Multi-disciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating
Authors
Vidanović, NenadRašuo, Boško

Kastratović, Gordana
Grbović, Aleksandar
Puharić, Mirjana
Maksimović, Katarina
Article (Accepted Version)

American Institute of Aeronautics and Astronautics
Metadata
Show full item recordAbstract
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.
Keywords:
fluid–structure interaction simulation (FSI) / multidisciplinary design optimization (MDO) / thermal–structure interaction / short-range ballistic missileSource:
Journal of Spacecraft and Rockets, 2020, 57, 3, 510-527Publisher:
- American Institute of Aeronautics and Astronautics
Funding / projects:
- Dynamics of hybrid systems with complex structures. Mechanics of materials. (RS-174001)
- Micromechanical criteria of damage and fracture (RS-174004)
Note:
- This is the peer-reviewed version of the article: Nenad Vidanović, Boško Rašuo, Gordana Kastratović, Aleksandar Grbović, Mirjana Puharić and Katarina Maksimović, Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating, Journal of Spacecraft and Rockets 2020 57:3, 510-527, DOI: https://doi.org/10.2514/1.A34575
DOI: 10.2514/1.A34575
ISSN: 0022-4650
WoS: 000537062000009
Scopus: 2-s2.0-85085690622
Institution/Community
IHTMTY - JOUR AU - Vidanović, Nenad AU - Rašuo, Boško AU - Kastratović, Gordana AU - Grbović, Aleksandar AU - Puharić, Mirjana AU - Maksimović, Katarina PY - 2020 UR - https://cer.ihtm.bg.ac.rs/handle/123456789/4057 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 - American Institute of Aeronautics and Astronautics T2 - Journal of Spacecraft and Rockets T1 - Multi-disciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating VL - 57 IS - 3 SP - 510 EP - 527 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 = "American Institute of Aeronautics and Astronautics", journal = "Journal of Spacecraft and Rockets", title = "Multi-disciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating", volume = "57", number = "3", pages = "510-527", doi = "10.2514/1.A34575" }
Vidanović, N., Rašuo, B., Kastratović, G., Grbović, A., Puharić, M.,& Maksimović, K.. (2020). Multi-disciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating. in Journal of Spacecraft and Rockets American Institute of Aeronautics and Astronautics., 57(3), 510-527. https://doi.org/10.2514/1.A34575
Vidanović N, Rašuo B, Kastratović G, Grbović A, Puharić M, Maksimović K. Multi-disciplinary 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, "Multi-disciplinary 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 . .