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019-液体火箭增压输送系统多学科动力学研究
: O4 Y _' b0 ~2 m# `- [1 e020-直接驱动阀的阀芯摩擦力自适应补偿研究/ D* \& c4 [9 b' t, o; I( @0 c
直接驱动阀的阀芯摩擦力自适应补偿研究: O6 D2 Z+ _ K4 i9 c
夏立群, 牛世勇
5 I+ H* F# x. a3 }# y6 y（西北工业大学 自动化学院，陕西 西安 710062）
' d3 M! j6 |0 x9 z. N: J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# o% q( U3 L" m! z
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! l* h9 V# Z5 o9 \
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3 x+ s! O- X/ z" d8 }0 E6 t0 t! M
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。
7 p, x5 ]/ b2 \" m关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制: t9 v$ u2 k7 c. T, q3 [! [- E# Q# F9 i
中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
0 P% Z k. `2 _6 IResearch of Adaptive Friction Compensation for Direct Drive Valve; s4 J! ^$ ~ n0 k
XIA Li-qun, NIU Shi-yong
' z6 g7 [8 q! {- i) d5 T（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
, B% u/ P, Z' k7 [3 j/ UAbstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several3 U5 l) u2 v& Y, z$ {
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an
+ k5 R2 V' W. U# t* hadaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation
7 b8 {; a) M( h; z# Y: Q# ^0 S1 umodels based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The
* z8 q/ d- T5 p, Zresults show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
3 G/ u+ O8 l6 o$ [% m$ v8 b; T1 f4 @nonlinearity due to friction.
8 h8 v8 c2 p8 w4 g0 ?$ U- AKey words: friction compensation; direct drive valve; LuGre model; adaptive control% a: V1 c# v/ F" Z8 S0 m
032-仿真技术在飞机起落架可靠性分析中的应用研究
# T6 d8 _# z! \6 K仿真技术在飞机起落架可靠性分析中的应用研究2 E% P9 H- k9 N5 D, K3 C4 `
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..2 n) \; y3 _4 X: Z( s
(1.西北工业大学航空学院, 西安7 100 72 )
8 D: s9 S5 r3 Z: u8 a- j7 M( l(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 ..9 D' L0 n7 ^* y+ t9 |$ q
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/ w. q( X% n1 }% z! G# l
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
% y E1 i4 H) f. gvi 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$ c( q& Q7 Q$ a [7 R
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
8 m) d Q1 U8 O* q8 f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/ s, t1 F5 e2 [* Y% Z
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/ P F2 P9 B7 R+ G Q5 p
杂机构可靠性分析具有可行性和实用性..
1 x4 [- _) o' T: u6 B关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
, D9 q) P D/ E! S Z中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
7 k- P. y9 n/ K) M# o9 r. V$ F' z PA P P lic a tio n o f S im u la tio n L T e e h n o lo g y o n R e lia b ility A n a ly sis fu r
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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 )
9 M' g7 T2 N0 U+ n( _# ?7 r2 Z; |A b s tra et : D y n a m ie lo a d o f la n d in g g e a r 15 h o v ie r , w h ie h lea d s to eo m p liea te d o p e ra t io n e n v iro n n 飞e n t o f ..y s re tn$ s/ t6 C( U' R( d# Z; Z( S* G' a
a n d m o re fa u lts . 5 0 re s ea re h o n re lla b ilit y o ] a ire r a ft la n d in g g e a r s y ste m b e e o m e s m o r e a n d m (..re e x ig e n r a n d
$ v0 d' r& U( t( F3 @8 gim p o r ta n t. B a s ed o n t h e s im u la t io n a n a ly s is m o d el , rh e p a p e r p r es e n ts re lia b ility a n a ly sis m e th o d fo r th e ty p ze a l
7 c3 y' i9 x! S$ D1 Ufa 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
, }3 v! J n5 _6 W& I2 Be d m o d e lin g s o ftw a re C A T IA , th e fin ite e l.:m e n t a n a ly s is s o fr w a r e N A S T R A N , m u ltib o d y d y n a m ie s a n ,一ly sls6 }9 ?$ E/ L) K6 j' H* {
so ftw a re L M S V irt u a l I a b a n d h y d r a u lie p r .Zss u re eo n r ro l s o ftw o re A M E S im . T h e s im u la tio n a n a ly s 一.. d a ta 15
" S1 Z0 Q! a6 ~- [2 Y, Lo b ta in e d b y a p p ly in g d a ta s h a r in g a n d fu s io ll m e e h a n is rn u n d e r th e d iffe re n t s o ftw a re p la tfo r m s . T h e n . e o m -5 y7 _. V/ t% G: E3 h$ N
b in e d w ith h ig h p r e eis lo n , h ig h e ffieien t rn e tllo d o f re lia b ility a n a ly s ls , re a lize th e re lia b ility a n a ly ..一5 fo r th o ty p lea
+ ^5 K" D9 }1 h5 Kl fa ilu r e m o d e g e a r s im u la tio n . T h e e x a rn p le o f a la n d in g g e a r d ro p re lia b ility a n a ly s is s h o w s th :It th e m e th o d ," r- s+ l9 m3 g; f" o8 s
w h ie h b a se d o n e st a b lis h e d s im u la t io n m o d e ] b y th e eo lla b o ra tiv e s im u la tio n te e h n o lo g y o f m u ltl一s o ftw a r ..一p la t -
% s: w) W' J+ [: Wfo r m a n d th e a n a ly s is o f t h e fa ilu re m e e h a n is m a n d fa ilu re n lo d e s o f m e e h a n ism s y s te m s , 15 o f tllc fe a s 一b 一1一ty a n d
5 d/ Y# y. ^9 ^$ H# i4 ~3 p( D7 hp ra e tie a b ility fo r th e eo m p le x la n d in g g e a r r le e h a n is n : ..y s te m s re lla b llity a n a ly s is.
2 \' N9 }) C; _: bK 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