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Innovative MDO methodology to design space launch system Application to the ALTAIR air-launch system

机译:创新的MDO方法,以设计空间发射系统应用到Altair Air-Launch系统

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This paper presents the methodology used to preliminary design a future cost-effective air launch system for small satellites, studied in the frame of the H2020 ALTAIR project (Air Launch space Transportation using an Automated aircraft and an Innovative Rocket). This methodology relies on the use of design to cost associated with multidisciplinary design optimization (MDO) techniques. The particularity of this system is to use a reusable unmanned aircraft carrier designed specifically for the air-launch mission associated with an expendable, low cost, launch vehicle. The methodology used to design the space launch system relies on collaborative engineering between sub-system design tasks and sustained application of design-to-cost techniques and multidisciplinary design optimization strategies. Risk mitigation, cost savings, reliability and performances are major drivers in the development of the final system, leading to a delicate balance between technological innovation, low cost solutions and maturity level. The main difficulty for a design of a new vehicle is to establish a first feasible design, due to the sensitivity on the various design parameters. To ensure a good optimization of the vehicle satisfying design constraints, simplified models have been elaborated and combined in an optimization platform using different optimization algorithms at different steps of the process (genetic, BFGS...). The originality of the methodology put into place is to target cost-effectiveness at every levels of the design system: at sub-system level and also at system level through an integrated carrier/design optimization process, with the main coupling variables being the launcher release conditions. The paper provides the results obtained at the end of the final design loop of the system. Finally, the paper illustrates how this methodology can help and foster the design of new space launch vehicle to manage safety margins, reduce design duration and to achieve a low cost s
机译:本文介绍用于初步设计未来的高性价比的空中发射系统,用于小卫星的方法,在(使用自动化的飞机和火箭的创新空中发射航天运输)的H2020 ALTAIR项目的框架研究。这种方法依赖于使用的设计与多学科设计优化(MDO)技术相关的成本。该系统的特殊性是使用专门用于与消耗性,成本低,运载火箭相关联的空气发射任务设计的可重复使用无人驾驶飞机的载体。用于设计的空间发射系统的方法依赖于子系统的设计任务,设计到成本的技术和多学科设计优化策略的持续应用程序之间的协作工程。缓解风险,节约成本,可靠性和性能是最终系统的发展主要驱动力,引领技术创新,低成本的解决方案和成熟度等级之间的微妙平衡。为一个新的车辆的设计的主要困难是建立第一种可行的设计,由于在不同的设计参数的灵敏度。为确保满足设计约束车辆的很好的优化,简化的模型已在过程(遗传,BFGS ...)的不同阶段采用不同的优化算法被阐述和组合的优化平台。到位的方法的原创性是在设计系统的各层次目标成本效益:在子系统级,并在通过一个集成的载体/设计优化过程中的系统级,主要耦合变量是发射器发布状况。本文提供了在该系统的最终设计循环的结束时得到的结果。最后,阐述了这种方法如何帮助培育新的运载火箭的设计来管理安全系数,减少设计时间,并实现低成本小号

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