DYSCO - An executive control system for dynamic analysis of synthesized structures
A. BERMAN · 24th Structures, Structural Dynamics and Materials Conference · 1983
u l e s o f a p a r t i c u l a r o r f o r c e techno logy module i s c a r r i e d o u t t h rough a s p e c i f i c named common b l o c k ( i .e., COMMON/C---/) as implemented i n FORTRAN. C e r t a i n o t h e r l i m i t e d p h y s i c a l i n f o r ma t i on wh ich must be shared between techno logy modu l e s i s c a r r i e d o u t w i t h i n s p e c i a l common b l o c k s , such as f o r c o n t r o l i n p u t s . System C h a r a c t e r i s t i c s The DYSCO ECS i s a u s e r f r i e n d l y system w i t h c o n s i d e r a t i o n f o r t h e i n t e r a c t i v e u s e r b e i n g a m a j o r d e s i g n f a c t o r . T h i s p h i l o s o p h y i s e x h i b i t e d by p r o v i d i n g adequate prompt i n f o r m a t i o n , v a l i d a t i n g u s e r i n p u t as r e c e i v e d , p r o v i d i n g a p a t h back t o a h i g h e r prompt l e v e l as a p p r o p r i a t e , p r o t e c t i n g a g a i n s t a c c i d e n t a l f i l e d e s t r u c t i o n , and p r o v i d i n g au toma t i c t u t o r i a l i n f o r m a t i o n as a p p r o p r i a t e . The system can be used as a r e p o s i t o r y f o r c u r r e n t and f u t u r e dynamic a n a l y s i s me thodo log ies . A b road spect rum o f s i m p l e and complex problems can be suppo r ted by t h e b a s i c mode l i ng s c e n a r i o . The t e c h n i c a l c a p a b i l i t i e s can be p r o g r e s s i v e l y expanded by a d d i t i o n s t o t h e Techno logy Module L i b r a r y t h rough w e l l d e f i n e d s o f t w a r e development and i n s t a l l a t i o n procedures . Techn i ca l C h a r a c t e r i s t i c s The c h a r a c t e r i s t i c s o f t h e DYSCO program a r e b r i e f l y d e s c r i b e d f r o m t h e v iew of a t e c h n i c a l use r . The t h e o r e t i c a l b a s i s has been p r e v i o u s l y d e s c r i b e d i n Ref. 9. A and a component a r e s e t s o f second o r d e r o r d i n a r y d i f f e r e n t i a l equa t i ons . The c o e f f i c i e n t s o f each may be a r b i t r a r y ( b u t computable) f u n c t i o n s o f t h e independent v a r i a b l e and t h e s t a t e v e c t o r . Each may have a s s o c i a t e d o p t i o n a l f o r c e 1 ' a1 go r i t hn l s f o r comput ing t h e g e n e r a l i z e d f o r c e s . Degree o f f reedom names a r e e i t h e r a u t o m a t i c a l l y formed i n a s tanda rd f o r m a t o r t h e y may be s u p p l i e d by t h e u s e r depend ing on t h e f o r m u l a t i o n o f t h e t echno logy module. The components a r e a u t o m a t i c a l l y coup led i n t o a model e i t h e r by r e c o g n i t i o n o f l i k e degree o f f reedom names o r by genera ted o r s u p p l i e d l i n e a r c o n s t r a i n t r e l a t i o n s . Each t echno logy module may r e p r e s e n t a s i m p l e f i n i t e e such as a r o d c r p l a t e o r a m a j o r such as an a i r c r a f t f u s e l a g e . The degrees o f freedom may r e p r e s e n t p h y s i c a l d i sp lacemen ts o r g e n e r a l i z e d mcdal d i sp lacemen ts . Each i s rep resen ted as an independent e n t i t y , t h e o n l y requ i remen t b e i n g t h a t necessary i n t e r f a c e c o o r d i n a t e s be i n c l u d e d as degrees o f f reedom. Components a r e genera l l y imp1 emented so t h a t a l l degrees o f f reedom a r e a r b i t r a r y . Each a v a T l a b l e i n t h e t echno logy l i b r a r y may be used more t h a n once i n a model. Each when used i n 2 model must re fe rence a p a r t i c u l a r s e t o f a s s o c i a t e d d a t a (DSIDM) f r o m t h e u s e r d a t a f i l e s , must be ass igned a un ique s t r u c t u r e number and o p t i o n a l l y r e f e r e n c e a p a r t i c u l a r f o r c e module and i t s a s s o c i a t e d d a t a s e t . Techn i ca l C a p a b i l i t i e s T y p i c a l o f t h e techno1 ogy modules p r e s e n t l y implemented i n DYSCO a r e : CRR2 H e l i c o p t e r r o t o r , b l a d e and hub degrees o f freedom; CFM2 Fuselage w i t h r i g i d body and e l a s t i c modes ; CSFl F i n i t e e lement M,C,K,F model; CESl N o n l i n e a r s p r i n g ; CLCl L i n e a r c o n s t r a i n t s s u p p l i e d by user ; FSSl S i n u s o i d a l shaker FRA0, FRAZ, FFC2 Ro to r dynamics ; STH3 Time h i s t o r y s o l u STRZ H e l i c o p t e r t r i m ; SEA3, SEA4 E igenana l ys and