ф3.2米低速风洞单自由度动导数试验技术研究
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摘要
动导数是飞机设计及运动分析(包括过失速机动飞行和尾旋分析)所需的重要参数,也是飞行控制律设计和飞机动态飞行品质研究的重要气动数据。本文研究了Φ3.2米低速风洞俯仰振荡和偏航/滚转振荡单自由度动导数试验技术。主要开展了如下工作:
一、通过对国内外相关文献调研动,掌握导数的研究现状并进一步阐述进行此研究的必要性,并分别根据弹性?阻尼特性和飞行器小扰动方程建立动导数提取方程。
二、对动导数数据采集系统所需要的硬件配置进行了研究,并基于各种数学变换对动导数的数据处理进行了研究,最后对各种动导数的计算方法进行了比较。
三、论证并选定实现俯仰振荡的机构,利用虚拟样机技术完成俯仰振荡和偏航/滚转振荡两套装置的机械设计,并完成运动控制部分设计。
四、完成两套机构的调试。利用所研制的俯仰振荡装置在Φ3.2米低速风洞进行风洞验证试验并对所获得的数据进行分析。结果表明:该装置所测试出来的数据数值合理、准确,具有测量动导数的能力。
Aerodynamic derivatives is one of the most important parameters for the airplane design and oscillation analyse. It is also important data for the design of control law and assessment of airplane’s dynamic characteristic. The main research of this passage is development 2 equipments which can realize 1 DOF force oscillation on pitch movement and yaw/roll movement. By doing this, the researcher can deeply analyze the aircraft’s unsteady aerodynamic characteristics. For all, the main work of this research as follows.
First of all, it has demonstrated the necessity and possibility by investigation the domestic and foreign thesis about the aerodynamic derivatives’research actuality. More the equations of aerodynamic derivatives extracting have been created by the mass-spring and Small Disturbance.
Secondly, this paper has researched the hardware configuration the dynamic derivatives acquisition system. Base on the mathematic transform, it also has researched the methods of data processing of derivatives. In addition, the methods have been compared with each other.
Thirdly, the cam and parallelogram drive mechanisms both can realize the pitch force oscillation, for this, this paper has argument the 2 methods and chosen the parallelogram drive mechanism for this research. Base on the virtual prototyping technology, the work of pitch force oscillation and yaw/roll force oscillation has been done. Except this, to reduce vibration during the test time, the pole wires have been designed by taking reduce vibration into count.
At last, carry out wind tunnel validate test by using the pitch force oscillation rig and compared the acquired data with others which had been acquired from other wind tunnels and other rigs. After doing this, we can get a conclusion that the data which have been tested by pitch force oscillation rig are rational and reliable, the rig can be used to design of an aircraft and research of aerodynamics.
一、通过对国内外相关文献调研动,掌握导数的研究现状并进一步阐述进行此研究的必要性,并分别根据弹性?阻尼特性和飞行器小扰动方程建立动导数提取方程。
二、对动导数数据采集系统所需要的硬件配置进行了研究,并基于各种数学变换对动导数的数据处理进行了研究,最后对各种动导数的计算方法进行了比较。
三、论证并选定实现俯仰振荡的机构,利用虚拟样机技术完成俯仰振荡和偏航/滚转振荡两套装置的机械设计,并完成运动控制部分设计。
四、完成两套机构的调试。利用所研制的俯仰振荡装置在Φ3.2米低速风洞进行风洞验证试验并对所获得的数据进行分析。结果表明:该装置所测试出来的数据数值合理、准确,具有测量动导数的能力。
Aerodynamic derivatives is one of the most important parameters for the airplane design and oscillation analyse. It is also important data for the design of control law and assessment of airplane’s dynamic characteristic. The main research of this passage is development 2 equipments which can realize 1 DOF force oscillation on pitch movement and yaw/roll movement. By doing this, the researcher can deeply analyze the aircraft’s unsteady aerodynamic characteristics. For all, the main work of this research as follows.
First of all, it has demonstrated the necessity and possibility by investigation the domestic and foreign thesis about the aerodynamic derivatives’research actuality. More the equations of aerodynamic derivatives extracting have been created by the mass-spring and Small Disturbance.
Secondly, this paper has researched the hardware configuration the dynamic derivatives acquisition system. Base on the mathematic transform, it also has researched the methods of data processing of derivatives. In addition, the methods have been compared with each other.
