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摘要:
基于模型的系统工程(MBSE)理论越来越广泛地应用于民用飞机设计与功能需求分析领域。研究起始于基于用户需求的自顶向下的民机系统产品顶层用例,辨识相关关键子用例,进一步基于对象用例展开“需求—功能分析”,构建黑盒活动图、顺序图表达实现相关飞机级需求的黑盒功能流,从而明确系统接口和辨识子系统,构建经验证可靠的可进行逻辑仿真的黑盒状态机。在黑盒功能架构的基础上驱动基于人机交互系统模型仿真的民机功能架构“正向设计”过程,对黑盒进行解白,基于建模分析和数值仿真结果,构建实现相关飞机级需求的系统功能白盒架构的“正向设计”。为充分演示上述方法,选择了对民用飞机产品安全性具有关键影响的最后进近着陆场景用例作为案例模型。研究表明,基于MBSE的民用飞机功能架构设计方法充分保证了需求分析和功能架构设计的紧密结合,正向构建了以满足民机产品需求为导向的结构化系统设计方法。
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关键词:
- 系统工程 /
- 基于模型的系统工程(MBSE) /
- 民机系统 /
- 需求分析 /
- 人机系统
Abstract:Model-based systems engineering (MBSE) theory has been widely used in the civil aircraft design and functional requirement analysis. Firstly, the research starts from the top-down use case of civil aircraft system product based on user requirements to identify the relevant key sub-use cases. Secondly, the method expands the "requirement-function analysis" based on the object use case, builds the black box activity diagram and sequence diagram to express the black box function flow so as to clarify the system interface and identify the subsystem, and constructs the black box state machine which is proved to be reliable and can be used for logical simulation. Finally, this paper carries out the "forward design" process of the civil aircraft functional architecture based on the man-machine interactive complex system model, and turns white the black box based on modeling analysis and numerical simulation results. Further to build a "forward design" of the system function white box architecture which realizes the relevant aircraft-level requirements. This paper selects the final approach and landing scenario which has a key effect on the safety of civil aircraft products as a case model. The research shows that the MBSE method for civil aircraft functional architecture fully guarantees the close combination of requirement analysis and functional architecture design, and constructs a structural system design method which meets the requirements of civil aircraft products.
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表 1 子系统划分
Table 1. Subsystem partition
具体功能 子系统 监控速度 监控子系统 监控高度 监控下降率 接受指令 报告飞行状态信息 报告飞行状态信息 调整速度 油门控制子系统 保持速度 刹车 慢车反推 调整滚转平衡 舵面调节子系统 调整滚转角 调节下降率 保持下降率 复飞 襟翼收放 襟翼系统 感知飞行状态信息 指令计算子系统 沿下滑道下滑 对准跑道 生成预测航迹 调定速度 调整下降率 表 2 波音747-400机身参数
Table 2. Boeing 747-400 aircraft parameters
参数 数值 翼展c/m 59.74 翼展b/m 8.32 参考面积s/m2 510.97 起飞质量m/kg 288 775 最大推力T/kg4 28 803 Ix 24 675 887 Iy 44 877 574 转动惯量/(kg·m2) Iz 67 384 152 Ixz 1 315 143 表 3 波音747-400气动力系数
Table 3. Boeing 747-400 aerodynamic coefficient
参数 数值 升力系数 CL0 0.21 CL_α 4.40 CL_adot 7.0 CL_q 6.6 CL_de 0.32 阻力系数 CD0 0.016 4 CD_α 0.2 侧力系数 CY_beta -0.9 CY_p 0 CY_dr 0.12 表 4 波音747-400气动力矩系数
Table 4. Boeing 747-400 aerodynamic moment coefficient
参数 数值 滚转力矩l Cl_beta -0.16 Cl_p -0.34 Cl_r 0.13 Cl_da -0.013 Cl_dr 0.008 俯仰力矩M CM0 0 CM_a -1.0 CM_adot -4 CM_q -20.5 CM_de -1.3 偏航力矩N CN_beta 0.16 CN_p -0.026 CN_r -0.280 CN_da -0.001 8 CN_dr -0.1 表 5 基础实验及对照实验仿真方法
Table 5. Basic experiment and control experiment simulation method
实验组别 参数设置 基础实验 时延:TSA~U(0, 1),
TMD~N(1, 1), TAC~T(1, 2)
升降舵控制精度IδE和油门控制精度IδT:
IδE~RandomInteger(1, 5)
IδT=U(1/50, 1/10)
高度控制灵敏度:对照实验1 时延:TSA~U(1, 2), TMD~N(2, 1),
TAC~T(2, 3)
其他参数设置与基础实验相同对照实验2 控制精度:
IδE~RandomInteger(1, 10)
IδT=U(1/50, 1/5)
其他参数设置与基础实验相同 -
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