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019-液体火箭增压输送系统多学科动力学研究% `! u! M! k- J- s |! [0 T
020-直接驱动阀的阀芯摩擦力自适应补偿研究
, n9 ~" ?( q. G2 p, Y% Q直接驱动阀的阀芯摩擦力自适应补偿研究; C" ]& O! \" N3 y: _
夏立群, 牛世勇 T3 A a9 }0 l$ y j0 ?
（西北工业大学 自动化学院，陕西 西安 710062）
3 K$ z6 X" \3 ?& u3 |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
: s8 ~* n" q* Q, A7 f: ]* x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3 S( r1 Y* `- ]; S E1 _
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
. }+ L" G2 ^( s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。
: x6 P# A) Q4 D S+ ]关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
; B* e, W0 b: [6 h, N6 a中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03' U* {! O* c* D8 \& }0 [
Research of Adaptive Friction Compensation for Direct Drive Valve: l7 n' `3 k5 k* x! d
XIA Li-qun, NIU Shi-yong
" u7 g& l, P* l& x( f（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
' M; C9 S0 y3 U$ c) xAbstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several* J9 j8 I \7 D4 z& L
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an' J! {8 }" a* i2 Y9 u8 L3 ~. t) m
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation9 U8 k8 X3 `0 h# o+ T* g* |
models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The3 [- m( m9 X+ ]
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard% K% ~+ L7 f6 H% n
nonlinearity due to friction.- | z9 C% ?+ x+ Y5 I* }) ]" {% l
Key words: friction compensation; direct drive valve; LuGre model; adaptive control; } K/ c- U0 i2 {
032-仿真技术在飞机起落架可靠性分析中的应用研究
) h2 Z' F# g$ g6 x5 `/ [# S P$ P6 S仿真技术在飞机起落架可靠性分析中的应用研究, `5 m9 S$ E5 v. z
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..
1 w8 @, N7 j% i9 h(1.西北工业大学航空学院, 西安7 100 72 )
! e8 r5 e/ G7 E# @2 T" ?( G% Z(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 ..: t0 F" p" G; F9 p9 N9 P' I
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! n5 m3 P8 J ?7 S
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$ P9 `- w1 z' y8 T: B. `
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 A6 {$ M* I1 F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
6 b) f2 ^* m/ @5 {* z( R" A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' h$ T* O8 q! Y/ h' v- _& @
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
- i6 a3 n I3 P6 L杂机构可靠性分析具有可行性和实用性..+ j( z% ?3 @% n: s
关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真1 M0 M9 U' a3 r) g
中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A' i0 [8 H# f5 c( f+ ~; U3 Q3 B$ ?+ I
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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
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Flight Control.part02.rar
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发表于 2013-3-25 20:56:44