高原机场飞机起飞滑跑距离计算方法

蔡良才; 王海服; 朱占卿; 种小雷

doi:10.19818/j.cnki.1671-1637.2013.02.010

高原机场飞机起飞滑跑距离计算方法

doi: 10.19818/j.cnki.1671-1637.2013.02.010

空军工程大学机场建筑工程系, 陕西西安 710038

基金项目:

军队科研项目 BKJ11J018

详细信息

作者简介:
蔡良才(1960-), 男, 浙江宁波人, 空军工程大学教授, 工学博士, 从事机场规划与设计研究

中图分类号: V351.11
计量
- 文章访问数: 854
- HTML全文浏览量: 171
- PDF下载量: 3034
- 被引次数: 0
出版历程
- 收稿日期: 2012-09-18
- 刊出日期: 2013-04-25

Calculation method of running distance for aircraft takeoff on plateau airport

Department of Airport and Architecture Engineering, Air Force Engineering University, Xi'an 710038, Shaanxi, China

More Information

Author Bio:
CAI Liang-cai(1960-), male, professor, PhD, +86-29-84787008, liangcai07@126.com

摘要

摘要: 针对高原机场的复杂环境和飞机发动机性能明显下降的特点, 分析了高原机场的飞机起飞滑跑过程。将机场实际气压换算为标准大气压力, 用修正的发动机瞬时推力计算不同时刻的滑跑距离, 提出了高原机场飞机起飞滑跑距离计算方法。分析了海拔高度、起飞质量、气温、风速等影响因素对飞机起飞滑跑距离的影响, 得出滑跑距离的简化计算公式并进行了实例验证。分析结果表明: 当高原机场海拔高度3 569.5 m, 气温为16.4 ℃, 逆风风速为2.1 m·s^-1时, 针对Ⅰ型飞机, 采用提出方法计算的滑跑距离与实测滑跑距离的最大绝对误差不超过48 m, 最大相对误差不超过2.7%;针对Ⅱ型飞机, 采用提出方法计算的滑跑距离与实测滑跑距离的最大绝对误差不超过100 m, 最大相对误差不超过4.2%;针对Ⅰ型飞机与Ⅱ型飞机, 应用简化计算公式计算的滑跑距离与实测滑跑距离的最大相对误差分别为3.9%和2.8%, 满足工程精度要求。
- 高原机场 /
- 滑跑距离 /
- 海拔高度 /
- 起飞质量 /
- 瞬时推力 /
- 气象条件
Abstract: Aiming at the complicated environment of plateau airport and the characteristic of significant decline for aircraft engine performance, the running process of aircraft takeoff on plateau airport was analyzed. The practical pressure of airport was transformed into standard atmosphere pressure, the running distances under different times were calculated by using the correctional instantaneous thrust of aircraft engine, and the calculation method of running distance for aircraft takeoff on plateau airport was put out. The influences of altitude, takeoff mass, temperature and wind speed on the running distances of aircraft takeoff were analyzed, the simplification formula of running distance was put forward, and example verification was carried out. Analysis result shows that when altitude is 3 569.5 m, temperature is 16.4 ℃ and upwind speed is 2.1 m·s^-1, the maximum absolute error between the running distance calculated by the proposed method and test running distance for aircraft Ⅰ is no more than 48 m, and the maximum relative error is no more than 2.7%. The maximum absolute error between the running distance calculated by the proposed method and test running distance for aircraft Ⅱ is no more than 100 m, and the maximum relative error is no more than 4.2%, The maximum relative errors between the running distances calculated by simplification formula and test running distances for aircraft Ⅰ and aircraft Ⅱ are 3.9% and 2.8% respectively, which meet the engineering requirement.
- plateau airport /
- running distance /
- altitude /
- takeoff mass /
- instantaneous thrust /
- meteorological condition

