By John H Blacelock
This can be on no account my favourite booklet on dynamics or keep an eye on, yet each person references it, so that you may still most likely have a replica of it in case you are a major aeronautics advice and regulate specialist.
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Extra resources for Automatic Control of Aircraft and Missiles
The X and Z axes lie in the plane of symmetry and the origin of the axis system is at the center of gravity of the aircraft. 2. 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.
The dimensions of 2U / c and 1/ Ii are 1/sec and sec, respectively; therefore this portion of the 'Ii term is nondimensional and can be replaced by a nondimensional coefficient. The remaining portion of the 'Ii term, which is (c/2U)'Ii, is also nondimensional. The remaining terms are handled in a similar manner. These nondimensional coefficients are referred to as "stability derivatives," and although there are several forms of these coefficients, the ones used in this text and listed in Table 1-1 are essentially the NACA standard longitudinal stability derivatives.
If the vertical velocity of the aircraft is changed, the angle of attack changes; thus the downwash varies with w. Therefore, it is necessary to investigate the effect of a change of w, the vertical velocity, on the angle of attack of the tail. Referring to Figure 1-3, it can be seen that w 4a""'- for U Wo=O (1-61) If it is assumed that w is still changing, (1-62) where w1 is the value of w at t 1, w2 is the value of w at t 2, a~ 4t = t2 - t 1• As the aircraft is moving at a finite velocity through the air mass it takes a finite time for the effect of this change in w to reach the tail.