三环驱动轴对称矢量喷管喉道逆运动学建模

李建鹏; 赵志刚; 李有德; 孟佳东

doi:10.13433/j.cnki.1003-8728.2017.0427

三环驱动轴对称矢量喷管喉道逆运动学建模

doi: 10.13433/j.cnki.1003-8728.2017.0427

1.
兰州交通大学机电工程学院, 兰州 730070

详细信息

作者简介:
李建鹏(1991-),硕士研究生,研究方向为轴对称矢量喷管的优化设计及控制,ljplzjtedu@163.com

通讯作者:
赵志刚(联系人),教授,博士,zhaozhg@mail.lzjtu.cn

计量
- 文章访问数: 131
- HTML全文浏览量: 30
- PDF下载量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2015-07-31
- 刊出日期: 2017-04-05

Inverse Kinematics Modeling for Throat Area of Axial-symmetric Vectoring Exhaust Nozzle Driving by Three Rings

1.
School of Mechatronic Engineering, Lanzhou Jiaotong University, Lanzhou 730070, China

摘要

摘要: 三环驱动推力矢量喷管是一种收-扩式轴对称推力矢量喷管，针对某三环驱动轴对称推力矢量喷管，利用拆杆法和相对转角法建立了轴对称矢量喷管喉道面积调节结构运动学模型，运用CATIA软件完成了轴对称矢量喷管各零件的建模和虚拟装配，并将装配体导入到ADAMS软件中进行仿真，验证了结构设计的合理性和所建模型用于喉道面积控制的有效性。对三环驱动轴对称推力矢量喷管的优化设计及控制器的设计与应用提供了一定的理论基础。
- 三环驱动轴对称矢量喷管 /
- 喉道面积 /
- 逆运动学建模 /
- 仿真
Abstract: The axial-symmetric vectoring exhaust nozzle driving by three ringsis one of the convergent/divergent type nozzles. In this paper, the inverse kinematics modeling for throat area of axial-symmetric vectoring exhaust nozzle is given by using the relative rotation angle method. The three dimensional model for nozzle was built via CATIA software and its kinematics simulation was carried out via ADAMS, the computer simulation results showed that the mechanic design was reasonable and the kinematics modeling was effective, which provided an important reference for optimizing and controllingthe axial-symmetric vectoring exhaust nozzles driving by three rings.
- axial-symmetric vectoring exhaust nozzles driving by three rings /
- throat area /
- inverse kinematics modelling /
- computer simulation

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参考文献(16)

[1]	Hauer T A. Axisymmetric vectoring exhaust nozzle: US 4994660[P]. 1991-02-19
[2]	王玉新.喷气发动机轴对称推力矢量喷管[M].北京:国防工业出版社,2006:1-19 Wang Y X. Axian-symmetric vectoring exhaust nozzle for jet-thrust-aircraft[M]. Beijing: National Defence Industry Press, 2006:1-19 (in Chinese)
[3]	丁凯锋,樊思齐.矢量喷管与发动机的共同工作研究[J].航空动力学报,2000,15(1):93-95 Ding K F, Fan S Q. A study on Co-Operating between thrust vectoring nozzle and aeroengine[J]. Journal of Aerospace Power, 2000,15(1):93-95 (in Chinese)
[4]	Benjamin G-O. Future jet technologies, Part C[J]. International Journal of Turbo and Jet-Engines, 2013,30(2):133-143
[5]	王玉新,王仪明,李雨桐.轴对称推力矢量喷管载荷变形的控制补偿[J].航空动力学报,2007,22(10):1685-1689 Wang Y X, Wang Y M, Li Y T. Load deformation compensation of the axisymmetric vectoring exhaust nozzle[J]. Journal of Aerospace Power, 2007,22(10):1685-1689 (in Chinese)
[6]	Matesanz A, Velazquez A, Rodriguez M. Mach disk simulation in jets from convergent-divergent axisymmetric and thrust-vectoring nozzles[C]//Fluid Dynamics Conference. Colorado Springs, CO: AIAA, 1994
[7]	高阳,白广忱,于霖冲.矢量喷管柔性机构运动及可靠性仿真[J].系统仿真学报,2006,18(S2):175-178 Gao Y, Bai G C, Yu L C. Simulation and reliability analysis of axisymmetric vectoring exhaust nozzle flexible mechanism[J]. Journal System Simulation, 2006,18(S2):175-178 (in Chinese)
[8]	蒲雪萍.轴对称矢量喷管控制系统半物理仿真试验[J].燃气涡轮试验与研究,2003,16(2):18-21 Pu X P. A Semi-physical simulation of axisymmetric vectoring nozzle[J]. Gas Turbine Experiment and Research, 2003,16(2):18-21 (in Chinese)
[9]	唐宇峰,沈锡钢,李泳凡,等.喷管喉道面积变化对大涵道比分排涡扇发动机性能的影响[J].航空发动机,2011,37(1):12-15,19 Tang Y F, Shen X G, Li Y F, et al. Effect of nozzle throat area variation on performance of high bypass ratio turbofan engine with separate flow[J]. Aeroengine, 2011,37(1):12-15,19 (in Chinese)
[10]	王莉,袁茹,王三民,等.温固耦合下轴对称推力矢量喷管驱动机构的运动精度分析[J].机械科学与技术,2008,27(6):752-756 Wang L, Yuan R, Wang S M, et al. Kinematic precision analysis of axial-symmetric vectoring exhaust nozzle with coupling of temperature and structure[J]. Mechanical Science and Technology for Aerospace Engineering, 2008,27(6):752-756 (in Chinese)
[11]	杨军刚,张卫红.轴对称推力矢量喷管调节环结构优化设计研究[J].机械制造,2012,50(4):16-19 Yang J G, Zhang W H. The research of optimization design for Axisymmetric thrust vectoring nozzle adjustment ring structure[J]. Machinery, 2012,50(4):16-19 (in Chinese)
[12]	张春林.高等机构学[M].北京:北京理工大学出版社,2005:60-72 Zhang C L. Advanced kinematics and dynamics of mechanisms[M]. Beijing: Beijing Institute of Technology Press, 2005:60-72 (in Chinese)
[13]	额日其太,李喜喜,王强.轴对称喷管喉道面积射流控制数值模拟研究[J].推进技术,2010,31(3):361-365 Eriqitai, Li X X, Wang Q. Computational investigation on axisymmetric nozzles with fluidic injection for throat area control[J]. Journal of Propulsion Technology, 2010,31(3):361-365 (in Chinese)
[14]	Williams R G, Vittal B R. Fluidic thrust vectoring and throat control exhaust nozzle[C]//38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Joint Propulsion Conferences. Indianapolis, Indiana: AIAA, 2002
[15]	Saito T, Fujimoto T. Numerical studies of shock vector control for deflecting nozzle exhaust flows[M]//Hannemann K, Seiler F. Shock Waves. Berlin Heidelberg: Springer, 2009:985-990
[16]	Deere K A, Berrier B L, Flamm J D, et al. Computational study of fluidic thrust vectoring using separation control ina nozzle[C]//21st AIAA Applied Aerodynamics Conference. Orlando, Florida: AIAA, 2003