高增益飞机飞行品质研究
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摘要
本文介绍了军用标准MIL-STD-1797A提供的评估短周期俯仰响应特性的6种不同判据，依据这六种判据利用等效系统方法对某型飞机纵向短周期运动的飞行品质进行计算和分析，结果表明这6种判据既有着许多共同之处，也有许多不一致的特点。运用序列二次规划方法计算出满足Neal—Smith准则条件的驾驶员模型参数，然后将ω_(sd)T_(θ2),S_(sd),τ_θ准则映射到Neal-Smith准则，确定它们的一致区域和矛盾区域，对参数影响进行分析，评估其变化趋势，为新机设计、实验和试飞过程中更好地选择合适的飞行品质参数提供参考。最后介绍了战斗机中等幅度滚转姿态快速性的定义，应用欧拉法对19种飞机构形的滚转快速性进行了仿真计算，并且与地面模拟战斗机滚转攻击机动实验相比较，结果表明滚转姿态快速性与滚转模态时间常数、滚转操纵效能、副翼操纵速率和控制系统增益等密切相关，飞行品质标准MIL-STD-1797没有完全涵盖中等幅度滚转姿态变化的要求。
This paper introduced six different methods which are given by MIL-STD-1797 offers for evaluating short-term pitch response. According to these methods, Flying qualities for aircraft short-term response are calculated and analyzed by equivalent system. The results indicate that there are both regions of agreement and regions of conflict in these methods. Sequential Quadratic Programming is used to solve the pilot model
in the Neal-Smith criterion. And then, the criteria of ωspTθ2,ζsp,τθ are
mapped to Neal-Smith criteria for short-term pitch to determine regions of agreement and regions of conflict. In order to provide better selections for the parameters of flying qualities on the design of a new aircraft, an experiment and a test- fly, the effects and the varying trends of the parameters are analyzed and evaluated.
Finally, Based on the definition of moderate amplitude roll attitude quickness criteria for fighter aircraft, The roll attitude quickness is calculated by Euler method for 19 types aircraft configurations in the paper. The results of the simulation calculation are compared with the pilots simulation experiment on aggressive maneuvering
in roll, The conclusions are obtained that roll attitude quickness is closely related to the flying qualities, such as the roll-mode constant, the roll control sensitivity, aileron control effectiveness and control system augment etc. Requirements for moderate amplitude maneuvering roll attitude changes are not completely involved in MIL-STD-1797A.
This paper introduced six different methods which are given by MIL-STD-1797 offers for evaluating short-term pitch response. According to these methods, Flying qualities for aircraft short-term response are calculated and analyzed by equivalent system. The results indicate that there are both regions of agreement and regions of conflict in these methods. Sequential Quadratic Programming is used to solve the pilot model
in the Neal-Smith criterion. And then, the criteria of ωspTθ2,ζsp,τθ are
mapped to Neal-Smith criteria for short-term pitch to determine regions of agreement and regions of conflict. In order to provide better selections for the parameters of flying qualities on the design of a new aircraft, an experiment and a test- fly, the effects and the varying trends of the parameters are analyzed and evaluated.
Finally, Based on the definition of moderate amplitude roll attitude quickness criteria for fighter aircraft, The roll attitude quickness is calculated by Euler method for 19 types aircraft configurations in the paper. The results of the simulation calculation are compared with the pilots simulation experiment on aggressive maneuvering
in roll, The conclusions are obtained that roll attitude quickness is closely related to the flying qualities, such as the roll-mode constant, the roll control sensitivity, aileron control effectiveness and control system augment etc. Requirements for moderate amplitude maneuvering roll attitude changes are not completely involved in MIL-STD-1797A.
引文
[1]张阿舟：浅谈《军用飞机飞行品质规范》(试用本)飞行力学，1983(1)．
[2]董庚寿：对MIL—STD-1797的初步分析，640所．
[3]ACT飞机飞行品质标准和手册建议本，《ACT飞机飞行品质研究》课题组，2000．10。
[4]国处飞行力学研究，飞行力学杂志社，1988．6。
[5]刘昶：敏捷性、过失速机动、飞行品质和推力矢量控制新进展，南京航空航天大学，1997．3．
[6]推力矢量控制飞机飞行品质研究进展，南京航空航天大学，2002．4。
[7]刘昶，蒋明：航天飞机飞行品质规范初步研究1990(3)
[8]孟宪蔷：控制工程基础，航空工业出版社，1992．9。
[9]张曙光，方振平：大迎角飞行品质的研究进展，飞行力学，1998．3
[10]张明谦：飞行控制系统，航空工业出版社，1993．9
[11]李利春：随控布局，国防工业出版社，1984．
[12]张翔伦，许洲，王晓辉：短周期运动飞行品质的几个判据，飞行力学，1998．3
[13]范立钦：直接力控制飞机的操纵品质判据—频带宽度，飞行力学，1993，(2)．
[14]高浩：应用等效系统法评价飞行品质，飞行力学，1992，(2)．
[15]国外飞行手册，国际航空编辑部，1975．
[16]方振平，范子强：战斗机俯仰瞬态敏捷性与飞行品质关系研究，飞行力学，1995．9．
[17]方振平，屈香菊，崔振新：驾驶员—飞机系统特性的匹配分析，飞行力学，1995．9．
[18]胡兆丰：人机系统和飞行品质，北京航空航天大学五0九教研室，1989．5．
[19]刘昶等：飞机飞行品质标准和手册(建议稿)，国防科工委航空气动力协作攻关办公室，1992．12．
[20]屈香菊等：驾驶员模型参数与飞行品质关系研究，北航科技报告，BH-B4242，1992．
[21]方振平等：关于飞机纵向短周期模态等效参数的确定，飞行力学，1986，(3)．
[22]Neal T P et al.Development of a flying qualities Criterion for the Design of Fighter Flight Control Systems.J. Guidance,1970.
