Aeroelastic stability of slender, spinning missiles

Platus, D. H.

doi:10.2514/3.20812

Cited by 55 publications

(18 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In a traditional design approach of guidance and control where the autopilot is separately designed, some researchers have considered linear aeroelastic dynamics and tried to reduce the bending vibrational effects from the feedback control signal [12,13]. The modeling approach in their work suffers from considering a linear model for aeroelasticity and ignoring the aero-dynamical coupling effects in dynamic modeling [14]. Consequently, the closed-loop system stability cannot be guaranteed in all situations using this design approach.…”

Section: Integrated Guidance and Control Of Elastic Vehicle 2609mentioning

confidence: 99%

“…In this research, only the first aeroelastic mode is considered in the design and analysis. In order to analyze the stability of a flexible body at supersonic flow, the first vibration mode can be considered [14]. Higher elastic modes have high natural frequencies and very low amplitudes and have no remarkable effect on control design and stability analysis.…”

Section: Nonlinear Elastic Flight Vehicle Modelmentioning

confidence: 99%

See 1 more Smart Citation

Integrated guidance and control of elastic flight vehicle based on robust MPC

Shamaghdari

Nikravesh

Haeri

2014

Int. J. Robust. Nonlinear Control

View full text Add to dashboard Cite

SUMMARYIntegrated guidance and control of an elastic flight vehicle based on constrained robust model predictive control is proposed. The design is based on a partial state feedback control law that minimizes a cost function within the framework of linear matrix inequalities. It is shown that the solution of the defined optimization problem stabilizes the nonlinear plant. Nonlinear kinematics and dynamics are taken into account, and internal stability of the closed-loop nonlinear system is guaranteed. The performance and effectiveness of the proposed integrated guidance and control against non-maneuvering and weaving targets are evaluated using computer simulations.

show abstract

Section: Integrated Guidance and Control Of Elastic Vehicle 2609mentioning

confidence: 99%

Section: Nonlinear Elastic Flight Vehicle Modelmentioning

confidence: 99%

Integrated guidance and control of elastic flight vehicle based on robust MPC

Shamaghdari

Nikravesh

Haeri

2014

Int. J. Robust. Nonlinear Control

View full text Add to dashboard Cite

show abstract

“…Platus [8] first applied his theory to a 5-ft-long rod stabilized by a very light 1.5-ft-long flare with a base diameter of 0.8 ft. Since he neglected the very small normal force associated with the nose, this missile has a very simple normal force distribution of The displacement oscillations of a free-free uniform beam can be described by the following sum of eigenfunctions:…”

Section: Flare-stabilized Rodmentioning

confidence: 99%

“…Recently, with the development of long-finned anti-armor projectiles and long flarestabilized reentry vehicles, the effects of aero-elasticity have become a matter of possible concern for designers. In 1992, Platus [8] developed a simple theory for elastically deforming missiles. This theory showed significant decreases in pitching frequency when the smallest bending frequency was less than four times the pitching frequency.…”

Section: Introductionmentioning

confidence: 99%

Flight Mechanics of an Elastic Symmetric Missile

Murphy

Mermagen

2001

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

The free-flight motion of an elastic missile is approximated with three bodies connected by two massless elastic cantilever beams. If the mass distribution of the three bodies is 1-2-1, the frequency of the symmetric oscillation of the outer bodies is within 5% of the classical frequency of the oscillation of a free-free beam. A second combined pitching antisymmetric flexing motion can occur with a frequency that is almost twice that of the symmetric flexing motion. As the beam stiffness is reduced, the symmetric flexing motion frequency approaches the rigid body aerodynamic zero-spin frequency, and the flight zero-spin aerodynamic frequency is considerably reduced. Moderate beam damping can cause dynamic instability for spins greater than the zero-spin aerodynamic frequency. Resonance mode amplification can occur when the spin is equal to the zero-spin aerodynamic frequency, but more importantly it can occur when the spin is equal to the two elastic flexing frequencies. Spin-yaw lock-in occurs at the lower elastic frequency.

show abstract

“…Further, the effect of servo dynamics for resonance behaviour is also considered. For this purpose, the SDE governing an EFW is derived using the modal approach that is widely used for elasticity analysis of various flying vehicles including EFWs (24,39) , missiles (40,41) , aircrafts (42) and airships (43) . In all latter studies, deflections are expanded in terms of the normal structural modes where the final governing equations are derived using the orthogonality conditions.…”

Section: Introductionmentioning

confidence: 99%

Analytical structural behaviour of elastic flapping wings under the actuator effect

2018

View full text Add to dashboard Cite

The effect of inertial forces on the Structural Dynamics (SD) behaviour of Elastic Flapping Wings (EFWs) is investigated. In this regard, an analytical modal-based SD solution of EFW undergoing a prescribed rigid body motion is initially derived. The formulated initial-value problem is solved analytically to study the EFW structural responses, and sensitivity with respect to EFWs’ key parameters. As a case study, a rectangular wing undergoing a prescribed sinusoidal motion is simulated. The analytical solution is derived for the first time and helps towards a conceptual understanding of the overall EFW's SD behaviour and its analysis required in their designs. Specifically, the EFW transient and steady response in on-off servo condition is also attended.

show abstract

Aeroelastic stability of slender, spinning missiles

Cited by 55 publications

References 3 publications

Integrated guidance and control of elastic flight vehicle based on robust MPC

Integrated guidance and control of elastic flight vehicle based on robust MPC

Flight Mechanics of an Elastic Symmetric Missile

Analytical structural behaviour of elastic flapping wings under the actuator effect

Contact Info

Product

Resources

About