|
|
马上注册，结识高手，享用更多资源，轻松玩转三维网社区。
您需要 登录 才可以下载或查看，没有帐号？注册
x
019-液体火箭增压输送系统多学科动力学研究( o! b/ n2 {0 K# W7 S n
020-直接驱动阀的阀芯摩擦力自适应补偿研究
' L/ E9 f) |, `, d8 O直接驱动阀的阀芯摩擦力自适应补偿研究
+ m$ h b8 [$ o/ l: `6 _! S' ]5 {夏立群, 牛世勇
! w7 J. l: ?* @（西北工业大学 自动化学院，陕西 西安 710062）) v4 ]: A' Q% P, I; ?) h
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 ^# a( Y4 v" ^0 x2 ]4 q9 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8 t$ f6 G4 |3 [! q6 G1 D
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4 l* \- ~: Z1 B# o5 k. C1 k/ m' g
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。+ D. k2 {" g6 x9 R
关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
# ^8 {+ Z( e% j/ V8 _7 Y! w中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03' D c2 e; R2 S- ]% f
Research of Adaptive Friction Compensation for Direct Drive Valve* C" A" b9 E" N; i+ {3 L
XIA Li-qun, NIU Shi-yong
e' z2 L+ Q/ U8 p（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
* L: J t' n; {. w3 R2 sAbstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several: x3 f5 \/ w+ J1 R; l' V
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an2 `/ F) N9 z9 o4 F3 _/ m
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation
a$ Y9 [ H9 ]/ Pmodels based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The
4 p$ H z7 y) D# R |8 yresults show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard* C1 z' U$ W2 d2 T" V1 c) ?2 ?
nonlinearity due to friction.# q$ Z- K% T8 E4 H" r, F1 Q
Key words: friction compensation; direct drive valve; LuGre model; adaptive control( ^7 \2 M+ k" x$ r, c
032-仿真技术在飞机起落架可靠性分析中的应用研究
, l+ ~' O3 @4 y, C2 Z仿真技术在飞机起落架可靠性分析中的应用研究& {0 V" |; L- x" L1 ^8 S' y3 j! J
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..8 J8 v9 B' v/ |4 r N2 n
(1.西北工业大学航空学院, 西安7 100 72 )# ^# G9 H$ ~. g$ j6 m5 H- _
(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 ..
2 w7 M4 N; B! d' L' 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% w, O5 ]) A9 E! M
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
, r/ `( w4 G! _! ^vi 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
5 w7 R$ E8 ^4 f* M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
9 b; t- K/ w' z0 p! O; W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" @& D+ S7 I! u& n
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
# ~( F1 D% P- m0 q% \: M% I杂机构可靠性分析具有可行性和实用性..
K2 V" g; D% e2 `) H) V关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
4 B* j/ h: h9 ~( }中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A6 B9 b( j P! R1 M* C0 Q
A 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 r3 b" M$ m O8 s3 B; ]
A ir e r a ft L a n d in g G e a r S y ste m
* O4 h7 k3 ]2 |5 u, X, ]; w# vZ 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 ..1 w9 y2 W) }" b
( 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 )
6 a( {$ \. X! m7 Z( 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* E* y% n. ?5 z1 v( R# c ~4 v7 ]
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 )7 t$ I5 d& K( [% p$ r0 A
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
1 a3 m" M" [9 \/ J1 m, b5 w" j0 w9 Va 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% i: ~) u% N. _' _/ I' E
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% l8 U: ]. C8 h! I2 `4 R, y
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
9 D g; j3 C3 M8 Y. S0 e6 b0 ge 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) ~5 B; ?# E1 s4 k; w/ n, C, y! p
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
6 V8 m/ S' [; B8 t# b2 P7 U) ]% n: jo 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 -
- f( K X: A) f6 w! o, n {8 zb 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
( l5 d3 ^) C* D6 k) I' c$ ol 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 ,
$ U- a B" E# C& `3 `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 -( L7 T0 R* S# C
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
9 N, j4 e1 a( b v+ G: y9 b5 O- j" Kp 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.' n, [+ H- O, B& Q! [+ W: B, h7 Y& o
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
( Y& X. [* z* ^
: p6 ?% m4 N @4 @, U! {/ y; `
Flight Control.part02.rar
(512 KB, 下载次数: 0)
|
|
发表于 2013-3-25 20:56:44