Thirdly, the cam and parallelogram drive mechanisms both can realize the pitch force oscillation, for this, this paper has argument the 2 methods and chosen the parallelogram drive mechanism for this research. Base on the virtual prototyping technology, the work of pitch force oscillation and yaw/roll force oscillation has been done. Except this, to reduce vibration during the test time, the pole wires have been designed by taking reduce vibration into count.
At last, carry out wind tunnel validate test by using the pitch force oscillation rig and compared the acquired data with others which had been acquired from other wind tunnels and other rigs. After doing this, we can get a conclusion that the data which have been tested by pitch force oscillation rig are rational and reliable, the rig can be used to design of an aircraft and research of aerodynamics.
引文
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[2] T.Flangham. Aircraft Motion Sensitivity To Dynamic Stability Derivatives[C]. AIAA79-1621
[3]孙海生,飞行器低速大迎角动稳定性风洞试验技术研究[D].西北工业大学.2003.5
[4] Jean Christophe. A New Rig for Flight Mechanics Studies in the ONERA Aerothermodynamic Test Center of Modane[R]. ONERA.AIAA80-0464.1980
[5] Alemdaroglu. N, Iyigun.I, Altun.M,etc. Determination of Dynamic Stability Derivatives Using Forced Oscillation Technique[R]. AIAA 2002-0528.2002
[6] Sue B. Grafton and Charles E.libbey. Dynamic stability derivatives of A twin-Jet Flighter Model for Angles of Attack from -10°to 110°[R].Langley Research Center.NASA TN D-6091.1971
[7] Sue B. Grafton, Lysle P. Parlett and Charles C.Smith, Jr. Dynamic Stability Derivatives of A Jet Transport Configuration with High Thrust-Weight Ratio and An Externally Blown Jet Flap [R]. Langley Research Center. NASA TN D-6440. 1971-9
[8] Dietrich Altenkirch. Flight Mechanics Analysis of The Dynamic Derivatives of The Dornier Variable Wind Tunnel Model. ESA-TT-854.1984.10
[9] D. Bruce Owens, Jay M. Brandon, etc. Overview of Dynamic Test Techniques for Flight Dynamics Research at NASA LaRC (Invited)[R]. NASA Langley Research Center, Hampton, VA, 23681
[10]孙海生. 96型低速大攻角动导数试验系统[J].流体力学试验与测量.1999.5
[11]杨恩霞,孔凡凯,刁彦飞.大攻角动导数支撑系统的设计与研究[J].哈尔滨工程大学学报,第17卷第2期,1999.6
[12] Thomas Loeser, Andreas Bergmann. Development of The Dynamic Wind Tunnel Testing Capabilities at DNW-NWB[J] AIAA 2003-453
[13] Makoto Ueno and Hitoshi Miwa. New Dynamic Stability Equipment for Transonic wind Tunnel Testing at NAL[J] AIAA2001-0406
[14]楼海烨李祥瑞等.大展弦比高平尾民用飞机的低速动导数试验[R].中国航空工业总公司.1995
[15]杜希奇,王学俭等.动导数支架干扰的试验研究[J].流体力学试验与测量.2003.6
[16]潘文欣,翟曼玲等.10°尖锥标模高超声速动导数的试验测量[J].空气动力学学报第15卷,1997.
[17]赵忠良,任斌. 1.2米风洞大攻角动导数试验技术[J].流体力学试验与测量1998.5
[18]吴东升,田利安.××型号1.2m风洞自由翻滚/强迫振动装置研究[J].流体力学试验与测量. 2001.9
[19]李潜.地面效应对飞机动稳定性的影响[C].中国航空学会2007年学术年会,气动专题67.
