By Jan Roskam
Moment Library reproduction. San Diego Air and house Museum.
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Extra resources for Airplane Flight Dynamics and Automatic Flight Controls
The expansion will be done in three steps. s. 21) are referred to as the moments and products of inertia of the airplane. Common symbols used for these integral quantities (inertias) are as follows: Iv (y2 + i 2)Q Adv = Ixx Iv (x2 + z2)QAdv Iv (x2 Chapter 1 f XYQAdv = Ixy. 17) Forces: FA = iFA, + jF Ay + kFA, (U8a) for the aerodynamic fOrce components. By a special orientation of the XYZ coordinate system relative to the airplane these forces wjl! be showntQ be the drag. jet forces respectively.
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. Such time dependent integrals are awkward to work with. To eliminate the time-dependence a switch in coordinate systems will be made.
For such vehicles Ixz = 0 is also satisfied. 17) into its scalar component form are now available. 19) and (1:25) form six differential equations of motion with U, V, W, P, Q and R as the dependent variables .. Time is the independent variable. At this point it is not yet possible to solve these equations for the time histories of motion U(t) through R(t). s. 19) and (1~~5)} vary with time and with the dependent variables U, V, W, P, Q and R. These dependencies will be explored and defined in Chapter 3.