A New Approach to Aeroelastic Response, Stability and Loads of Missiles and Projectiles

Hodges, Dewey H.

doi:10.21236/ada424568

Cited by 7 publications

(4 citation statements)

References 49 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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“…An early study by Crimi [11] identified the impacts of static and dynamic aeroelastic behaviors of flexible tactical weapons using a linear beam model. In [12,13], Chae and Hodges modeled the flight dynamics of flexible missiles using a mixed-form geometrically nonlinear beam formulation, coupled with the combined viscous crossflow theory [14] and the potential flow slender-body theory [15]. They studied the flight stability of such vehicles and the impact of the thrust force on their flight stability.…”

Section: Introductionmentioning

confidence: 99%

“…The aeroelastic effect is not involved in the direct solution. Additionally, it has been shown that longitudinal forces (thrusts) may impact the bending behavior of a flexible launch vehicle [12,13,23]. This effect is not involved in the current study, but the solution approaches developed can be adapted to include multiaxial loading conditions.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Beam Solutions for Real-Time Simulation and Control Development of Flexible Rockets

Clark

Griffin

et al. 2016

57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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In this study, flexible rockets are structurally represented by linear beams. Both direct and indirect solutions of beam dynamic equations are sought to facilitate real-time simulation and control development for flexible rockets. The direct solution is obtained by numerically integrating the beam structural dynamic equation using an explicit Newmark-based scheme, which allows for stable and fast transient solutions to the dynamics of flexile rockets. Furthermore, in real-time operation, the bending strain of the beam is measured by fiber-optical sensors at discrete locations along the span, whereas both the angular velocity and translational acceleration are measured at a single point by an inertial measurement unit. Another aspect in this paper is finding the analytical and numerical solutions of the beam dynamics based on limited measurement data to facilitate the real-time control development. Numerical studies demonstrate the accuracy of these real-time solutions of the beam dynamics. Such analytical and numerical solutions, when integrated with data processing and control algorithms and mechanisms, have the potential to increase launch availability by processing flight data into the flexible launch vehicle's control system.

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“…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. Rasti and Fazelzadeh [22] investigated multibody dynamic modeling and flutter analysis of a flexible slender vehicle based on the hybrid equations of motion in terms of quasi-coordinates.…”

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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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A New Approach to Aeroelastic Response, Stability and Loads of Missiles and Projectiles

Cited by 7 publications

References 49 publications

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

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

Dynamic Beam Solutions for Real-Time Simulation and Control Development of Flexible Rockets

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

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