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Damage-Mitigating Control of Space Propulsion Systems for High Performance and Extended Life

机译:高性能和延长寿命的空间推进系统的减损控制

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摘要

A major goal in the control of complex mechanical system such as spacecraft rocket engine's advanced aircraft, and power plants is to achieve high performance with increased reliability, component durability, and maintainability. The current practice of decision and control systems synthesis focuses on improving performance and diagnostic capabilities under constraints that often do not adequately represent the materials degradation. In view of the high performance requirements of the system and availability of improved materials, the lack of appropriate knowledge about the properties of these materials will lead to either less than achievable performance due to overly conservative design, or over-straining of the structure leading to unexpected failures and drastic reduction of the service life. The key idea in this report is that a significant improvement in service life could be achieved by a small reduction in the system dynamic performance. The major task is to characterize the damage generation process, and then utilize this information in a mathematical form to synthesize a control law that would meet the system requirements and simultaneously satisfy the constraints that are imposed by the material and structural properties of the critical components. The concept of damage mitigation is introduced for control of mechanical systems to achieve high performance with a prolonged life span. A model of fatigue damage dynamics is formulated in the continuous-time setting, instead of a cycle-based representation, for direct application to control systems synthesis. An optimal control policy is then formulated via nonlinear programming under specified constraints of the damage rate and accumulated damage. The results of simulation experiments for the transient upthrust of a bipropellant rocket engine are presented to demonstrate efficacy of the damage-mitigating control concept.
机译:控制复杂机械系统(例如航天器火箭发动机的先进飞机和发电厂)的主要目标是在提高可靠性,部件耐用性和可维护性的同时实现高性能。决策和控制系统综合的当前实践侧重于在通常不能充分代表材料退化的约束条件下提高性能和诊断能力。鉴于系统对高性能的要求以及改进材料的可用性,由于对设计的过于保守或对结构的过度拉伸,缺乏对这些材料的性能的适当了解将导致性能无法达到预期的水平。意外故障和使用寿命大大降低。该报告的主要思想是,通过稍微降低系统动态性能,可以显着提高使用寿命。主要任务是表征损坏的产生过程,然后以数学形式利用此信息来合成满足系统要求并同时满足关键部件的材料和结构特性所施加的约束的控制定律。引入了减轻损害的概念来控制机械系统,以实现高性能并延长使用寿命。疲劳损伤动力学模型是在连续时间设置中制定的,而不是基于周期的表示形式,可直接应用于控制系统综合。然后,通过非线性编程在指定的损伤率和累积损伤约束条件下制定最优控制策略。提出了用于双推进火箭发动机瞬态上推的模拟实验结果,以证明减轻损害控制概念的有效性。

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    Ray, Asok; Wu, Min-Kuang;

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  • 年度 1994
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