Aeronautics Astronautics

Aircraft Dynamic Stability and Response by A. W. Babister (Auth.)

By A. W. Babister (Auth.)

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Fig. 5 Forces acting in steady SEPARABILITY OF LONGITUDINAL AND LATERAL flight MOTION From E q s . 7) to ( 2 . 36) to ( 2 . 4 4 ) , we see that the equations of motion for small disturbances can be split up into two groups. 47) = M(t) q = 0 . 48) These equations involve only symmetric disturbances (u the increment in the velocity of 0 along Ox, w the increment in the velocity of 0 along Oz, 0 the angle of pitch, and their derivatives with respect to t ) . 52) . 53) These equations involve only asymmetric disturbances (V the velocity of sideslip, cj) the angle of bank, ij; the angle of yaw, and their derivatives with respect to t).

From the above discussion it is seen that there are contributions to N v from various parts of the aircraft, the contributions often being of opposite sign. For this reason it is preferable to measure Ny experimentally early on in the design stage of an aircraft. Side force derivative due to sideslip Y v= Y /{p V S v ee This is the only side force derivative of importance for a conventional aircraft. The main contribution to Y usually arises from the vertical surfaces of the airv craft, especially from the fuselage and fin.

In radians) from the trimmed position. The corresponding aero-normalised non-dimensional derivatives are defined by 2 73 *n = \l\» VeS e Z n = Z /Jp K M n = M /^p 7 n n 2 e e2S . 74) e eS e . 75) NON-DIMENSIONAL AERODYNAMIC DERIVATIVES o o o o o o o (LATERAL) o o The aerodynamic derivatives Y , Yp, Y , L , Lp, L , N , Np, N occur in the equations v r v r v r of lateral asymmetric motion. 78) p= Ypl\p V Sb (this being the datum reference length in lateral stability analysis). 80) . 83) due to rate of yaw, N = N l\p V Sb .

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