By Richard L. Bielawa
Drawing on his vast adventure as a training engineer, fashion designer, educator, and researcher in rotorcraft, the writer offers a accomplished account of the basic suggestions of structural dynamics and aeroelasticity for traditional rotary wing airplane, in addition to for the newly rising tilt-rotor and tilt-wing suggestions. meant to be used in graduate-level classes and by means of practising engineers, the amount covers all the vital themes wanted for the total figuring out of rotorcraft structural dynamics and aeroelasticity, together with easy research instruments, rotating beams, gyroscopic phenomena, force procedure dynamics, fuselage vibrations, tools for controlling vibrations, dynamic attempt approaches, balance research, mechanical and aeromechanical instabilities of rotors and rotor-pylon assemblies, unsteady aerodynamics and flutter of rotors, and version checking out. The textual content is extra better by means of the inclusion of difficulties in every one bankruptcy.
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Additional info for Rotary Wing Structural Dynamics and Aeroelasticity
T h e arbitrary constants Aj, Β ι, C , and D can be e v a l u a t e d a c c o r d i n g to the appropriate root b o u n d a r y condition. 39c) l l w h e r e m e t h o d s for d e t e r m i n i n g the nonrotating natural frequencies c o are p r e s e n t e d in the s u c c e e d i n g s e c t i o n s . A l t h o u g h closed forms for the m o d a l integrals defined in E q . ( 3 . 3 2 ) are not directly a v a i l a b l e , explicit definitions of the i n t e g r a n d s are thus available from E q s .
Blades that have no pitch, twist, or p r e c o n i n g . Such simplified blade configurations p r o d u c e what w e will refer to as uncoupled mode characteristics. T h e u n c o u p l e d modal responses are characterized as h a v i n g , for any one m o d e , cui of the motion in either the i n - p l a n e , out-of-plane, or torsional degrees of freedom. In reality, rotor blades d o h a v e all of these c o m p l i c a t i n g characteristics (pitch, twist, and p r e c o n e ) , and material is therefore presented explaining h o w the basic u n c o u p l e d characteristics for the simplified blade are modified or " c o u p l e d " by these additional c o n s i d e r a t i o n s .
7 . H o w e v e r , the veracity of the orthogonality principle is not limited to this simple p r o b l e m , but can easily be generalized to other m o r e c o m p l i c a t e d , but linear, d y n a m i c s y s t e m s . / = 1 // ω; Σ 2 // ιη,-xy''x'r = Σ // Σ / = ! / = ! 82b) 24 ROTARY WING STRUCTURAL DYNAMICS Since for conservative s y s t e m s , Κ· = K the sums on the right-hand sides of these t w o equations are e q u a l . 83) 0 S i n c e , for/? Φ r , the first term is clearly n o n z e r o , the second term must be zero.
Rotary Wing Structural Dynamics and Aeroelasticity by Richard L. Bielawa