基于Radau伪谱法的再入航天器多学科设计优化

IF 12.2 1区 工程技术 Q1 MECHANICS Applied Mechanics Reviews Pub Date : 2022-09-26 DOI:10.3390/applmech3040067
Masoud Kabganian, S. M. Hashemi, J. Roshanian
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引用次数: 1

摘要

再入航天器及其子系统的设计与优化本质上是一个多学科或多目标优化问题。多学科设计优化(MDO)侧重于使用数值优化来设计具有相互作用和独立行动的多个子系统或学科的系统。在本文中,由于航天器是一个非线性的、广泛的和稀疏的系统,利用Radau伪谱方法将系统级优化器、轨迹、几何和形状、空气动力学和空气热力学微分方程转换为代数方程。在MDO的帮助下,通过将所有学科一起迭代来解决问题;人们可以同时改进设计,减少整个设计周期的时间和成本,并使再入航天器的结构质量最小化。在综合前人研究成果的基础上,针对低升阻比(L/D)返回舱型航天器设计过程中的关键子系统,提出了一种综合创新的基于rpm的一次性(AAO) MDO方法。考虑钝舱几种几何形状的状态和控制变量、各种约束条件和参数,并利用阿波罗的气动和气动系数,给出了再入航天器的优化尺寸。与阿波罗飞船的原始质量相比,引入的优化方案使质量减少了17%。该方法采用快速计算和简化模型相结合的方法,在概念设计过程中分析了广泛的车辆形状和入口类型。
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Multidisciplinary Design Optimization of a Re-Entry Spacecraft via Radau Pseudospectral Method
The design and optimization of re-entry spacecraft or its subsystems is a multidisciplinary or multiobjective optimization problem by nature. Multidisciplinary design optimization (MDO) focuses on using numerical optimization in designing systems with several subsystems or disciplines that have interactions and independent actions. In the present paper, the system-level optimizer, trajectory, geometry and shape, aerodynamics, and aerothermodynamics differential equations, are converted to algebraic equations using the Radau pseudospectral method (RPM) since a spacecraft is a nonlinear, extensive, and sparse system. The solution to the problem with the help of MDO is reached by iterating all the disciplines together; one can simultaneously enhance the design, decrease the time and cost of the entire design cycle, and minimize the structural mass of a re-entry spacecraft. Considering various methods presented in earlier research works, a combined and innovative all-at-once (AAO), RPM-based MDO method, including the key subsystems in the design process of a re-entry capsule-shape spacecraft with a low lift-to-drag ratio (L/D), is presented. Considering the applicable state and control variables, various constraints, and parameters applied to several geometric shapes of a blunt capsule and using Apollo’s aerodynamic and aerothermodynamic coefficients, the optimized dimensions for a re-entry spacecraft are presented. The introduced optimization scheme led to a 17% mass reduction compared to the original mass of the Apollo vehicle. Fast computing and simplified models are used together in this method to analyze a wide range of vehicle shapes and entry types during conceptual design.
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来源期刊
CiteScore
28.20
自引率
0.70%
发文量
13
审稿时长
>12 weeks
期刊介绍: Applied Mechanics Reviews (AMR) is an international review journal that serves as a premier venue for dissemination of material across all subdisciplines of applied mechanics and engineering science, including fluid and solid mechanics, heat transfer, dynamics and vibration, and applications.AMR provides an archival repository for state-of-the-art and retrospective survey articles and reviews of research areas and curricular developments. The journal invites commentary on research and education policy in different countries. The journal also invites original tutorial and educational material in applied mechanics targeting non-specialist audiences, including undergraduate and K-12 students.
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