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执行尾翼初算（尾容积系数法）并输出 Sh/Sv。当总体设计需要尾翼面积初值或静稳定裕度不足需调整尾容积时调用。
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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_stability_control_runbook |
| description | 执行尾翼初算（尾容积系数法）并输出 Sh/Sv。当总体设计需要尾翼面积初值或静稳定裕度不足需调整尾容积时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/stability_control.py, aircraft_design/class2_preliminary/tail_sizing.py |
| dependencies | ["fixed_wing_stability_control_spec"] |
fixed_wing_overall_sizing_runbook 在扩展阶段驱动。tail.vh, tail.vvtail.lh_m, tail.lv_ms_m2, b_m, cbar_mtail.sh_m2, tail.sv_m2在获得尾翼尺寸后，调用 aircraft_design/stability_dynamic.py 进行模态分析：
from aircraft_design.stability_dynamic import DynamicStabilityAnalyzer
# ... 实例化 analyzer ...
results = analyzer.analyze(...)
fixed_wing_overall_sizing_runbook
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