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固定翼推进/能量系统方案：推力/功率等级、耗油/效率模型与可用推力随高度速度变化。当需要把推进假设接入总体性能闭环时调用。
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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_propulsion_spec |
| description | 固定翼推进/能量系统方案：推力/功率等级、耗油/效率模型与可用推力随高度速度变化。当需要把推进假设接入总体性能闭环时调用。 |
| stage | class2_preliminary |
| code_module | aircraft_design/class2_preliminary/propulsion.py, aircraft_design/config/engine_library.py |
| dependencies | ["fixed_wing_overall_sizing_runbook"] |
fixed_wing_overall_sizing_runbook 当前对推进的最小输入是：
initial_guess.sfc_cruise_1_s（统一用 1/s 表达耗油强弱）initial_guess.thrust_to_weight（决定推力等级量级）sfc_cruise_1_s 统一入口字段承载）T/W 与 MTOW 共同确定stage3_propulsion.*）