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固定翼重量方案（Class I）：空重统计模型 + 航程燃油估算 + MTOW 迭代闭合。当需要建立重量闭合与敏感性分析时调用。
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| name | fixed_wing_weights_spec |
| description | 固定翼重量方案（Class I）：空重统计模型 + 航程燃油估算 + MTOW 迭代闭合。当需要建立重量闭合与敏感性分析时调用。 |
| stage | class1_conceptual |
| code_module | aircraft_design/class1_conceptual/weights_class1.py |
| dependencies | ["fixed_wing_overall_sizing_runbook"] |
fixed_wing_overall_sizing_runbook 统一驱动，输入来自同一份 JSON：
requirements.range_minitial_guess.sfc_cruise_1_sinitial_guess.cd0、initial_guess.oswald_e、initial_guess.aspect_ratiorequirements.payload_kgoutputs.mtow_kg、outputs.empty_weight_kg、outputs.fuel_weight_kgoutputs.converged 与迭代历史（若写入）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。