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019-液体火箭增压输送系统多学科动力学研究
: B4 j+ f' O% c% {1 L% a020-直接驱动阀的阀芯摩擦力自适应补偿研究* N; F7 w! l3 J6 h" |
直接驱动阀的阀芯摩擦力自适应补偿研究4 G9 A( d# g0 m) M
夏立群, 牛世勇6 h7 P. T" U- E- c
（西北工业大学 自动化学院，陕西 西安 710062）4 L- k$ [: e# v+ p1 d' v
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
6 ]/ @' s F- r6 F9 ?2 P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
, Y% c$ M8 Z' K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
% ~# H6 c W+ t# a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。
1 s2 G5 H2 \ _5 R0 U9 k! v关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制4 k! f+ E5 [2 ^9 {8 ~" F1 \
中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
( @: }6 u" C; f8 vResearch of Adaptive Friction Compensation for Direct Drive Valve
) B4 ?: L% j ?& G. DXIA Li-qun, NIU Shi-yong
8 I* @1 m9 u8 v* _9 V- J' @% M) B（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
' G& g8 t J p& d! Z+ p, CAbstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several
2 R' V0 A/ ?. |( Z% n' Wmodel of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an R! E; Z) a* a& G% X. D& D
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation3 o4 p- E: R& ]" p0 a f
models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The0 u: O: y2 Z3 I9 z; p+ I; q
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
3 U$ b* q4 M5 gnonlinearity due to friction./ `7 S, q2 m. c: e8 ~
Key words: friction compensation; direct drive valve; LuGre model; adaptive control
! X3 X5 h( C/ Y6 a8 a: I8 T032-仿真技术在飞机起落架可靠性分析中的应用研究$ s. i' F1 X9 H0 c+ A# G( q f
仿真技术在飞机起落架可靠性分析中的应用研究0 i. X& w( ~) y
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋... G. z7 H+ ]2 X" j2 S
(1.西北工业大学航空学院, 西安7 100 72 )( ?% E2 _1 P& c. @( m1 C" V4 q
(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 ..
8 p+ T! g: J& {2 ]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
; J4 {- K, K/ r- t' l) A' f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
$ G( O, g$ M) x! yvi 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
8 v3 g3 N/ V5 t8 t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
# t) g/ D3 t7 i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" ?$ n' ^ e& B/ I* e+ g
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/ E- _; o) L+ z) s8 X- U2 g
杂机构可靠性分析具有可行性和实用性..8 n: c* R6 M. J+ I
关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
) `, X+ ^7 G: ]中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
: N0 N2 P& b! e* s( W* B9 W2 fA 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
( V/ r" _; E6 }9 s7 t, h6 sA ir e r a ft L a n d in g G e a r S y ste m
$ z' ~# R) _" k+ ]. dZ 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 i0 F& J( x2 ^) i. t
( 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 )* U! g w E" q' Q% A- f
( 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( E" d/ T6 S. D5 r' L, S# dC 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 )5 a4 o+ p9 C8 m0 T; X3 X8 U
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! r4 K* g+ C5 A, x0 R* x+ D
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$ Y$ v4 D. p/ L0 c' E: R
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
5 d! F |/ t0 Lfa 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
% j. l8 O4 r/ M/ x. ae 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: [' h$ V2 B3 \* O5 K& N
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& g2 \2 K8 H( d! y7 m
o 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 -
* a2 S9 p" O! J: |+ ~: K) Wb 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 j8 c3 g0 z" o' r" Jl 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 ,* c" L0 O% u" Z
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 -
3 g, k q" A9 I" i5 p7 L" t. Dfo 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
2 H; M1 ]' b' j5 E3 |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.
7 v4 y j9 z* n: h5 QK 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- r4 g$ M" e) t
5 Z! Y( T6 [0 \# ?1 J: O. S
Flight Control.part02.rar
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发表于 2013-3-25 20:56:44