[20] Byeong-Hee Chang,Sang-oh Cho,etc. Development of Dynamic Stability Derivatives of An Airplane from Static Wind Tunnel Tests. AIAA 2004-112
[21]赵忠良,任斌,黄叙辉.SDM标模大攻角动导数试验[J].航空学报1998.5
[22]孙海生,张钧.Φ3.2米低速风洞滚转/偏航振荡试验装置设计报告[R].中国空气动力研究与发展中心低速所.2008年
[23]孙海生,张钧.Φ3.2米低速风洞俯仰振荡试验装置设计报告[R].中国空气动力研究与发展中心低速所.2009年
[24]黄达,张文华.非定常风洞洞壁干扰研究[J].空气动力学学报.第22卷第4期,2004.12
[25]黄达.飞行器大振幅运动非定常空气动力特性研究[D].南京航空航天大学.2007.01
[26]郁飞鹏,贾鸿社.ADAMS与UG、SolidWorks的数据交换实践[J].工艺与工艺装备.2005.03
[27]张胜利.Pro/E、ADAMS、与ANSYS在机械系统设计中的联合运用[J].机械设计与制造.2005.11
[28]刘小平,郑建荣,朱治国等.SolidWorks与ADAMS/View之间的图形数据交换研究[J].机械工程师.2003.12
[29]汪伟,宋嗣新.基于ADAMS和ANSYS的垃圾粉碎机运动部件设计[J].郑州轻工业学报(自然科学版).2006.11
[30]陈立平,张雯清,任卫群等.机械动力学分析及ADAMS应用教程[M].北京.清华大学出版社.2005年
[31]方振平,陈万春等.航空飞行器飞行动力学[M].北京.北京航空航天大学出版社.2005
[32] Torulf Jansson and Lars Torngren. New Dynamic Testing Technique and Related Results at FFA[R]. The Aeronautical Research Institute of Sweden(FFA),S-16111 Bromma,Sweden.AD-P005024.
[33]徐灏,邱悬怀,蔡春源等.机械设计手册[M].第1卷第3篇第3章,北京:机械工业出版社.1991
[34]戴振东,岳林.机械设计基础[M].北京:国防工业出版社,2005
[35]孙海生,姜裕标,黄勇,刘志涛.飞机模型大振幅振荡气动特性及支架干扰试验研究[R].中国空气动力研究与发展中心低速所.2006
[36]恽起麟.风洞试验[M].北京:国防工业出版社,2003
[37]李军、邢俊文、覃文洁等.ADAMS实例教程[M].北京:北京理工大学出版社.2002.7
[38]洪学玲.基于ADAMS的小车式起落架着陆及全机滑跑动态仿真[D].南京航空航天大学,2008
[39] Marc J. M. Mulkens and Albert O. Ormerod. Measurements of Aerodynamic Rotary Stability Derivatives Using a Whirling Arm Facility[J]. Cranfield Institute of Technology, Cranfield, Bedfordshire MK 43 OAL, England, UK. Journal of Aircraft. 1993.4
[40]周述光.低速风洞滚转/偏航振荡试验技术研究及数据分析[D].中国空气动力研究与发展中心.2008
[41]张扬.飞行器低速动稳定性特的试验与计算研究[D].中国空气动力研究与发展中心.2007
[2] T.Flangham. Aircraft Motion Sensitivity To Dynamic Stability Derivatives[C]. AIAA79-1621
[3]孙海生,飞行器低速大迎角动稳定性风洞试验技术研究[D].西北工业大学.2003.5
[4] Jean Christophe. A New Rig for Flight Mechanics Studies in the ONERA Aerothermodynamic Test Center of Modane[R]. ONERA.AIAA80-0464.1980
[5] Alemdaroglu. N, Iyigun.I, Altun.M,etc. Determination of Dynamic Stability Derivatives Using Forced Oscillation Technique[R]. AIAA 2002-0528.2002
[6] Sue B. Grafton and Charles E.libbey. Dynamic stability derivatives of A twin-Jet Flighter Model for Angles of Attack from -10°to 110°[R].Langley Research Center.NASA TN D-6091.1971
[7] Sue B. Grafton, Lysle P. Parlett and Charles C.Smith, Jr. Dynamic Stability Derivatives of A Jet Transport Configuration with High Thrust-Weight Ratio and An Externally Blown Jet Flap [R]. Langley Research Center. NASA TN D-6440. 1971-9
[8] Dietrich Altenkirch. Flight Mechanics Analysis of The Dynamic Derivatives of The Dornier Variable Wind Tunnel Model. ESA-TT-854.1984.10
[9] D. Bruce Owens, Jay M. Brandon, etc. Overview of Dynamic Test Techniques for Flight Dynamics Research at NASA LaRC (Invited)[R]. NASA Langley Research Center, Hampton, VA, 23681
[10]孙海生. 96型低速大攻角动导数试验系统[J].流体力学试验与测量.1999.5
[11]杨恩霞,孔凡凯,刁彦飞.大攻角动导数支撑系统的设计与研究[J].哈尔滨工程大学学报,第17卷第2期,1999.6
[12] Thomas Loeser, Andreas Bergmann. Development of The Dynamic Wind Tunnel Testing Capabilities at DNW-NWB[J] AIAA 2003-453
[13] Makoto Ueno and Hitoshi Miwa. New Dynamic Stability Equipment for Transonic wind Tunnel Testing at NAL[J] AIAA2001-0406
[14]楼海烨李祥瑞等.大展弦比高平尾民用飞机的低速动导数试验[R].中国航空工业总公司.1995
[15]杜希奇,王学俭等.动导数支架干扰的试验研究[J].流体力学试验与测量.2003.6
[16]潘文欣,翟曼玲等.10°尖锥标模高超声速动导数的试验测量[J].空气动力学学报第15卷,1997.
