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摘要: 为了确定飞机起飞航迹, 应用数值计算理论, 提出了发动机瞬时推力的计算方法, 以发动机推力曲线已知推力为基础, 通过拉格朗日插值确定未知推力。基于计算的发动机瞬时推力, 计算了起飞航迹, 并与实测航迹进行了比较。计算结果表明: 飞机1的实测拟合航迹与程序计算航迹的最大绝对误差不超过10 m, 最大相对误差不超过3.9%;飞机2的实测拟合航迹与程序计算航迹的最大绝对误差不超过35 m, 最大相对误差不超过8.3%, 计算方法可靠。Abstract: In order to confirm aircraft take-off track, a computational method of engine instantaneous thrust was put forward by using numerical calculation theory.Based on certain engine instantaneous thrusts and thrust curve, the unknown thrusts were calculated by Lagrange interpolation.Two certain aircrafts' take-off tracks were computed when their engine instantaneous thrusts were calculated by the algorithm, and a comparison between computation tracks and actual flight test fitted tracks was made.Comparison result shows that the maximum absolute error of aircraft 1 is not more than 10 m, and the one of aircraft 2 is not more than 35 m.The maximum relative error of aircraft 1 is not more than 3.9%, and the one of aircraft 2 is not more than 8.3%.The result indicates that the algorithm is precise and feasible.
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表 1 飞机1发动机推力插值节点
Table 1. Interpolation nodes of engine thrusts for aircraft 1
表 2 飞机2发动机推力插值节点
Table 2. Interpolation nodes of engine thrusts for aircraft 2
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[1] 蔡良才, 邵斌, 郑汝海, 等. 机场净空规定过渡面范围的计算确定[J]. 空军工程大学学报: 自然科学版, 2007, 8(1): 11-13, 17. doi: 10.3969/j.issn.1009-3516.2007.01.004CAI Liang-cai, SHAO Bin, ZHENG Ru-hai, et al. Calcula- tion of confirmation to transitional surface range in the airfield clearance rules[J]. Journal of Air Force Engineering University: Natural Science Edition, 2007, 8(1): 11-13, 17. (in Chinese) doi: 10.3969/j.issn.1009-3516.2007.01.004 [2] 马玉凡, 王卫安. 机场净空限制计算模型及可视化研究[J]. 测绘工程, 2008, 17(1): 32-36. doi: 10.3969/j.issn.1006-7949.2008.01.009MA Yu-fan, WANG Wei-an. Research on the computing model of airport clearance limitation and its visualization[J]. Engineering of Surveying and Mapping, 2008, 17(1): 32-36. (in Chinese) doi: 10.3969/j.issn.1006-7949.2008.01.009 [3] 张洪伟. 民用机场净空环境保护标准分析[J]. 中国民航大学学报, 2009, 27(3): 15-19. doi: 10.3969/j.issn.1001-5590.2009.03.005ZHANG Hong-wei. Analysis on the specification of civil air- port clearance[J]. Journal of Civil Aviation University of China, 2009, 27(3): 15-19. (in Chinese) doi: 10.3969/j.issn.1001-5590.2009.03.005 [4] 张洪海, 胡明华. 多跑道降落飞机协同调度优化[J]. 交通运输工程学报, 2009, 9(3): 86-91. doi: 10.3321/j.issn:1671-1637.2009.03.017ZHANG Hong-hai, HU Ming-hua. Multi-runway collabora- tive scheduling optimization of aircraft landing[J]. Journal of Traffic and Transportation Engineering, 2009, 9(3): 86-91. (in Chinese) doi: 10.3321/j.issn:1671-1637.2009.03.017 [5] 张兆宁, 沈金炜, 刘计民. 基于CNS定位误差的侧向碰撞风险模型[J]. 交通运输工程学报, 2009, 9(6): 110-113. doi: 10.3969/j.issn.1671-1637.2009.06.021ZHANG Zhao-ning, SHEN Jin-wei, LIU Ji-min. Lateral col- lision risk model based on CNS position error[J]. Journal of Traffic and Transportation Engineering, 2009, 9(6): 110- 113. (in Chinese) doi: 10.3969/j.issn.1671-1637.2009.06.021 [6] 蔡良才, 王声, 郑汝海, 等. 飞机起飞着陆航迹测试与分析[J]. 东南大学学报: 自然科学版, 2002, 32(2): 264-267. doi: 10.3321/j.issn:1001-0505.2002.02.026CAI Liang-cai, WANG Sheng, ZHENG Ru-hai, et al. Test and analysis of airplane's running track in taking off and landing[J]. Journal of Southeast University: Natural Science Edition, 2002, 32(2): 264-267. (in Chinese) doi: 10.3321/j.issn:1001-0505.2002.02.026 [7] 崔飞. 两室一推结构提高试验火箭发动机推力[J]. 探测与控制学报, 2008, 30(6): 17-20. https://www.cnki.com.cn/Article/CJFDTOTAL-XDYX200806005.htmCUI Fei. Enhancement of test rocket motor thrust by struc- ture of two-chamber single-thrust[J]. Journal of Detection& Control, 2008, 30(6): 17-20. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-XDYX200806005.htm [8] 杨全廷, 杨纪明, 韩小全. 一种高精度的发动机推力测量系统[J]. 传感器与微系统, 2008, 27(12): 82-87. https://www.cnki.com.cn/Article/CJFDTOTAL-CGQJ200812028.htmYANG Quan-ting, YANG Ji-ming, HAN Xiao-quan. High- precision measuring system for aeroengine thrust[J]. Trans- ducer and Microsystem Technologies, 2008, 27(12): 82-87. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-CGQJ200812028.htm [9] 余晓京, 何国强, 李江, 等. 涡流阀式变推力发动机性能影响因素数值研究[J]. 西北工业大学学报, 2009, 27(2): 178-183. doi: 10.3969/j.issn.1000-2758.2009.02.007YU Xiao-jing, HE Guo-qiang, LI Jiang, et al. Calculating effects of relevant parameters on vortex valve control of vari- able thrust SMR[J]. Journal of Northwestern Polytechnical University, 2009, 27(2): 178-183. (in Chinese) doi: 10.3969/j.issn.1000-2758.2009.02.007 [10] 赵永平, 孙健国. 最小二乘支持向量回归机在发动机推力估计中的应用[J]. 航空动力学报, 2009, 24(6): 1420-1425. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI200906036.htmZHAO Yong-ping, SUN Jian-guo. Aeroengine thrust estimation using least squares support vector regression machine[J]. Journal of Aerospace Power, 2009, 24(6): 1420-1425. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI200906036.htm -
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