Structural stability of slender aerospace vehicles: Part I

Trikha, Manish; Mahapatra, D. Roy; Gopalakrishnan, S.; Pandiyan, R.

doi:10.1016/j.ijmecsci.2010.03.011

Cited by 6 publications

(2 citation statements)

References 46 publications

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“…The divergence and flutter of a spinning beam with a concentrated mass and subjected to a pulsating thrust has been investigated by Yoon and Kim [8], 2 of 13 where they modeled the beam as a Timoshenko formulation and solved by applying a finite element method. More recently, slender rocket studies have included aerodynamic forces, gravitational forces, and internal load effects [9][10][11][12]. However, research into this area is found to be limited, with very few sustained investigations being undertaken.…”

Section: Introductionmentioning

confidence: 99%

Effect of Thrust on the Structural Vibrations of a Nonuniform Slender Rocket

Adair

Nagimova

Jaeger

2020

MCA

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The vibration characteristics of a nonuniform, flexible and free-flying slender rocket experiencing constant thrust is investigated. The rocket is idealized as a classic nonuniform beam with a constant one-dimensional follower force and with free-free boundary conditions. The equations of motion are derived by applying the extended Hamilton’s principle for non-conservative systems. Natural frequencies and associated mode shapes of the rocket are determined using the relatively efficient and accurate Adomian modified decomposition method (AMDM) with the solutions obtained by solving a set of algebraic equations with only three unknown parameters. The method can easily be extended to obtain approximate solutions to vibration problems for any type of nonuniform beam.

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Section: Introductionmentioning

confidence: 99%

Effect of Thrust on the Structural Vibrations of a Nonuniform Slender Rocket

Adair

Nagimova

Jaeger

2020

MCA

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“…They discussed the transverse vibration, dynamic stability and flutter characteristics of a flexible missile with constant thrust. Trikha et al [19,20] used two methods to deduce the equations of motion of nonspinning slender aerospace vehicles and analyzed the effect of follower thrust on structure stability. Hodges [21] discussed several issues within one framework, in which the structural part is based on a mixed variational formulation which is geometrically-exact and based on finite elements and aerodynamic theories which vary according to the flight regime and missile geometry, and investigated the effects of follower forces on aeroelastic stability of flexible missiles.…”

mentioning

confidence: 99%

Dynamic modeling and stability analysis of a flexible spinning missile under thrust

Rong

Xiang

et al. 2016

International Journal of Mechanical Sciences

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The general equations of motion of a flexible spinning missile under thrust in the powered flight phase are established and the stability of the motion of the missile is analyzed. The spinning missile is approximated to the unconstrained flexible rotor. Moreover, the thrust in the powered flight phase is deemed as a follower load when the factors of gyroscopic effect, aeroelastic effect, and axial force are considered under the mean axis condition. The equations of motion and stability of the flexible spinning missile in the powered flight phase are then deduced. The stability and dynamic response of the flexible spinning missile under thrust is analyzed through numerical calculation. Calculation results show that thrust, spinning speed, and dynamic pressure exert different influences on the stability of the spinning missile. These factors should be considered and analyzed comprehensively.

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