HTML全文

图 1 计算值与实测值对比曲线

Figure 1. Comparison curves bewteen calculation values and test values

下载: 全尺寸图片幻灯片

图 2 滑跑距离与海拔高度的关系

Figure 2. Relations between running distances and altitudes

下载: 全尺寸图片幻灯片

图 3 Ⅰ型飞机滑跑距离与起飞质量的关系

Figure 3. Relations between running distances and takeoff masses for aircraft Ⅰ

下载: 全尺寸图片幻灯片

图 4 Ⅱ型飞机滑跑距离与起飞质量的关系

Figure 4. Relations between running distances and takeoff masses for aircraft Ⅱ

下载: 全尺寸图片幻灯片

图 5 Ⅰ型飞机滑跑距离与机场温度的关系

Figure 5. Relations between running distances and airport temperatures for aircraft Ⅰ

下载: 全尺寸图片幻灯片

图 6 Ⅱ型飞机滑跑距离与机场温度的关系

Figure 6. Relations between running distances and airport temperatures for aircraft Ⅱ

下载: 全尺寸图片幻灯片

图 7 Ⅰ型飞机滑跑距离与风速的关系

Figure 7. Relations between running distances and wind speeds for aircraft Ⅰ

下载: 全尺寸图片幻灯片

图 8 Ⅱ型飞机滑跑距离与风速的关系

Figure 8. Relations between running distances and wind speeds for aircraft Ⅱ

下载: 全尺寸图片幻灯片

表 1 绝对误差与相对误差

Table 1. Absolue errors and relative errors

机型	组号	1	2	3	4	5
Ⅰ型	绝对误差/m	20	25	26	31	48
Ⅰ型	相对误差/%	2.0	2.2	1.8	1.9	2.7
Ⅱ型	绝对误差/m	32	75	71	22	100
Ⅱ型	相对误差/%	2.6	3.8	3.3	0.8	4.2

下载: 导出CSV

表 2 起飞质量与滑跑距离

Table 2. Takeoff masses and running distances

Ⅰ型飞机	起飞质量/kg	24 140	25 560	26 160	27 720	28 000
	计算距离/m	1 150	1 325	1 400	1 595	1 630
	实测距离/m	1 162	1 303	1 366	1 537	1 569
Ⅱ型飞机	起飞质量/kg	13 297	14 139	15 415	16 477	17 757
	计算距离/m	586	847	1 243	1 571	1 969
	实测距离/m	603	805	1 198	1 537	1 921

下载: 导出CSV

参考文献(23)

