考虑风不确定性与燃油节省因素的最优终端区进近程序
Optimal TRACON Descent Procedures under Wind Uncertainty and Fuel Savings Factors
AI总结：
该研究针对A319等四种机型，提出连续进近延迟减速进近（CDDA），经优化后在3.50°下滑道角下相比传统进近可减少11%-21%预期燃油，且明确了减速架构、下滑道角等因素对燃油节省的影响及DDA平飞段的作用
AI中文摘要：
终端区进近程序需在整个风气候条件下执行，而非单一风况。尽管延迟减速进近（DDA）的飞行演示显示出显著燃油节省，但DDA将延迟减速与更陡峭的3.77°最终进近相结合，掩盖了每项设计选择的贡献。本研究提出连续进近延迟减速进近（CDDA），其将延迟减速应用于连续进近（CDA）剖面，且在下滑道截获前无平飞段。基于仿真的随机优化选择襟翼展开触发速度与下滑道捕获距离，以在给定稳定进近概率约束下，最小化风不确定性下的预期燃油消耗。最优控制降维将设计空间限制为数百个候选方案，可利用六自由度快速时间仿真对加权风网格计算精确期望。针对A319、B737-800、B767-400及A340-300机型，在匹配的3.00°、3.50°、3.77°最终角下对CDA与CDDA进行优化。结果显示，减速架构是影响最小的因素，在3.50°时可实现0.3%至3.9%的燃油节省，仅在3.77°时对B767-400机型产生显著影响；下滑道角度主导燃油节省，在3.50°类别D设计最大值下，优化后的CDDA相比优化后的3°CDDA可减少11%至21%的预期燃油，而襟翼程序优化可额外增加2%至17%的燃油节省。DDA的平飞段主要作为顺风鲁棒性缓冲，且3.77°最终进近超过1000英尺/分钟的稳定进近下降率要求，限制了其近期的运行适用性。
英文摘要：
A terminal-area descent procedure need to perform across the wind climatology rather than a single wind condition. Although flight demonstrations of the delayed deceleration approach (DDA) showed substantial fuel savings, DDA combined late deceleration with a steeper $3.77^\circ$ final descent, obscuring the contribution of each design choice. In this work, we propose the continuous-descent delayed deceleration approach (CDDA), which applies delayed deceleration to a continuous descent approach (CDA) profile without a level segment before glideslope intercept. A simulation-based stochastic optimization selects flap deployment trigger speeds and glideslope-capture distance to minimize expected fuel under wind uncertainty subject to a given stabilized-approach probability. An optimal control reduction limits the design space to a few hundred candidates, enabling exact expectation over a weighted wind grid using six-degree-of-freedom fast-time simulations. CDA and CDDA are optimized at matched final angles of $3.00^\circ$, $3.50^\circ$, and $3.77^\circ$ for the A319, B737-800, B767-400, and A340-300. Results show that deceleration architecture is the weakest factor, yielding 0.3--3.9\% savings at $3.50^\circ$ and becoming material only for the B767-400 at $3.77^\circ$. Glideslope angle dominates fuel saving. At the $3.50^\circ$ Category D design maximum, optimized CDDA reduces expected fuel by 11-21\% relative to optimized $3^\circ$ CDA, while flap-schedule optimization adds 2-17\%. The DDA level segment acts primarily as a tailwind-robustness buffer, and the $3.77^\circ$ final exceeds the 1,000 ft/min stabilized-approach sink-rate element, limiting its near-term operational applicability.
