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固定翼稳定与操纵方案：尾容积系数定尺寸、静稳定裕度与配平接口。当需要从总体几何推导尾翼与稳定性初算时调用。
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| name | fixed_wing_stability_control_spec |
| description | 固定翼稳定与操纵方案：尾容积系数定尺寸、静稳定裕度与配平接口。当需要从总体几何推导尾翼与稳定性初算时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/stability_control.py, aircraft_design/class2_preliminary/tail_sizing.py |
| dependencies | ["fixed_wing_overall_sizing_runbook"] |
fixed_wing_overall_sizing_runbook 在收敛后阶段 2–7 中使用：
tail.vh、tail.vv、tail.lh_m、tail.lv_mstability.*outputs.wing_area_m2、outputs.geometry.*），或由 geometry_shape 派生tail：vh、vv、lh_m、lv_mstability（可选）：x_ac_w_cbar、x_cg_cbar、x_cg_fwd_cbar、x_cg_aft_cbar、cm0_w、tail_efficiency 等geometry_shape.tail.*（可选）：用于把“面积初算”落到可视化/网格/导出层Sh, Sv：水平/垂直尾翼面积初算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。