-
摘要:
逃逸复飞特性对于确定舰载机的进舰速度、航母航速与着舰海况等级限制等均具有重要的影响。根据逃逸复飞的任务要求,提出了离舰滑跑距离、逃逸复飞段最大迎角相对进舰配平迎角的增量和着舰时的俯仰角作为安全性评定的3个参数。建立了数字飞行员模型,基于数字虚拟飞行仿真计算的方法,获得了满足逃逸复飞安全要求的参数适配包线。研究结果表明:在每一确定的着舰重量下,均对应存在一个最佳的进舰速度范围,能够使舰载机逃逸复飞的离舰滑跑距离最短;逃逸复飞段最大迎角相对进舰配平迎角的增量、着舰时舰载机的俯仰角分别决定了进舰速度大小的上、下边界;舰载机重心位置变化将使参数适配包线的边界位置和范围发生改变,但边界形状基本不变;航母航速减小将显著地缩小参数适配包线;适配包线内每一点的逃逸复飞成功率,可以为不同海况等级下的逃逸复飞安全性判断提供参考。
Abstract:The bolter characteristics have significant effect on the approach airspeed determination of a carrier-based aircraft, the grade limits of ship speed and sea state during carrier landing. Three parameters are proposed as the safety indexes according to the bolter task requirements. They are taxing distance of the bolter, angle of attack angle of attack increment (the peak angle of attack during bolter minus the approach angle of attack), and pitch angle of touchdown. Numerical pilot model is formulated, and the parameter suitability envelope which satisfies the bolter safety requirements is obtained based on the digital virtual flight testing method. The results show that, for each landing weight, there is a best approach airspeed range to minimize the bolter taxing distance. The angle of attack increment and the pitch angle of touchdown respectively determine the upper and lower boundary of approach airspeed. Movement of the center of gravity will change the position and range of the parameter suitability envelope, but the envelope shape is nearly unchanged. Reducing the ship speed will narrow the parameter suitability envelope. The success rate corresponding to each point in the parameter suitability envelope provides a reference for the bolter safety judgment under different grades of sea state.
-
Key words:
- carrier-based aircraft /
- bolter /
- suitability envelope /
- simulation model /
- deck motion
-
表 1 不同海况等级下的甲板运动建模数据
Table 1. Modeling data of deck motion under different sea states
参数 4级海况 6级海况 垂荡位移幅值/m 0.68 1.63 横摇角幅值/(°) 0.62 1.45 纵摇角幅值/(°) 0.52 1.24 垂荡频率/(rad·s-1) 0.35 0.35 横摇频率/(rad·s-1) 0.29 0.29 纵摇频率/(rad·s-1) 0.52 0.52 -
[1] U.S.Department of Defense.Air vehicle joint service specification guide: JSSG-2001A[S].Patuxent River: Naval Air Systems Command, 2002: D-40. [2] 杨一栋, 江驹, 张宏涛, 等.着舰安全与复飞技术[M].北京:国防工业出版社, 2013:116-150.YANG Y D, JIANG J, ZHANG H T, et al.Safety and waveoff technologies in carrier landing[M].Beijing:National Defense Industry Press, 2013:116-150(in Chinese). [3] RUDOWSKY T, COOK S, HYNES M, et al.Review of the carrier approach criteria for carrier-based aircraft.Phase I: Final report[R].Patuxent River: Naval Air Warfare Center Aircraft Division, 2002. [4] 杨一栋.舰裁机进场着舰规范评估[M].北京:国防工业出版社, 2016:123-124.YANG Y D.Review of the carrier approach criteria[M].Beijing:National Defense Industry Press, 2006:123-124(in Chinese). [5] 王永庆, 罗云宝, 王奇涛, 等.面向机舰适配的舰载飞机起降特性分析[J].航空学报, 2016, 37(1):269-277. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201601022WANG Y Q, LUO Y B, WANG Q T, et al.Carrier suitability-oriented launch and recovery characteristics of piloted carrier-based aircraft[J].Acta Aeronautica et Astronautica Sinica, 2016, 37(1):269-277(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201601022 [6] 励缨, 温玮, 金长江.舰载飞机逃逸复飞动力学特性研究[J].飞行力学, 1994, 12(2):1-9. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=Y149682LI Y, WEN W, JIN C J.The study of dynamic character of bolting and going-around for carrier aircraft[J].Flight Dynamics, 1994, 12(2):1-9(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=Y149682 [7] 崔坤林, 胡国才, 罗云宝.舰载飞机纵向逃逸性能仿真研究[J].