[17]赵忠良,任斌. 1.2米风洞大攻角动导数试验技术[J].流体力学试验与测量1998.5
[18]吴东升,田利安.××型号1.2m风洞自由翻滚/强迫振动装置研究[J].流体力学试验与测量. 2001.9
[19]李潜.地面效应对飞机动稳定性的影响[C].中国航空学会2007年学术年会,气动专题67.
[20] Byeong-Hee Chang,Sang-oh Cho,etc. Development of Dynamic Stability Derivatives of An Airplane from Static Wind Tunnel Tests. AIAA 2004-112
[21]赵忠良,任斌,黄叙辉.SDM标模大攻角动导数试验[J].航空学报1998.5
[22]孙海生,张钧.Φ3.2米低速风洞滚转/偏航振荡试验装置设计报告[R].中国空气动力研究与发展中心低速所.2008年
[23]孙海生,张钧.Φ3.2米低速风洞俯仰振荡试验装置设计报告[R].中国空气动力研究与发展中心低速所.2009年
[24]黄达,张文华.非定常风洞洞壁干扰研究[J].空气动力学学报.第22卷第4期,2004.12
[25]黄达.飞行器大振幅运动非定常空气动力特性研究[D].南京航空航天大学.2007.01
[26]郁飞鹏,贾鸿社.ADAMS与UG、SolidWorks的数据交换实践[J].工艺与工艺装备.2005.03
[27]张胜利.Pro/E、ADAMS、与ANSYS在机械系统设计中的联合运用[J].机械设计与制造.2005.11
[28]刘小平,郑建荣,朱治国等.SolidWorks与ADAMS/View之间的图形数据交换研究[J].机械工程师.2003.12
[29]汪伟,宋嗣新.基于ADAMS和ANSYS的垃圾粉碎机运动部件设计[J].郑州轻工业学报(自然科学版).2006.11
[30]陈立平,张雯清,任卫群等.机械动力学分析及ADAMS应用教程[M].北京.清华大学出版社.2005年
[31]方振平,陈万春等.航空飞行器飞行动力学[M].北京.北京航空航天大学出版社.2005
[32] Torulf Jansson and Lars Torngren. New Dynamic Testing Technique and Related Results at FFA[R]. The Aeronautical Research Institute of Sweden(FFA),S-16111 Bromma,Sweden.AD-P005024.
[33]徐灏,邱悬怀,蔡春源等.机械设计手册[M].第1卷第3篇第3章,北京:机械工业出版社.1991
[34]戴振东,岳林.机械设计基础[M].北京:国防工业出版社,2005
[35]孙海生,姜裕标,黄勇,刘志涛.飞机模型大振幅振荡气动特性及支架干扰试验研究[R].中国空气动力研究与发展中心低速所.2006
[36]恽起麟.风洞试验[M].北京:国防工业出版社,2003
[37]李军、邢俊文、覃文洁等.ADAMS实例教程[M].北京:北京理工大学出版社.2002.7
[38]洪学玲.基于ADAMS的小车式起落架着陆及全机滑跑动态仿真[D].南京航空航天大学,2008
[39] Marc J. M. Mulkens and Albert O. Ormerod. Measurements of Aerodynamic Rotary Stability Derivatives Using a Whirling Arm Facility[J]. Cranfield Institute of Technology, Cranfield, Bedfordshire MK 43 OAL, England, UK. Journal of Aircraft. 1993.4
[40]周述光.低速风洞滚转/偏航振荡试验技术研究及数据分析[D].中国空气动力研究与发展中心.2008
[41]张扬.飞行器低速动稳定性特的试验与计算研究[D].中国空气动力研究与发展中心.2007