[1]	王振辉, 蔡良才, 邵斌. 军用机场跑道长度设计方法[J]. 交通运输工程与信息学报, 2007, 5(1): 67-70, 76. doi: 10.3969/j.issn.1672-4747.2007.01.013 WANG Zhen-hui, CAI Liang-cai, SHAO Bin. Design method of military airfield runway length[J]. Journal of Transportation Engineering and Information, 2007, 5(1): 67-70, 76. (in Chinese). doi: 10.3969/j.issn.1672-4747.2007.01.013
[2]	蔡良才, 郑汝海, 种小雷, 等. 高原机场飞机起飞着陆滑跑距离测试与分析[J]. 空军工程大学学报: 自然科学版, 2000, 1(2): 4-7. doi: 10.3969/j.issn.1009-3516.2000.02.002 CAI Liang-cai, ZHENG Ru-hai, CHONG Xiao-lei, et al. Test and analyses of airplane's running distance of taking-off and landing on plateau airport[J]. Journal of Air Force Engineering University: Natural Science Edition, 2000, 1(2): 4-7. (in Chinese). doi: 10.3969/j.issn.1009-3516.2000.02.002
[3]	宋花玉, 蔡良才, 吴利荣, 等. 基于BP网络的飞机起飞滑跑距离计算[J]. 空军工程大学学报: 自然科学版, 2004, 5(6): 4-6. doi: 10.3969/j.issn.1009-3516.2004.06.002 SONG Hua-yu, CAI Liang-cai, WU Li-rong, et al. Calculation of aircraft taking-off running distance based on BP network[J]. Journal of Air Force Engineering University: Natural Science Edition, 2004, 5(6): 4-6. (in Chinese). doi: 10.3969/j.issn.1009-3516.2004.06.002
[4]	杨洪平, 王立新, 李勤红. 民机最小离地速度的工程计算方法[J]. 飞行力学, 2006, 24(2): 9-12. doi: 10.3969/j.issn.1002-0853.2006.02.003 YANG Hong-ping, WANG Li-xin, LI Qin-hong. An engineering method to determine the minimum unstick speed of civil airplanes[J]. Flight Dynamics, 2006, 24(2): 9-12. (in Chinese). doi: 10.3969/j.issn.1002-0853.2006.02.003
[5]	邓扬晨, 张爽, 陈华, 等. 飞机地面滑行过程中最短滑跑距离的确定[J]. 航空计算技术, 2006, 36(1): 71-74, 78. doi: 10.3969/j.issn.1671-654X.2006.01.021 DENG Yang-chen, ZHANG Shuang, CHEN Hua, et al. The optimal taxi-distance determining on aircraft take-off and landing[J]. Aeronautical Computing Technique, 2006, 36(1): 71-74, 78. (in Chinese). doi: 10.3969/j.issn.1671-654X.2006.01.021
[6]	张志刚, 王百争, 王和平, 等. MA60飞机高原机场起飞性能研究[J]. 飞行力学, 2006, 24(4): 65-69. https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX200604016.htm ZHANG Zhi-gang, WANG Bai-zheng, WANG He-ping, et al. Research on take-off performance of the MA60aircraft at plateau airport[J]. Flight Dynamics, 2006, 24(4): 65-69. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX200604016.htm
[7]	AC 150/5300-13B, airport design[S].
[8]	葛志浩, 徐浩军, 孟捷. 驾驶员模型随机性研究与仿真[J]. 系统仿真学报, 2007, 19(2): 453-455. doi: 10.3969/j.issn.1004-731X.2007.02.057 GE Zhi-hao, XU Hao-jun, MENG Jie. Research on pilot model random and numerical simulation[J]. Journal of System Simulation, 2007, 19(2): 453-455. (in Chinese). doi: 10.3969/j.issn.1004-731X.2007.02.057
[9]	李秋红, 孙健国, 王前宇. 航空发动机推力估计新方法[J]. 控制理论与应用, 2011, 28(2): 185-191. https://www.cnki.com.cn/Article/CJFDTOTAL-KZLY201102010.htm LI Qiu-hong, SUN Jian-guo, WANG Qian-yu. A new method for estimating the thrust of aircraft engines[J]. Control Theory and Applications, 2011, 28(2): 185-191. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KZLY201102010.htm
[10]	PINDER S D. Aircraft takeoff performance monitoring in farnorthern regions: an application of the global positioning system[D]. Saskatoon: University of Saskatchewan, 2003.
[11]	BALL T, TUMER S, MARSHALL D D. Short takeoff per-formance using circulation control[C]//AIAA. 46th AIAA Aerospace Sciences Meeting and Exhibit. Reno: AIAA, 2008: 1-14.
[12]	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.htm ZHAO 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
[13]	宋花玉. 飞机起飞滑跑发动机推力数值确定方法[J]. 航空计算技术, 2010, 40(6): 43-46. https://www.cnki.com.cn/Article/CJFDTOTAL-HKJJ201006012.htm SONG Hua-yu. A numerical value confirmation method of engine thrustin aircraft in take-off running[J]. Aeronautical Computing Technique, 2010, 40(6): 43-46. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKJJ201006012.htm
