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019-液体火箭增压输送系统多学科动力学研究, v4 T: v0 U6 g% E+ E# X
020-直接驱动阀的阀芯摩擦力自适应补偿研究2 Z6 M/ I6 k. d$ [
直接驱动阀的阀芯摩擦力自适应补偿研究
1 P4 y9 Y/ ~; N1 g: r夏立群, 牛世勇
/ Z U% e& c7 Q7 n: f* T（西北工业大学 自动化学院，陕西 西安 710062）
/ f" G$ }- d U6 R6 ^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. B; |! \1 U/ a2 n3 z; c
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
( H+ X3 J9 t R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
% N5 `3 f; ~8 w* p/ h$ J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。, g) v! y# W& @) M
关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
9 H2 x1 e& d# ?0 s0 T( ~! k中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
: A6 h" F' e& n- R' b8 D# W% iResearch of Adaptive Friction Compensation for Direct Drive Valve
, ?! Q2 z6 p, X3 U* U" ZXIA Li-qun, NIU Shi-yong. S+ F% o& [% P6 X5 D
（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)) U" u$ l4 q0 _! W; [) g
Abstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several4 r1 y4 [' e8 m5 V: f" A
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an& k1 u# r/ _6 e, V, a& B
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation
$ |7 D1 [6 {+ y0 L- Umodels based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The# ]5 F9 o& C$ r; _
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
$ ~* o0 ^7 N# l4 fnonlinearity due to friction., k# y/ W4 t; ^8 f8 I: J
Key words: friction compensation; direct drive valve; LuGre model; adaptive control; [: S# @% t% r! y- i
032-仿真技术在飞机起落架可靠性分析中的应用研究
D3 Z4 T+ {" R, m; g" H7 G! h仿真技术在飞机起落架可靠性分析中的应用研究: T+ O4 c8 p! h% i9 M- t
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..
/ U" W Q/ ~! u$ T' R(1.西北工业大学航空学院, 西安7 100 72 )/ Q5 I3 w! O; H/ ~- J
(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 ..& ]: F0 ~0 N: 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- M3 c) W0 H: V
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
( Q7 ?4 Y$ T' O" ]4 _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
; H% e4 Q/ q* D* v: ?7 }" 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
$ [4 p" P2 H" B4 O7 M$ Y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# y5 ~0 }/ s& R
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
4 K' o, B- K! u! u杂机构可靠性分析具有可行性和实用性..1 O. M: `& u9 C; \# g) y( E
关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
8 {- N9 k9 z: Z0 P) Z1 U% y中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
4 ]% O8 y- I" _5 ^) L' I/ UA 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
, g8 L7 u! ]- M. W/ h6 W( V2 o: `A ir e r a ft L a n d in g G e a r S y ste m
1 g4 g* I9 U6 SZ 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 ..
: Z" c: K7 u9 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 )
9 N2 E% t2 G+ {) S; H8 j; d( 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
4 P$ r8 V. B1 h0 f0 R/ w5 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 ); z% R9 [9 P9 l. y( L: c
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7 C; n# F4 {- G1 N0 oim 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
6 [# S- ?7 y) J; @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
5 o- b6 n# H6 ^! ?$ oe 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" A' v, u. @& A& r3 K
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) F T4 }& ^! i7 u" i- u z% p
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 -. l" n8 _) e0 ?' {% f, _3 U6 {
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
1 L6 E! L) {3 M$ {1 O. u. `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 ,) q' ]. ~" e4 p! C( Q3 A# v
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 -/ ~# {/ y/ }. l% E
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+ c. r, w- b- W5 N+ s7 p
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.; F" B$ T6 V- g0 h1 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
" |+ M$ o Q8 a) H( i' @. J5 B" U8 t8 z8 D8 w' U) h
Flight Control.part02.rar
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发表于 2013-3-25 20:56:44