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指导固定翼总体设计如何迭代收敛与做敏感性检查。当总体入口已跑完但结果不满足/不收敛，需要系统化调整变量时调用。
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Based on SOC occupation classification
执行包含高级分析与机身几何的固定翼总体设计流程。初步分析收敛后调用，含高级分析、几何约束与机身外形。
固定翼总体设计唯一入口：执行 Class I 闭环并在收敛后进入阶段 2–7 扩展分析，落盘输出报告/数据/外形资产，并可选 PySide6 实时可视化。
生成固定翼总体设计方案（需求→约束→设计点→初步尺寸→重量/性能闭合）。当需要给出固定翼总体方案、关键参数范围与决策依据时调用。
| name | fixed_wing_design_loop_runbook |
| description | 指导固定翼总体设计如何迭代收敛与做敏感性检查。当总体入口已跑完但结果不满足/不收敛，需要系统化调整变量时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/design_loop_orchestrator.py |
| dependencies | ["fixed_wing_overall_sizing_runbook"] |
fixed_wing_overall_sizing_runbook。aircraft_design.run_sizing 为准）：设计点约束修正、Class I 重量闭合、巡航/爬升一级校核、尾翼体积系数初算、收敛后阶段 2–7 扩展wing_loading_pa, aspect_ratio, thrust_to_weight, cd0, e, cl_maxL/D（降低 cd0、提高 e、提高 AR）或改善推进耗油模型thrust_to_weight 或降低重量/阻力wing_loading_pa 或提高 cl_maxw0_kg 相对变化 < 1e-3