[14]	薛宏涛, 王克波. 基于起降性能模型的军用飞机起降规划与计算[J]. 计算机工程与设计, 2011, 32(5): 1837-1840. https://www.cnki.com.cn/Article/CJFDTOTAL-SJSJ201105080.htm XUE Hong-tao, WANG Ke-bo. Military aircraft takeoff and landing planning and computing based on performance model[J]. Computer Engineering and Design, 2011, 32(5): 1837-1840. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-SJSJ201105080.htm
[15]	王辉, 张伟方. 计算机环境下的实时飞行仿真系统的构建[J]. 机械科学与技术, 2011, 30(8): 1235-1238. https://www.cnki.com.cn/Article/CJFDTOTAL-JXKX201108005.htm WANG Hui, ZHANG Wei-fang. Construction of a real-time flight simulation system based on computer environment[J]. Mechanical Science and Technology for Aerospace Engineering, 2011, 30(8): 1235-1238. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-JXKX201108005.htm
[16]	吴利荣. 现代飞机与发动机高原性能设计和使用技术基础研究[D]. 西安: 空军工程大学, 2004. WU Li-rong. Basic research on performance desgin and use technology for modern aircraft and engine on plateau region[D]. Xi'an: Air Force Engineering University, 2004. (in Chinese).
[17]	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. https://www.cnki.com.cn/Article/CJFDTOTAL-XBGD200902009.htm YU Xiao-jing, HE Guo-qiang, LI Jiang, et al. Calculating effects of relevant parameters on vortex valve control of variable thrust SMR[J]. Journal of Northwestern Polytechnical University, 2009, 27(2): 178-183. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-XBGD200902009.htm
[18]	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. https://www.cnki.com.cn/Article/CJFDTOTAL-DNDX200202025.htm CAI 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). https://www.cnki.com.cn/Article/CJFDTOTAL-DNDX200202025.htm
[19]	王何巍. 高原军用机场跑道长度计算方法的研究[D]. 西安: 空军工程大学, 2000. WANG He-wei. The study on calculation method of runway length on plateau military airport[D]. Xi'an: Air Force Engineering University, 2000. (in Chinese).
[20]	葛志浩, 徐浩军, 胡飞, 等. 先进战斗机人-机闭环系统仿真研究[J]. 弹箭与制导学报, 2004, 24(3): 389-391. https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD2004S6043.htm GE Zhi-hao, XU Hao-jun, HU Fei, et al. MATLAB simulation model of closed-loop aircraft-pilot system[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2004, 24(3): 389-391. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD2004S6043.htm
[21]	王春光, 李瑰贤, 郑叔涛, 等. 飞行员滑模最优化控制行为特性分析[J]. 哈尔滨工业大学学报, 2011, 43(3): 38-43. https://www.cnki.com.cn/Article/CJFDTOTAL-HEBX201103009.htm WANG Chun-guang, LI Gui-xian, ZHENG Shu-tao, et al. Characteristic analysis of optimal control behavior of pilot sliding[J]. Journal of Harbin Institute of Technology, 2011, 43(3): 38-43. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HEBX201103009.htm
[22]	高健, 郑淑涛, 韩俊伟. 基于最小二乘法的飞行员模型参数辨识[J]. 江南大学学报: 自然科学版, 2011, 10(6): 648-652. https://www.cnki.com.cn/Article/CJFDTOTAL-JLXY201106005.htm GAO Jian, ZHENG Shu-tao, HAN Jun-wei. Pilot model parameters identification based least square method[J]. Journal of Jiangnan University: Natural Science Edition, 2011, 10(6): 648-652. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-JLXY201106005.htm
[23]	李大伟, 徐浩军, 胡新江, 等. 基于等效系统拟配的人-机闭环系统稳定性研究[J]. 飞行力学, 2011, 29(4): 19-22. https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201104005.htm LI Da-wei, XU Hao-jun, HU Xin-jiang, et al. Research on stability of aircraft-pilot closed loop system based on matching of equivalent system[J]. Flight Dynamics, 2011, 29(4): 19-22. (in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201104005.htm