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019-液体火箭增压输送系统多学科动力学研究
1 N9 e3 A7 a$ A. Z9 z020-直接驱动阀的阀芯摩擦力自适应补偿研究! Z. N8 \- r; d& v
直接驱动阀的阀芯摩擦力自适应补偿研究
; n7 Q$ p' [2 {$ d& m7 m# S夏立群, 牛世勇
; [/ Y- c; ^- a（西北工业大学 自动化学院，陕西 西安 710062）5 b: ~& g4 D% [: c
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 j Y' W6 z
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1 N% t* O/ m; r, H# z
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 G1 ~0 W; H* R
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。
8 e }: O& g5 O; a. s' k$ t- p关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
9 s% p, K' R' C0 x! b% i中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03( j# K" ~+ p6 q0 ?# D1 `
Research of Adaptive Friction Compensation for Direct Drive Valve0 R" `6 v/ O6 @9 u' b4 T# |! W* @; H
XIA Li-qun, NIU Shi-yong
0 V. Y3 w5 |4 Y+ P- ]（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)4 Y% |) f0 N. g! b( |# e
Abstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several
7 M x7 z& M- ]: k5 Umodel of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an
; t3 n+ x' G+ I: w$ ~( Wadaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation' A$ [" A7 S# M5 R, H8 B+ o
models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The9 z! L: P ]2 H9 O7 Y6 c7 E
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
/ {. }1 k) i) ?7 E+ D: ]/ W2 `; nnonlinearity due to friction.- J, U; H6 j" k. Y% G
Key words: friction compensation; direct drive valve; LuGre model; adaptive control
+ f5 E7 q: M- y! J0 N+ O, N032-仿真技术在飞机起落架可靠性分析中的应用研究, N9 o% [% s+ u$ o1 G
仿真技术在飞机起落架可靠性分析中的应用研究/ s* ?; M8 N% F& n {- X
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..+ C" X0 g; R V) q
(1.西北工业大学航空学院, 西安7 100 72 ). B) S) `0 t8 _' P t7 k, `5 C" t
(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 ..
% `; |/ X0 d8 W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' e4 N4 i8 W3 ]: Z$ d! t
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
4 v/ ], \, q: T* N. j ovi 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' p/ L* F( ~8 }
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
8 x' L/ i2 ?4 z% n( e9 k8 {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3 m/ O- k9 _8 P2 r/ [5 ^
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
: }! { v7 B! _杂机构可靠性分析具有可行性和实用性..
: G$ ^; V6 `- W8 n/ G关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真8 \% \& d8 w+ z( D; a
中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A
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Flight Control.part02.rar
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发表于 2013-3-25 20:56:44