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首页> 外文期刊>Journal of Aircraft >Multicontrol Surface Optimization for Blended Wing-Body Under Handling Quality Constraints
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Multicontrol Surface Optimization for Blended Wing-Body Under Handling Quality Constraints

机译：处理质量约束下的机翼混合体多控制面优化

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摘要

Control architecture sizing is a main challenge of blended-wing-body design. This aircraft configuration typically features redundant elevons located at the trailing edge of the wing, acting simultaneously on pitch and roll axes. Consequently, a proper sizing requires one to consider coupled longitudinal and lateral criteria. Moreover, significant hinge moments due to large control surface areas, combined with high deflection rates in order to safely control the longitudinal instability, may result in excessive power consumption and actuator mass penalty. Therefore, it is highly desirable at the preliminary design level to minimize control surface areas, while ensuring adequate closed-loop handling qualities, with limited deflections and deflection rates. The problem of integrated design of control surface sizes and flight control laws for an unstable blended-wing-body aircraft is addressed here. The latest tools for H nonsmooth optimization of structured controllers are used to optimize in a single step the gains for both longitudinal and lateral control laws, as well as a control allocation module, while minimizing the control surface span. The following constraints are ensured: maximal deflection angles and rates for 1) pilot longitudinal pull up, 2) pilot bank angle order, and 3) longitudinal turbulence. Using this coupled approach, significant gains in terms of the outer elevon's span as compared to the initial layout are demonstrated, whereas closed-loop handling quality constraints are guaranteed.
机译：控制架构的大小是混合机翼机身设计的主要挑战。这种飞机配置通常具有位于机翼后缘的多余电子，同时在俯仰和横滚轴上起作用。因此，适当的尺寸需要考虑纵向和横向的耦合标准。此外，由于较大的控制表面积而产生的明显的铰链力矩，再加上较高的挠曲率，以便安全地控制纵向不稳定性，可能会导致功耗过大和致动器质量下降。因此，非常需要在初步设计水平上最小化控制表面面积，同时确保足够的闭环处理质量，并且偏转和偏转速率有限。这里讨论了不稳定的混合翼体飞机的控制面尺寸和飞行控制规律的集成设计问题。用于结构化控制器的H非平稳优化的最新工具可单步优化纵向和横向控制律以及控制分配模块的增益，同时最大程度地减小控制面跨度。确保以下约束：1）飞行员纵向上拉，2）飞行员倾斜角阶数和3）纵向湍流的最大偏转角和速率。使用这种耦合方法，可以证明与初始布局相比，外部元件的跨度显着提高，同时保证了闭环处理质量的约束。

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  • 来源
    《Journal of Aircraft》 |2018年第2期|638-651|共14页
  • 作者

    Denieul Yann; Bordeneuve Joel; Alazard Daniel; Toussaint Clement; Taquin Gilles;

  • 作者单位

    Univ Toulouse, ISAE SUPAERO, 10 Av Edouard Belin, F-31055 Toulouse, France;

    Univ Toulouse, ISAE SUPAERO, 10 Av Edouard Belin, F-31055 Toulouse, France;

    Univ Toulouse, ISAE SUPAERO, 10 Av Edouard Belin, F-31055 Toulouse, France;

    ONERA French Aerosp Lab, 2 Av Edouard Belin, F-31055 Toulouse, France;

    Airbus Operat SAS, Future Projects Off, 316 Route Bayonne, F-31060 Toulouse, France;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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