海军航空工程学院学报, 2009, 24(4):435-439. doi: 10.3969/j.issn.1673-1522.2009.04.018CUI K L, HU G C, LUO Y B.Simulated investigation for carrier-based airplane longitudinal go-around performance[J].Journal of Naval Aeronautical and Astronautical University, 2009, 24(4):435-439(in Chinese). doi: 10.3969/j.issn.1673-1522.2009.04.018 [8] 史卫民, 韩维, 李辉青.基于ADAMS/Aircraft的舰载机逃逸性能分析[J].海军航空工程学院学报, 2010, 25(5):481-484. doi: 10.3969/j.issn.1673-1522.2010.05.001SHI W M, HAN W, LI H Q.The carrier-based aircraft bolter analysis based on ADAMS/Aircraft[J].Journal of Naval Aeronautical and Astronautical University, 2010, 25(5):481-484(in Chinese). doi: 10.3969/j.issn.1673-1522.2010.05.001 [9] 陶杨, 韩维, 李军亮.舰载机逃逸过程动力学研究[J].计算机仿真, 2015, 32(3):77-80. doi: 10.3969/j.issn.1006-9348.2015.03.017TAO Y, HAN W, LI J L.Dynamic research of carrier aircraft's escaping[J].Computer Simulation, 2015, 32(3):77-80(in Chinese). doi: 10.3969/j.issn.1006-9348.2015.03.017 [10] 段萍萍, 聂宏, 魏小辉.飞机触舰后逃逸复飞性能分析[J].中国机械工程, 2014, 25(9):1225-1231. doi: 10.3969/j.issn.1004-132X.2014.09.017DUAN P P, NIE H, WEI X H.Bolting and go-around performance analysis of carrier-based aircraft[J].China Mechanical Engineering, 2014, 25(9):1225-1231(in Chinese). doi: 10.3969/j.issn.1004-132X.2014.09.017 [11] 张声伟, 段卓毅, 耿建中, 等.阻拦索断裂对螺旋桨舰载机着舰安全影响数值分析[J].航空学报, 2019, 40(4):622293. http://d.old.wanfangdata.com.cn/Periodical/hkxb201904002ZHANG S W, DUAN Z Y, GENG J Z, et al.Carrier suitability-oriented launch and recovery characteristics of piloted carrier-based aircraft[J].Acta Aeronautica et Astronautica Sinica, 2019, 40(4):622293(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkxb201904002 [12] 国防科学技术工业委员会.舰载飞机强度和刚度规范地面载荷: GJB 2753-96[S].北京: 中国标准出版社, 1997.The Commission of Science, Technology and Industry for National Defense.Carrier-based airplane strength and rigidity specification ground loads: GJB 2753-96[S].Beijing: Standards Press of China, 1997(in Chinese). [13] SCHARL J, MAVRIS D N, BURDUN I Y.Use of flight simulation in early design: Formulation and application of the virtual testing and evaluation methodology: AIAA-2000-5590[R].Reston: AIAA, 2000. [14] 《飞机设计手册》总编委会.飞机设计手册第14册起飞着陆系统设计[M].北京:航空工业出版社, 2002:96-98.The Chief Committee of Aircraft Design Manual.Aircraft design manual.Volume 14:Takeoff and landing system design[M].Beijing:Aviation Industry Press, 2002:96-98(in Chinese). [15] 高金源, 李陆豫, 冯亚昌.飞机飞行品质[M].北京:国防工业出版社, 2003:139-143.GAO J Y, LI L Y, FENG Y C.Aircarft handing qualities[M].Beijing:National Defense Industry Press, 2003:139-143(in Chinese). [16] ZAAL P M, POOL D M, BRUIN J, et al.Use of pitch and heave motion cues in a pitch control task[J].Journal of Guidance, Control and Dynamics, 2009, 32(2):366-377. doi: 10.2514/1.39953 [17] 陈俊平, 王立新.低能量状态对飞行安全的危害及改出方法[J].航空学报, 2017, 38(8):61-71. http://d.old.wanfangdata.com.cn/Periodical/hkxb201708007CHEN J P, WANG L X.Hazards of low energy state to flight safety and recovery methods[J].Acta Aeronautica et Astronautica Sinica, 2017, 38(8):61-71(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkxb201708007 [18] 彭競.舰载飞机进舰着舰的自动引导和控制研究[D].北京: 北京航空航天大学, 2001: 33-41. http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=Y425400PENG J.Research on the automatic guide and control of carrier-based airplane approach and landing[D].Beijing: Beihang University, 2001: 33-41(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=Y425400 [19] DENISON N A.Automated carrier landing of an unmanned combat aerial vehicle using dynamics inversion[D].Wright-Patterson Air Force Base: Air Force Institute of Technology, 2007: 42-43.