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019-液体火箭增压输送系统多学科动力学研究
V$ h5 }$ J( o6 I% ?! {% d020-直接驱动阀的阀芯摩擦力自适应补偿研究( g' M, l6 @9 M* i. d2 q
直接驱动阀的阀芯摩擦力自适应补偿研究4 j' a" q' }* g1 d, q2 Y
夏立群, 牛世勇& i0 X, @! Z g+ b) j! e( `
（西北工业大学 自动化学院，陕西 西安 710062）
7 a* v% l8 ^/ _0 O) n4 S摘要：针对直接驱动阀阀芯摩擦力，论述了基于模型的摩擦力自适应补偿。描述了几种摩擦力4 t0 q. u2 K1 F. z2 o7 i
的动静态模型，建立了直接驱动阀的动态模型，设计了基于摩擦力动态补偿的自适应补偿器，并; {5 Q( _2 _& f6 |8 L, A
采用SIMULINK 和AMESIM 联合仿真进行了验证。结果表明：基于LuGre 模型的摩擦力自适应
5 W: j( K2 O3 o! p7 V3 ^$ N \动态补偿控制器能够有效改善摩擦的非线性特性对DDV 式作动器性能的影响。' m/ E. X- @! D1 |
关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制" J% Z5 v0 Z- S2 j' ^: a- Y. ?
中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03! M8 U2 G( K( b, T
Research of Adaptive Friction Compensation for Direct Drive Valve6 C8 s! M6 s" `) B! x( P9 \0 w2 K% }
XIA Li-qun, NIU Shi-yong* n- B! z+ s( Z) }# G# t
（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)! O/ v3 R+ J: n: J, r2 ^
Abstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several
7 B: l3 W0 K/ N0 ^2 Gmodel of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an
% x, }* ]) k& c- I7 h4 Q7 Kadaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation; C+ f# d, V: [2 b$ Z! h
models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The
9 s/ H% X0 D* Q( x7 I$ ~results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
4 a+ m$ F4 e* nnonlinearity due to friction.% b8 V" P5 t; k0 O
Key words: friction compensation; direct drive valve; LuGre model; adaptive control
) b0 y' r5 m* V032-仿真技术在飞机起落架可靠性分析中的应用研究 d9 U2 L) A% c/ g* A0 P
仿真技术在飞机起落架可靠性分析中的应用研究4 ]- B1 u/ [8 G2 v5 e3 U( m7 m
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..% c* Z9 Y# ~/ l4 h6 Q) w k
(1.西北工业大学航空学院, 西安7 100 72 )
/ `. {' i" ?3 |7 G. T3 \+ G2 G% H5 g& Z(2 . 中国航空工业集团公司成都飞机设计研究所, 成都6 1 ....理1 ..
, h5 ]+ m+ A% R# I2 {+ j# o摘要: 起落架所承受的动载荷较大, 造成系统工作环境复杂, 出现故障较多, 因此对起落架系统可靠性的研) A* `8 B3 s' Q2 ~$ x4 ?
究显得迫切和重要.. 以三维辅助建模软件..A T IA ..有限元分析软件N A S T R A N ..多体动力学分析软件I M S
; ~. _) H. h3 V5 }$ b. u7 a1 vvi rt ua l.La b 和液压控制仿真软件A M E Si m 等为工具, 采用自动仿真求解策略针对某起落架典型失效模式进
3 N: {% d6 G/ k* q5 ]行仿真分析, 得到仿真分析数据的数据库, 并通过各平台下数据之间的共享和融合, 结合高精度..高效率的,叮靠2 h) f4 ~& Q- _4 _; N
性分析方法,实现起落架典型失效模式的可靠性仿真分析.. 结合某飞机起落架落震可靠性分析案例,结果表" v' d$ v1 p! v$ n- t& c8 B6 l
明:采用仿真技术建立仿真模型, 通过分析机构失效机理和失效模式, 结合可靠性分析方法进行起落架系统复9 O6 L, }- i) o/ `: o# t, ~
杂机构可靠性分析具有可行性和实用性.. Y. D* ^* P; }8 Y
关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
1 {" P& W- W _' l中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
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C o rp o ra tio n ()f C h in a , C h e n g d u 6 1 0 0 4 1 , C h in a )
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fa ilu r e m o d e o f th e la n d in g g e a r. T h e m e th o d a d o p ts a u to m a tie sim u la tlo n s o lu t io n s t r:..re g y b y tl s in g th e 3 1) a id
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K e y w o rd s : la n d in g g e a r s im u la tio n ; re lia b ility a n a ly s is ; h y b rid s一m u la tlo n ; d ro p s in i u la tio n
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Flight Control.part02.rar
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发表于 2013-3-25 20:56:44