Uncertainty analysis and design optimization of solid rocket motors with finocyl grain
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Uncertainty analysis and design optimization of solid rocket motors with finocyl grain Zhu Hao 1,2
&
Luo Haowen 1,2 & Wang Pengcheng 1,2 & Cai Guobiao 1,2 & Hu Feng 3
Received: 17 October 2019 / Revised: 17 July 2020 / Accepted: 21 August 2020 # Springer-Verlag GmbH Germany, part of Springer Nature 2020
Abstract The traditional multidisciplinary design optimization (MDO) method for the conceptual design of the solid rocket motor (SRM) is usually deterministic and seldom focuses on systematic design optimization. This paper develops a systematic design model of the SRM with a finocyl grain and proposes an approach for uncertainty analysis and design optimization of SRM. The mean value and standard deviation of the target function, as well as the probability that the constraints can be met, are calculated using Monte Carlo simulation (MCS) analysis. The uncertainty-based multidisciplinary design optimization (UMDO), together with the deterministic multidisciplinary design optimization (DMDO), is applied to the conceptual design of SRM based on the thirdstage engine ZEFIRO9 of the Vega launch vehicle. By main effect diagrams and Pareto diagrams, the most influential design variables and standard deviation of uncertain parameters are obtained, which can help designers understand more of the uncertainty relationships between parameters and system performance. Keywords Uncertainty analysis . Design optimization . Solid rocket motor . Finocyl grain
1 Introduction Solid rocket motors (SRMs) are widely used in missile weapons traditionally (George and Oscar 2017). In recent years, they have also been applied in low-cost fast-response small launch vehicles (Daniele et al. 2018; Bertacin et al. 2013; Stefano et al. 2007; Phil 2018; Mark et al. 2011; Huang 1990) and some other aircrafts (Thomas 2011; Kennedy et al. 1999; Yves and Jean-Marc 2006; Weihua et al. 2018; Pawel et al. 2017). The design process of SRMs is complex and involves multiple disciplines such as thermodynamic, internal ballistic, structure and pneumatic, especially the SRMs with a finocyl grain is more widely used but more complex (Ali et al. 2013; Mascio et al. 2014; Ali et al. 2010). Responsible Editor: Christian Gogu * Zhu Hao [email protected] 1
School of Astronautics, Beihang University, Beijing 100191, China
2
Key Laboratory of Spacecraft Design Optimization & Dynamic Simulation Technologies, Ministry of Education, Beijing, China
3
Xi’an Changfeng Institute of Electrical and Mechanical, Xi’an 710065, China
The conceptual design comes right after mission requirements during the whole design workflow, and by the time the conceptual design is “frozen,” it becomes increasingly difficult to implement wholesale changes in the basic requirements or operations concept of the space vehicle (Walter 2001). In order to find the optimal conceptual design at an affordable computational cost, low-fidelity disciplinary analyses are mostly employed, introducing model (epistemic) uncertainties (Loic et al. 2014). During conceptua
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