Abstract
To present the basic flight dynamics modeling approach applicable to aircraft, rockets, and spacecraft. To derive the equations of motion for typical flight dynamic systems. To describe the sensors used in flight control systems.
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Notes
- 1.
The time derivative relative to a rotating frame is given by the chain rule \(\vec{\dot{A}} = \frac{\partial \vec{A}} {\partial t} = \frac{\mathrm{d}\vec{A}} {\mathrm{d}t} - (\omega\times \vec{ A})\).
- 2.
The distance between any two points in a rigid body does not vary with time.
- 3.
Even when the aerodynamics is unimportant (as in space flight), the wind axes provide a convenient reference frame for the vehicle’s attitude.
- 4.
When the vehicle’s structural flexibility is taken into account, it is necessary to include the unsteady aerodynamic effects of control surface deflections, i.e., dependence of aerodynamic forces and moments on deflection rates, \(\dot{{\delta }}_{\mathrm{E}},\dot{{\delta }}_{\mathrm{A}},\dot{{\delta }}_{\mathrm{R}}\).
- 5.
Missiles rolling at a high rate can have a significant aerodynamic coupling between longitudinal and lateral aerodynamics. However, as such motions are inherently nonlinear, they are beyond our present scope.
- 6.
The wheel’s speed is maintained constant by a feedback control system called servomotor, which works by taking an angular speed feedback from a tachometer (or an incremental angle encoder) as a sensor, and applies a torque by a direct-current(DC) motor as the actuator.
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© 2011 Springer Science+Business Media, LLC
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Tewari, A. (2011). Flight Dynamic Models. In: Automatic Control of Atmospheric and Space Flight Vehicles. Control Engineering. Birkhäuser, Boston, MA. https://doi.org/10.1007/978-0-8176-4864-0_2
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DOI: https://doi.org/10.1007/978-0-8176-4864-0_2
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Publisher Name: Birkhäuser, Boston, MA
Print ISBN: 978-0-8176-4863-3
Online ISBN: 978-0-8176-4864-0
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