lazansky C. Refinement of a low-shock separation system. 41th Aerospace Mechanisms Symposium, 2012, pp. 329–343.

[34] NEA® hold down & release mechanisms (HDRM). ebad.com: website. URL: https://www.ebad.com/nea-hold-down-release-mechanisms-hdrm/ (accessed: 29.01.2026).

[35] Lucy M.H., Hardy R.C., Kist E.H. et al. Report on alternative devices to pyrotechnics on spacecraft. 10th Annual AIAA/USU Conference on Small Satellites. NASA Langley Research Center, 1996. 22 p.

[36] 2000785N MkII MLB user manual. PSC by Rocket Lab, 2025. 86 p.