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首页> 外文期刊>IEEE Aerospace and Electronic Systems Magazine >New approach in designing solid upper stage for interplanetary missions using finite burn assumption
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New approach in designing solid upper stage for interplanetary missions using finite burn assumption

机译：使用有限燃烧假设为行星际飞行设计固体上层的新方法

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In this article a new approach is proposed for the design of solid propulsion upper stages. The majority of this research has focused on the design environment and interaction between disciplines to optimize design and save time. In this article, finite burn is inserted in the initial phases of design, and a propulsion system was designed based on this assumption. Results are similar to real and optimum values, with no correction needed. In this way, further validations or corrections of design are no longer needed. In the final phases of design, correcting and changing the design is time consuming. The design environment proposed in this article has demonstrated a dramatic analysis of time savings and presented excellent design outputs. Mass properties, propulsion analysis, and trajectory analysis disciplines are integrated to improve transfer vehicle performance and decrease total mass. This work will be useful for designing optimum and actual space vehicles. The design environment of liquid propulsion upper-stage and multimaneuver transfer vehicles, which have reignite capabilities, will be documented in forthcoming articles.
机译：在本文中，提出了一种用于固体推进上段设计的新方法。这项研究大部分集中在设计环境和学科之间的交互上，以优化设计并节省时间。在本文中，有限燃烧被插入设计的初始阶段，并基于此假设设计了推进系统。结果类似于真实值和最佳值，无需校正。这样，不再需要对设计进行进一步的验证或修正。在设计的最后阶段，校正和更改设计非常耗时。本文提出的设计环境已经证明了对节省时间的戏剧性分析，并提供了出色的设计输出。质量属性，推进分析和轨迹分析学科被整合在一起，以改善转运车辆的性能并减少总质量。这项工作对于设计最佳和实际的航天器将是有用的。具有点火功能的液体推进上级和多机动转移车的设计环境将在以后的文章中进行介绍。

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