[23]Innocent M et al.Pilot Modeling Techniques for the Analysis of Aircraft Linnear Dynamic Behaviour.Aeronatical Journal,May 1990.
[24]飞机飞行品质计算手册，中华人民共和国航空工业部，1983．
[25]张明廉：飞行控制系统，航空工业出版社，1994．
[26]Kish, B.A.,A Comparison of the Neal-Smith and ω_(sp),Τ_,(θ2),ι_θ,Flying Qualities Criteria,M.S.Thesis,Air Force Institute of Technology,AFIT/GAE/ENY/94D-11,Wright-Patterson AFB,OH,Dec.1994.
[27]Hodgkinson et al.,Handling Qualities of Aircraft with Stability and Control Augmentation System—A Fundamental Approach,Aeronautical Journal February 1976.
[28]Military Standard, Flying Qualities of Piloted aircraft,MIL-STD-1797A,30 Jan.1990.
[29]Huffily,Robert K.,Simon M. Boume,et al.,Study of Helicopter Roll Control Effectiveness Criteria,NASA CR 177404,U.S.Army AVSCOM TR-85-A-5,Apr.1986.
[30]David H. Klyde and Bimal L.Aponso, et al.,Development of Roll Attitude Quickness Criteria for Fight Aircraft. AIAA-95-3205-CP.
[31]Key, David L,and Roger H.Hoh,"New Handling Qualities Requirements and How They can be Wet,"43rd Annual Forum Proceedings,American Helicopter Society,St.Louis, MO, May 1987,pp.975-990.
[2]董庚寿：对MIL—STD-1797的初步分析，640所．
[3]ACT飞机飞行品质标准和手册建议本，《ACT飞机飞行品质研究》课题组，2000．10。
[4]国处飞行力学研究，飞行力学杂志社，1988．6。
[5]刘昶：敏捷性、过失速机动、飞行品质和推力矢量控制新进展，南京航空航天大学，1997．3．
[6]推力矢量控制飞机飞行品质研究进展，南京航空航天大学，2002．4。
[7]刘昶，蒋明：航天飞机飞行品质规范初步研究1990(3)
[8]孟宪蔷：控制工程基础，航空工业出版社，1992．9。
[9]张曙光，方振平：大迎角飞行品质的研究进展，飞行力学，1998．3
[10]张明谦：飞行控制系统，航空工业出版社，1993．9
[11]李利春：随控布局，国防工业出版社，1984．
[12]张翔伦，许洲，王晓辉：短周期运动飞行品质的几个判据，飞行力学，1998．3
[13]范立钦：直接力控制飞机的操纵品质判据—频带宽度，飞行力学，1993，(2)．
[14]高浩：应用等效系统法评价飞行品质，飞行力学，1992，(2)．
[15]国外飞行手册，国际航空编辑部，1975．
[16]方振平，范子强：战斗机俯仰瞬态敏捷性与飞行品质关系研究，飞行力学，1995．9．
[17]方振平，屈香菊，崔振新：驾驶员—飞机系统特性的匹配分析，飞行力学，1995．9．
[18]胡兆丰：人机系统和飞行品质，北京航空航天大学五0九教研室，1989．5．
[19]刘昶等：飞机飞行品质标准和手册(建议稿)，国防科工委航空气动力协作攻关办公室，1992．12．
[20]屈香菊等：驾驶员模型参数与飞行品质关系研究，北航科技报告，BH-B4242，1992．
[21]方振平等：关于飞机纵向短周期模态等效参数的确定，飞行力学，1986，(3)．
[22]Neal T P et al.Development of a flying qualities Criterion for the Design of Fighter Flight Control Systems.J. Guidance,1970.
[23]Innocent M et al.Pilot Modeling Techniques for the Analysis of Aircraft Linnear Dynamic Behaviour.Aeronatical Journal,May 1990.
[24]飞机飞行品质计算手册，中华人民共和国航空工业部，1983．
[25]张明廉：飞行控制系统，航空工业出版社，1994．
[26]Kish, B.A.,A Comparison of the Neal-Smith and ω_(sp),Τ_,(θ2),ι_θ,Flying Qualities Criteria,M.S.Thesis,Air Force Institute of Technology,AFIT/GAE/ENY/94D-11,Wright-Patterson AFB,OH,Dec.1994.
[27]Hodgkinson et al.,Handling Qualities of Aircraft with Stability and Control Augmentation System—A Fundamental Approach,Aeronautical Journal February 1976.
[28]Military Standard, Flying Qualities of Piloted aircraft,MIL-STD-1797A,30 Jan.1990.
[29]Huffily,Robert K.,Simon M. Boume,et al.,Study of Helicopter Roll Control Effectiveness Criteria,NASA CR 177404,U.S.Army AVSCOM TR-85-A-5,Apr.1986.
[30]David H. Klyde and Bimal L.Aponso, et al.,Development of Roll Attitude Quickness Criteria for Fight Aircraft. AIAA-95-3205-CP.
[31]Key, David L,and Roger H.Hoh,"New Handling Qualities Requirements and How They can be Wet,"43rd Annual Forum Proceedings,American Helicopter Society,St.Louis, MO, May 1987,pp.975-990.