Calculation method of thrust target value for civil aircraft
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摘要:
推力管理是民航客机飞行管理系统的重要功能之一。在整个航线内，飞行管理系统根据不同飞行航段以及不同飞行状态，确定飞机对发动机的推力需求，并以此作为推力目标值形成发动机油门杆控制的指令，其中推力目标值的计算是推力管理的核心。针对民航客机各飞行航段的特点，采用飞行动力学方法对飞机爬升、巡航、下降三个航段中不同飞行方式下的推力目标值计算方法进行研究。以波音737-800实际飞行记录数据为算例，进行推力目标值计算方法仿真对比验证，结果表明：所计算的推力目标值变化趋势与飞行性能理论相符，典型航段推力目标值计算与实际飞行数据的对比误差不大于3%。所提出的推力目标值计算方法可为民航客机推力管理系统设计提供参考。
Abstract:Thrust management is one of the important functions of civil aircraft flight management system. In different flight phases and flight states of the whole route, the flight management system needs to calculate the aircraft thrust requirements for engine, and then use the required thrust as the target thrust to generate the command of engine throttle control. Of which, thrust target value calculation is the core of thrust management. According to different flight characteristics of each phase, the calculation method of aircraft thrust target value was studied by using flight dynamics. The calculation process of climb, cruise, descent phases at different flight modes were analyzed in detail. Taking Boeing 737-800 flight record data as an example, the thrust target value calculation method was simulated and verified. The results showed that the calculated thrust value was consistent with the flight performance theory, and the relative error between the calculated thrust and the actual flight record data in typical flight phases was less than 3%. The thrust target value calculation method can provide a reference for civil aircraft thrust management system design.
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图 11 Sr与飞机质量和飞行高度关系
Figure 11. Relationship between aircraft weight and Sr and flight altitude
图 12 巡航马赫数与Sr和飞行高度关系
Figure 12. Relationship between Sr and cruise Mach number and flight altitude
图 13 巡航高度、飞机质量、马赫数关系曲线
Figure 13. Relationship between cruise altitude and aircraft weight and Ma
图 14 巡航航段推力目标值计算流程图
Figure 14. Flow chart of thrust target calculation in cruise phase
图 15 航空发动机Tcor、 Ma 和N1cor的关系曲线
Figure 15. Relationship of aeroengine between Tcor, Ma and N1cor
图 17 爬升航段仿真结果和飞行数据对比
Figure 17. Comparison of simulation results and flight data in climb phase
图 18 巡航航段仿真结果和飞行数据对比
Figure 18. Comparison of simulation results and flight data in cruise phase
图 19 下降航段（a）仿真结果和飞行数据对比
Figure 19. Comparison of simulation results and flight data in descent phase （a）
图 20 下降航段（b）仿真结果和飞行数据对比
Figure 20. Comparison of simulation results and flight data in descent phase （b）
图 21 全航段推力目标值仿真结果和飞行数据对比
Figure 21. Comparison of simulation results and flight data in full flight phase
D/N 飞机阻力 CD 阻力系数 Vt/（m/s） 真空速 T0/K 大气温度 Vias/（m/s） 表速 T1*/K 发动机进口总温 Sw/m2 机翼面积 p0/Pa 大气压力 h/m 飞行高度 a/（m/s） 当地声速 Ma 马赫数 Rc/（m/s） 爬升率 T/N 发动机推力 Tcor/N 发动机换算推力 m/kg 飞机质量 
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表 1 爬升航段飞行数据及仿真数据
Table 1. Flight data and simulation results in climb phase
时间/s 发动机转速N1/% 误差/% 飞行数据 数值仿真 200 87.8 88.0153 0.2153 250 89.6 87.7877 1.8123 300 91.1 90.2353 0.8647 350 92.4 92.3923 0.0077 400 94.4 94.5747 0.1747 450 96.3 95.7673 0.5327 500 96.5 96.0531 0.4469 550 83.1 80.3186 2.7814 600 80.0 80.1885 0.1885 650 97.6 98.3322 0.7322 700 94.1 91.6704 2.4296
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表 2 巡航航段的飞行数据及仿真数据
Table 2. Flight data and simulation results in cruise phase
时间/s 发动机转速N1/% 误差/% 飞行数据 数值仿真 800 78.8 79.3539 0.5539 1100 78.9 79.8125 0.9125 1400 79.4 79.34 0.06 1700 78.9 79.7117 0.8117 2000 79.0 79.5576 0.5576 2300 79.5 79.7561 0.2561 2600 79.1 79.5105 0.4105 2900 78.6 79.8032 1.2032 3200 79.6 79.5647 0.0353 3500 79.3 79.7215 0.4215 3800 79.3 79.5771 0.2771 4100 79.1 79.9257 0.8257
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表 3 下降航段（a）飞行数据及仿真数据
Table 3. Flight data and simulation results in descent phase （a）
时间/s 发动机转速N1/% 误差/% 飞行数据 数值仿真 4200 64.0 63.62260 0.37740 4300 55.5 53.73930 1.76070 4400 33.3 33.36600 0.06600 4500 32.6 32.68570 0.08570 4600 44.8 45.29445 0.49445 4700 45.9 47.47890 1.57890 4800 52.8 53.21670 0.41670 4900 62.6 62.68380 0.08380 5000 63.4 61.9956 1.40440 5100 63.4 61.6779 1.72210
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表 4 下降航段（b）飞行数据及仿真数据
Table 4. Flight data and simulation results in descent phase （b）
时间/s 发动机转速N1/% 误差/% 飞行数据 数值仿真 5150 40.6 46.52916 5.92916 5200 40.6 44.29788 3.69788 5250 64.7 61.78360 2.91640 5300 36.4 35.76290 0.63710 5350 39.5 40.77256 1.27256 5400 34.9 45.25020 10.35020
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