A Multi-Step Sequential System Optimization Design Method for Upper Stages

IF 0.9 Q3 ENGINEERING, AEROSPACE
Vahid Bohlouri, M. Zakeri, M. Nosratollahi
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引用次数: 0

Abstract

This paper proposes a new approach in multi-step sequential system optimization (MSSO) to implement a conceptual design for satellite upper stage with a maneuver in the conditions close to reality. In this method of design, there are two main cycles; trajectory optimization cycle and optimal design cycle, each one is correlated to each other in another cycle called configuration. In the trajectory optimization, the optimization objective is to place the upper stage in the destination orbit, using the minimum amount of fuel consumption. In this cycle, a new approach has been introduced for a three-dimensional trajectory using two genetic algorithms inside each other. In addition, selecting the suitable engine is carried out in this cycle. Convergence of design and exclusion of design are carried out in the configuration cycle. Convergence and optimization of subsystems design are carried out in the optimal design cycle. The innovations of this paper are implementation of the design according to multi-step sequential system design in which optimization is performed step by step, and orbital optimization is introduced according to a new approach. Choosing a desirable criterion for optimization process and proper coefficient for convergence in design, are among considerable characteristics of this paper. Validation has been performed using one of the upper stages in the world.
一种多级序贯系统优化设计方法
本文提出了一种新的多步顺序系统优化方法,实现了接近实际条件下具有机动的卫星上级的概念设计。在这种设计方法中,有两个主要周期;轨迹优化周期和优化设计周期,在另一个称为构型的周期中相互关联。在轨道优化中,优化目标是使上级在目标轨道上,以最小的燃料消耗为目标。在这个循环中,一种新的方法被引入了一个三维轨迹,使用两个遗传算法彼此内部。并在此循环中选择合适的发动机。在配置周期内进行设计的收敛和设计的排除。在优化设计周期内进行子系统设计的收敛与优化。本文的创新之处在于按照多步序贯系统设计的思路逐步进行优化设计,并根据新的思路引入轨道优化。选择理想的优化准则和适当的设计收敛系数是本文的重要特点。目前已在世界上某一级进行了验证。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
CiteScore
2.00
自引率
0.00%
发文量
16
审稿时长
20 weeks
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