Aeroelastic stability of a slender missile with constant thrust

The transverse vibration, dynamic stability and flutter characteristics of a flexible missile with constant thrust are discussed. In the vibration analysis, the missile body is idealized as an un-uniform beam and the end rocket thrust is considered as constant force. The rudder is connected to the body, using the dynamic sub-structure method. Following the establishment of mathematic model based on the extended Hamilton's principle, the finite element method is introduced in the simulation of model for dynamic analysis. The first order piston theory is used in the calculation of supersonic unsteady aerodynamics. Then the flutter characteristics of flexible missile are analyzed. The results indicate that the transverse vibration characteristics of missile can be influenced in consideration of the constant thrust, which results in the dynamic instability and reduction of critical flutter speed.