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By Peter W. Likins, Robert E. Roberson, Jens Wittenburg (auth.)

ISBN-10: 3211811990

ISBN-13: 9783211811993

ISBN-10: 3709129087

ISBN-13: 9783709129081

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Read or Download Dynamics of Flexible Spacecraft: Department of General Mechanics Course held in Dubrovnik, September 1971 PDF

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Extra resources for Dynamics of Flexible Spacecraft: Department of General Mechanics Course held in Dubrovnik, September 1971

Example text

D'lr s 33 +JwTCC[c+2w(a (~ +ww)c]J-1-d'lr s +M5 w:r {CC0X +C 5 C(~ + ww)R] +C\~a + wawa)R:} - jw\G- Drilr)du +jwr Dr if'dv . (42) s Eq. (42) is still not in the desired final form for -s L , because the dependence of c on y 5 has not yet been ex- plicitly accomodated (see Fig. nnation). The mass center shift -gcan be attributed in part to the shifts of the mass center locations of the finite elements during defor mation, in part to the similar mass center motions of the nodal bodies and in part to the behaviourof moving parts other than the elastic appendage under consideration.

S. Hopkins of UCLA and McDonnel-Douglas Corp. Vibration About Initial Orientation f case with A = D =0 , I 49 the advantage would appear to be with Eq. (74). Transformations superior to Eq. (74) are well known to exist when A' = G' = 0 , and particularly so when DI is a polynomial I 1 in M and K; in this last and simplest case, one can accomplish a transformation to dynamically uncoupled coordinates even at the level of second order differential equations. Specifically, if an elastic appendage is vibrating about a state of rest in inertial space, Eq.

The influence of spin on mode shapes and frequencies A qualitative appreciation of the influence of spin on structural oscillations can be gained by consideration of the simple systems illustrated in Fig. 2. lQ 3 (unit vectors b1, b2, b3 b). 1Qi + u. 2 2 + U.. 3 Q3 from its nominal I or steady-state location P relative to b • The spring identified by k2. ~ (C) Fig. 1 5. fl. were zero the location I of P would be a small distance A closer to the bearing axis of b, 2 where k2 A=mRQ. The only significant difference in systems 2a), 2b), and 2c) is in the steady-state load in the spring restraining the motion of P within the tube; in case 2a) this spring is in tension, in case 2b) it is unloaded, and in case 2c) it is in compression.

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Dynamics of Flexible Spacecraft: Department of General Mechanics Course held in Dubrovnik, September 1971 by Peter W. Likins, Robert E. Roberson, Jens Wittenburg (auth.)

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