Flight Dynamics Modeling of Dual-Spin Guided Projectiles

This paper presents a complete nonlinear parameter-dependent mathematical model, as well as a procedure for computing the quasi-linear parameter-varying (q-LPV) model of a class of spin-stabilized canard-controlled guided projectiles. The proposed projectile concept possesses a so-called dual-spin c...

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Vydáno v:IEEE transactions on aerospace and electronic systems Ročník 53; číslo 4; s. 1625 - 1641
Hlavní autoři: Seve, Florian, Theodoulis, Spilios, Wernert, Philippe, Zasadzinski, Michel, Boutayeb, Mohamed
Médium: Journal Article
Jazyk:angličtina
Vydáno: New York IEEE 01.08.2017
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Institute of Electrical and Electronics Engineers
Témata:
Aerodynamic coefficients
Aerodynamics
Atmospheric modeling
Automatic
Axes (reference lines)
Computational modeling
Dynamical systems
Engineering Sciences
Flight mechanics
guided projectiles
Mathematical model
Nonlinear dynamical systems
Nonlinear dynamics
Nose
Pitch (inclination)
Position sensing
Projectiles
quasi-linear parameter-varying (q-LPV) systems
Rolling motion
Stability analysis
uncertain systems
Weapons
Yaw
guided projectiles
uncertain systems
Flight mechanics
nonlinear dynamical systems
quasi-linear parameter-varying (q-LPV) systems
ISSN:0018-9251, 1557-9603
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Popis
Shrnutí:This paper presents a complete nonlinear parameter-dependent mathematical model, as well as a procedure for computing the quasi-linear parameter-varying (q-LPV) model of a class of spin-stabilized canard-controlled guided projectiles. The proposed projectile concept possesses a so-called dual-spin configuration: the forward section contains the necessary control and guidance software and hardware, whereas the aft roll-decoupled and rapidly spinning section contains the payload. Wind-axes instead of body-axes variables, as is the case in the existing literature, are preferred for the modeling of the highly coupled pitch/yaw airframe nonlinear dynamics, since they are better suited to control synthesis. A q-LPV model, approximating these nonlinear dynamics around the system equilibrium manifold and capturing their dependence on diverse varying flight parameters, is analytically obtained. In addition, a detailed stability analysis specific to this kind of weapons is performed throughout their large flight envelope using the aforementioned q-LPV model. Furthermore, a study is conducted in order to quantify the influence of reducing the dimension of the flight parameter vector on the exactness of the q-LPV model. Finally, the critical influence on the pitch/yaw-dynamics of the nose-embedded sensor position, and of uncertainty on the various static and dynamic aerodynamic coefficients as well as the aerodynamic angles, is shown.
Bibliografie:ObjectType-Article-1
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content type line 14
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2017.2667820