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019-液体火箭增压输送系统多学科动力学研究% X6 S/ ]% ?/ k* c
020-直接驱动阀的阀芯摩擦力自适应补偿研究
0 _6 V; |9 x/ L直接驱动阀的阀芯摩擦力自适应补偿研究
( `4 ]" Q5 [/ q" s夏立群, 牛世勇, v/ [/ n/ h4 q
（西北工业大学 自动化学院，陕西 西安 710062）
% Q7 n7 {# h* m$ g2 C- p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 F2 M- `( [3 t; U9 r
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 ]: ]5 H' c( o! q
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
5 k9 X: C5 R9 C. ^! _& B" p! O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。
2 A! m, `2 Q( R- @ J( K3 h: c关键词：摩擦力补偿；直接驱动阀；LuGre 模型；自适应控制
) I& ]7 Z1 O" g5 f0 Q7 d: i& R中图分类号：TP273.21 文献标识码：A 文章编号：1004-731X (2008) 12-3327-03
w4 H4 n; _% j( o3 x$ WResearch of Adaptive Friction Compensation for Direct Drive Valve
d& r+ k; A6 q G% XXIA Li-qun, NIU Shi-yong
U* U/ s. o% n S7 m7 v（Department of Automatic Control; Northwestern Polytechnical University, Xi′an 710062, China)5 u4 {( q* f6 D, {# L' T1 B
Abstract: An adaptive friction compensation scheme for direct drive valve was proposed based on LuGre model. Several3 A& y! e8 C" P, e
model of friction was described, especially LuGre z model. The dynamic model of direct drive valve (DDV) was built, and an0 s" I6 Q0 [3 E: H
adaptive friction compensation controller was designed. In order to verify the performance of adaptive controller, simulation! m+ ^9 G1 m* k- }$ ^
models based on SIMULINK and AMESIM were built, and co-simulation of SIMULINK and AMESIM was carried out. The% q) q4 d4 z8 {, ~/ o
results show that the adaptive controller improves a lot of DDV dynamic performance, which is influenced by hard
+ b4 u: U6 J+ y& B, v3 {- ?. k0 s nnonlinearity due to friction.$ h3 z+ V* Y4 K2 x7 l" m f
Key words: friction compensation; direct drive valve; LuGre model; adaptive control
0 z1 D9 u0 Z4 v) O2 u032-仿真技术在飞机起落架可靠性分析中的应用研究' O4 h& g4 d$ J4 H6 K0 [3 z t
仿真技术在飞机起落架可靠性分析中的应用研究* H! N' C6 K) p2 u' g/ q
赵世春.. ,2:喻天翔.. , 王慧.. , 宋笔锋..
. C$ @2 m# y5 i5 ^! k* l0 s+ U(1.西北工业大学航空学院, 西安7 100 72 )
8 J8 c# v1 v. ? [/ Q# ?3 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 ..2 R/ i* m) d, a5 k7 \
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# j& e" L# j+ t1 E7 q g$ D
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
& ^0 R; ^) |+ H0 H9 x7 t: ~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9 ?( R0 v8 Y; ?& s8 F& b. h
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
* A; V6 |1 v7 |0 R+ i0 V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( x9 W7 X* Q: O2 D% F+ {! _9 B
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
3 _* }* F. \" Z, w4 _/ F杂机构可靠性分析具有可行性和实用性..
5 f* H& q$ W8 v1 q- q关键词: 起落架仿真;可靠性分析;混合仿真;落震仿真
7 f$ {( ?. g. F, |4 B中图分类号: T B ll4 . 3 ; V 21 5 .7 文献标识码: A& q8 ^0 j8 e, d5 x8 h7 Z, H
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9 C$ e4 s/ E6 y+ G# r, ifa 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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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.' V( o, \$ E* i# s6 j$ E
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
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Flight Control.part02.rar
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发表于 2013-3-25 20:56:44