By John H Blacelock
This can be on no account my favourite publication on dynamics or keep an eye on, yet each person references it, so that you should still most likely have a replica of it if you are a significant aeronautics suggestions and keep an eye on specialist.
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Extra info for Automatic Control of Aircraft and Missiles
1-124 and Figure 1-10 indicates that the numerator quadratic effectively cancels the phugoid quadratic, thus substantiating the earlier statement that the phugoid oscillation takes place at almost constant angle of attack. Figure 1-11 shows that a considerable variation in (J occurs at both the phugoid and short-period frequencies. These observations lead to the following approximations of the phugoid and short-period oscillations: Short-Period Approximation. As mentioned earlier, the short-period oscillation occurs at almost constant forwarc:i speed; therefore, let 'u = 0 in the equations of motion.
The mass of the aircraft is constant. 3. The aircraft is a rigid body. ~ 4. The earth is an inertial reference. 5. The perturbations from equilibrium are small. [6. The flow is quasisteady (to be explained in Section 1-7). These equations require that the X axis be aligned with the aircraft velocity vector while the aircraft is in equilibrium flight. The stability derivatives are defined in Table I-land are derived in Section 1-7. d t 26 LONGITUDINAL DYNAMICS It should be remembered that in these equations U = Uo, q = tpuo2 , 'u=ujUo, 'a=wjUo, and 'a=wjUo.
Own elevator (stick forward) is defined as "positive elevator" by NACA convention. Thus a positive elevator deflection produces a negative 8, which means that the transfer function for elevator deflection input to 8 output is negative. For this reason some references reverse the elevator sign convention; however, that is not done in this book. Taking the Laplace transform of Eq. 710ae (s) (1-113) where ae is the elevator deflection in radians. The transfer function for input to 'u output using determinants is (see Appendix E for method).