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首页> 外文会议>AIAA/ASCE/AHS/ASC structures, structural dynamics and materials conference;AIAA SciTech Forum >An Examination of Vehicle Design Tradeoffs and Trajectory Optimization for Trimmed Scramjet-Powered Hypersonic Vehicles On Ascent
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An Examination of Vehicle Design Tradeoffs and Trajectory Optimization for Trimmed Scramjet-Powered Hypersonic Vehicles On Ascent

机译：上升式修整超燃冲压超音速飞行器的车辆设计权衡和轨迹优化研究

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Several design rules are discussed that can be helpful in optimizing the design and the ascent trajectory of a generic hypersonic vehicle that is powered by a dual-mode ranvjet-scramjet engine. The focus is on "vehicle integration" design rules, which differ from the "propulsion-oriented" optimization that has been discussed in certain textbooks. Vehicle-integration rules account for realistic constraints, including the requirement that the vehicle must be trimmed at all points along an ascent trajectory and that additive drag and vehicle stability are considered. A hypersonic waverider does not follow rules for a conventional airplane, where the goal is a large ratio of wing area to frontal area in order to maximize Lift/Drag ratio. Nor does a waverider follow rules for a rocket (where the goal is to maximize the Thrust/Drag ratio, requiring a small ratio of wing area to frontal area). Instead a waverider requires an optimization of both T/D and L/D, which introduces certain challenges. Governing parameters that were varied were: aspect ratio (fc/c), engine inlet width (W), root chord length (c), acceleration profiles (n), and flight Mach number i VI). The output parameters selected for optimization were thrust-to-drag (T/D) and lift-to-drag (L/D). Trends for auxiliary parameters such as angle-of-attack (a), elevon deflection angle (<>), and equivalence ratio (0) were examined. A surrogate-based optimization algorithm was applied. The advantages of selecting the largest possible dynamic pressure are discussed. Trajectory optimization was also performed to minimize fuel burn m and maximize (T/D) along an ascent trajectory.
机译：讨论了一些设计规则，这些规则可有助于优化由双模式ranvjet-scramjet发动机提供动力的通用超音速飞行器的设计和上升轨迹。重点是“车辆集成”设计规则，该规则与某些教科书中已讨论的“面向推进”的优化不同。车辆整合规则考虑了实际的约束，包括以下要求：必须沿上升轨迹在所有点上修剪车辆，并考虑附加阻力和车辆稳定性。高超音速的ridrider不遵循常规飞机的规则，在常规飞机中，目标是机翼面积与前部面积的比例较大，以使升力/阻力比达到最大。 Waverider也不遵循火箭的规则（目标是最大化推力/阻力比，要求机翼面积与前部面积的比例很小）。取而代之的是，乘波器需要同时优化T / D和L / D，这带来了某些挑战。改变的控制参数为：纵横比（fc / c），发动机进气口宽度（W），根弦长度（c），加速度曲线（n）和飞行马赫数i VI）。选择用于优化的输出参数是推力-拖动（T / D）和升力-拖动（L / D）。研究了辅助参数的趋势，如攻角（a），电子偏转角（<>）和当量比（0）。应用了基于代理的优化算法。讨论了选择最大可能的动态压力的优点。还进行了轨迹优化，以最大程度地减少燃油消耗并沿上升轨迹最大化（T / D）。

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