Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating
Само за регистроване кориснике
2020
Аутори
Vidanović, NenadRašuo, Boško
Kastratović, Gordana
Grbović, Aleksandar
Puharić, Mirjana
Maksimović, Katarina
Чланак у часопису (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal-structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multi...disciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic-thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects.
Извор:
Journal of Spacecraft and Rockets, 2020, 57, 3, 510-527Издавач:
- Amer Inst Aeronautics Astronautics, Reston
Финансирање / пројекти:
- Интегритет опреме под притиском при истовременом деловању замарајућег оптерећења и температуре (RS-MESTD-Technological Development (TD or TR)-35011)
- Микромеханички критеријуми оштећења и лома (RS-MESTD-Basic Research (BR or ON)-174004)
DOI: 10.2514/1.A34575
ISSN: 0022-4650
WoS: 000537062000009
Scopus: 2-s2.0-85085690622
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Vidanović, Nenad AU - Rašuo, Boško AU - Kastratović, Gordana AU - Grbović, Aleksandar AU - Puharić, Mirjana AU - Maksimović, Katarina PY - 2020 UR - https://machinery.mas.bg.ac.rs/handle/123456789/3380 AB - The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal-structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multidisciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic-thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects. PB - Amer Inst Aeronautics Astronautics, Reston T2 - Journal of Spacecraft and Rockets T1 - Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating EP - 527 IS - 3 SP - 510 VL - 57 DO - 10.2514/1.A34575 ER -
@article{ author = "Vidanović, Nenad and Rašuo, Boško and Kastratović, Gordana and Grbović, Aleksandar and Puharić, Mirjana and Maksimović, Katarina", year = "2020", abstract = "The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid-structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal-structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid-thermal-structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multidisciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic-thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects.", publisher = "Amer Inst Aeronautics Astronautics, Reston", journal = "Journal of Spacecraft and Rockets", title = "Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating", pages = "527-510", number = "3", volume = "57", doi = "10.2514/1.A34575" }
Vidanović, N., Rašuo, B., Kastratović, G., Grbović, A., Puharić, M.,& Maksimović, K.. (2020). Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating. in Journal of Spacecraft and Rockets Amer Inst Aeronautics Astronautics, Reston., 57(3), 510-527. https://doi.org/10.2514/1.A34575
Vidanović N, Rašuo B, Kastratović G, Grbović A, Puharić M, Maksimović K. Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating. in Journal of Spacecraft and Rockets. 2020;57(3):510-527. doi:10.2514/1.A34575 .
Vidanović, Nenad, Rašuo, Boško, Kastratović, Gordana, Grbović, Aleksandar, Puharić, Mirjana, Maksimović, Katarina, "Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating" in Journal of Spacecraft and Rockets, 57, no. 3 (2020):510-527, https://doi.org/10.2514/1.A34575 . .