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019-液体火箭增压输送系统多学科动力学研究
j7 h9 f: G8 [5 a5 r020-直接驱动阀的阀芯摩擦力自适应补偿研究0 r; t, G3 j5 I7 i# y; F4 s
直接驱动阀的阀芯摩擦力自适应补偿研究
7 z( E; t8 S) Q9 p5 P夏立群, 牛世勇
$ g7 {5 K( O' |+ R: ]" ^+ ]( }（西北工业大学 自动化学院，陕西 西安 710062）
( f' _# P5 K- c8 D0 I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
9 }: I% d/ ~$ ?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4 f5 L$ k% b2 K+ I
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) g" j$ a" V7 A1 @, b9 v- ^3 K
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。' J% x- G) }3 ?$ ~6 j* L' n
关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
4 [9 V% F; a( {7 Q中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
8 L( g W4 {6 j6 ]) k' [Research of Adaptive Friction Compensation for Direct Drive Valve2 D F, v9 e5 q; B
XIA Li-qun, NIU Shi-yong1 T1 f) \$ K( I
（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)
. ~# O5 T# P0 L" @, G: P. }Abstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several4 p0 I+ q& k5 j
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an2 ~$ C* H1 W! V5 |0 i
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation
% m" Z! J. z- u7 G2 |. n ?models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The
! c2 R$ f9 @. D# V' Uresults show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
, P( b% P2 O' v* Inonlinearity due to friction.
0 v. K9 V% K6 KKey words: friction compensation; direct drive valve; LuGre model; adaptive control7 P' Y% F8 y- d& }
032-仿真技术在飞机起落架可靠性分析中的应用研究
0 K, {, q& k1 Y5 o. W, K" A仿真技术在飞机起落架可靠性分析中的应用研究
$ O9 T# u% j) Q( {1 \- M赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..& g6 L( E$ {4 q! G1 m0 A
(1.西北工业大学航空学院, 西安7 100 72 )( l0 j2 B& ^% z6 |
(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 ..
: O3 g2 ]6 Q1 Z# S* {: X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
) A0 i0 N1 K. k1 n3 t4 c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- Q' d' m' O5 d' N% }
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
/ U; a- m) Q# I# }- m5 G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
; k p5 s- z! _8 k7 S. T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 z+ U# T" x. {4 F0 h7 |7 Z) s
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
5 e9 Q2 `: H* }1 u! {杂机构可靠性分析具有可行性和实用性..
; R2 P1 |7 c; v3 \关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真* L( i# h; v0 v
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