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019-液体火箭增压输送系统多学科动力学研究& x2 {. M; @8 T: \& r: w, c
020-直接驱动阀的阀芯摩擦力自适应补偿研究
: L9 s0 S( p6 H# I直接驱动阀的阀芯摩擦力自适应补偿研究% u2 r2 C* R9 [) M% H: }: X
夏立群, 牛世勇# e6 S# d8 ]" \7 @
（西北工业大学 自动化学院，陕西 西安 710062）
, |! ~2 `4 j/ u% I! A" ]% h& O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) q, z' K8 `( d* x8 T
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
% |" Z7 z" T0 J+ @& {/ H$ j! `; H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
8 |: q/ E% h- o4 _) Y1 w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。
) @' j X7 [3 c$ s% b关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
4 F' b4 W) n; {" m- I# z中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
# N, n7 {% t: b6 M2 m6 iResearch of Adaptive Friction Compensation for Direct Drive Valve
9 }! N5 ] ^ ]! l/ b- j5 h8 uXIA Li-qun, NIU Shi-yong. I+ I. l0 W, `6 P$ x: G2 F7 m; R
（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
9 T, @# }4 F. M1 p, b; ^: r vAbstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several
, |0 h$ s7 @' Q. k+ S) ymodel of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an4 j5 E, A: H0 S3 n! d4 t/ |, w
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation
4 C. c3 R4 A# O8 C% }models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The/ b4 o# y, b3 a4 I' W# r! J/ C7 ]
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard; r h* y; ?4 P3 q$ G
nonlinearity due to friction./ m- C+ u' G H# @1 H5 u/ i- M5 N* F
Key words: friction compensation; direct drive valve; LuGre model; adaptive control
8 ?+ h. t+ y1 }/ |8 I( t* k, U032-仿真技术在飞机起落架可靠性分析中的应用研究; B* K; W$ P( z" V9 u
仿真技术在飞机起落架可靠性分析中的应用研究
) U* u( D( S. V# ^1 G赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..
+ R' ?& n$ H; U9 e/ {0 c(1.西北工业大学航空学院, 西安7 100 72 )& K8 H8 c- u2 I' [2 F" U- I
(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 ..
: B e6 ^6 r4 K6 C8 C$ @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$ P, }# V! `! `; x2 B
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
3 t! f, X# A! Svi 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
# f, A. d. | p0 r5 V3 N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/ e* u+ y* Q9 {% ?$ h
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: P. l. I0 ]' f! [/ ]( J
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) w9 v) e0 t/ L, I$ A
杂机构可靠性分析具有可行性和实用性.." e) _; S" [: L# u, i
关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
" e5 [) W% r4 d3 d6 H- @* z, l中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
9 V' M& j1 A( r* QA 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 r6 N: i+ ^3 \1 Z5 T
A ir e r a ft L a n d in g G e a r S y ste m' C' Z6 h) c( j+ u$ h3 P' A
Z h a o S h ieh u n ..,2 , Y u T ia n x ian g l , W a n g H u il , S o n g B ife n g ..
4 \' t! q# E' O. S3 |9 ?( 1 . S e h o o l o f A e ro n a u tie s , N o r th w e s te rn o f P o ly t ee h n iea l U n iv e r sity , X i ..a n 7 1 0 0 7 2 , C h in a )
- i" V% y6 r& F! N( 2 . C h e n g d u A ir e ra ft l)e s ig n R e s e a re h I n s ritu te , A v za tio n In d u s try" m$ U' K/ t$ ^
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 )
- ?3 e3 F# Z6 o% s$ C6 nA 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: T! P9 [; S$ {) ha 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
1 |* v% O. ?/ e9 }2 }im 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
& s; O& p: W; ^% m* F: ?- Xfa 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
, V) I& L! b+ p2 ?) l' me 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 sls
3 ^; H/ g5 _& Jso 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
n) m* e" v t5 |1 A" ]. so 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 -
, d( g$ L5 V1 G% y: @9 qb 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 lea3 ~2 o4 G) M+ n6 y( F7 R; O
l 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 ,5 s/ |/ P. o% X, p
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 -
. Z5 a6 h/ C" h2 M+ \fo 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
0 \, U u u1 g4 j9 V* S0 @p 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.% Q3 X+ }" c$ ?: w# s
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; T0 Y1 n$ p/ [' i0 p- L. G
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Flight Control.part02.rar
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发表于 2013-3-25 20:56:44