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Download Airplane Flight Dynamics and Automatic Flight Controls by Jan Roskam PDF

By Jan Roskam

Moment Library reproduction. San Diego Air and house Museum.

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Sample text

Reminder: The integrals f. and f. 12) represent volume and surface inte- grals for the entire airplane. These integrals can be evaluated only if the external geometry of the airplane is knoWn. This is the case if the airplane is rigid. If the airplane is highly elastic then an aeroelastic equilibrium must be established before the external shape of the airplane can be determined. Methods for accomplishing this are discussed in Chapter 7. 12) implies that the volume integral (on the left hand side) is a time dependent function.

This assumption infers that the center of gravity of the airplane stays in the same place during a 60 second interval. Phenomena such as fuel sloshing, shifting payloads and wandering passengers are therefore outside the scope of the equations which follow. 1 requests that the reader remove this assumption. 1 with the help of the vectors r'. It is more convenient to use the vectors 1 and ? p. To that end the body-fixed coordinate system XYZ is introduced. The selection of the orientation of system XYZ relative to the airframe is done quite arbitrarily.

3 all contain products or cross products of perturbed motion variables. These terms are also referred to as non-linear terms. At this point the so-called small perturbation assumption will be made: the non-linear terms will be assumed to Chapter! l>lsinE>1 :r. 74c) 29 Equations of Motion and Axis Systems be negligible compared with the linear tenns. 3 will also be dropped. 76) to small perturbations only! ) this assumption is not very restrictive from a pragmatic viewpoint. Even fighter and attack ait{>lanes operate mostly under conditions where small perturbations are desired: ordnance delivery ~uracy partly depends on that!

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