State-of-the-Art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

Moore, Frank G.

doi:10.21236/ada273680

Cited by 2 publications

(1 citation statement)

References 15 publications

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“…For the purposes of numerical experiments, a 6 degrees of freedom (6-DOF) mathematical model has been used to investigate the rocket behavior (McCoy, 2004;Zipfel, 2014;Żugaj and Głębocki, 2010). The nondimensional forces and moments aerodynamic coefficients were obtained with the aim of semi-empirical engineering methods (Moore, 1993). Next, the aero database was validated using FLUENT CFD code.…”

Section: Test Platform and Simulation Modelmentioning

confidence: 99%

Modified trajectory tracking guidance for artillery rocket

Ożóg¹,

Jacewicz²,

Głębocki³

2020

Journal of Theoretical and Applied Mechanics

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This paper contributes to a modified guidance scheme based on a trajectory tracking method which is dedicated for an artillery rocket with a finite set of single use solid propellant side thrusters. Frequency modulation of pulses was used to achieve effective firing logic. The proposed control law is applicable in the last phase of flight when the rocket reaches the vertex of the trajectory. A correction engine activation sequence was chosen in such a way that possibility of rocket axial unbalance is minimized due to motors firing. Numerical simulation results indicate that significant dispersion reduction was achieved and the number of activated side rocket thrusters is minimized.

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Section: Test Platform and Simulation Modelmentioning

confidence: 99%

Modified trajectory tracking guidance for artillery rocket

Ożóg¹,

Jacewicz²,

Głębocki³

2020

Journal of Theoretical and Applied Mechanics

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Improving Conventional Longitudinal Missile Autopilot Using Cerebellar Model Articulation Controller Neural Networks

Lin¹,

Chen

2003

Journal of Guidance, Control, and Dynamics

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A way to integrate the cerebellar model articulation controller (CMAC) neural network with the missile longitudinal conventional feedback controller (CFC) to compensate for nonlinearities, unmodeled dynamics, parameter variations, etc., is proposed. The inner loop of the CFC will essentially be left unchanged to improve the stability of the missile. The outer loop of CFC, in addition to playing its traditional role, would work with the CMAC to learn quickly to approximate the dynamic inversion from angle of attack to control de ection, to achieve better tracking in normal acceleration. In this arrangement, the well-known CFC acts as a safety net, whereas additional performance is brought about through CMAC learning. Nomenclatureaerodynamic coef cients d = reference diameter, cm I y = pitch moment of inertia, kg ¢ m 2 M m = Mach number Q = dynamic pressure, kg/(m.sec 2 / q = pitch rate, deg/s S = reference area, m 2 U = U C C U O U C = output of cerebellar model articulation controller neural network, deg U I = command generated by the inner loop of conventional feedback controller, deg U O = command generated by the outer loop of conventional feedback controller, deg V m = missile speed, m/s W = missile weight, kg ® = angle of attack, deg ± = tail-n de ection, deg µ = pitch angle, deg

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State-of-the-Art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

Cited by 2 publications

References 15 publications

Modified trajectory tracking guidance for artillery rocket

Modified trajectory tracking guidance for artillery rocket

Improving Conventional Longitudinal Missile Autopilot Using Cerebellar Model Articulation Controller Neural Networks

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