Su-27 Flanker by S. Skrynnikov

By S. Skrynnikov

The Su-27 seemed as a Soviet response to improvement of U. S. air superiority opponents of the overdue Seventies and proved to be enough to counteract essentially all air threats of that time period, the final years of the chilly battle.

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26) - The rotor i is assumed to have a moment of inertia IR; about its own spin axis. _ _ " ---<~ Angular momentum of airplane .. Chapter 1 with rotors fixed. 30c) ORIENTATION OF THE AIRPLANE RELATIVE TO THE EARTH FIXED COORDINATE SYSTEM X'Y'Z' .. ~ To define the orientation of an airplane relative to theeartlrfixed coordinate system X'Y'Z' it suffices to define the orientation of its body-fixed axis system XYZ. 1 shows the two axis systems without defining their interrelation. 5 show&axis system X'Y'Z' translated parallel to itself until its origin coincides with the center of mass, point P on the airplane.

3 CASE 3: EQUATIONS QF MOTlQN FOR STEADY SYl\QJETRICAL PULL-UP ',. 65) are used to study airplane controllability problems in the following conditions: * Symmetrical pull-up flight with all engines operating * Symmetrical pull-up flight with one or more engines inoperative * Ability to perform pull-up flight with certaiil failed systems Applications are disc~ssed in Chapter 4. 9 . S; V = VI + u ,. 68b) These substitutions are referred to as the 'Perturbation Substitutions'. At this stage, the magnitude of these perturbations is quite arbitrary!

By a process of elimination of variables it is also possible to think of these equations as a set of six differential equations of motion in six variables: either U, V, W, P, Q and R or U, V, W, qt, 9 and Ill. In either case, general solutions to the equations can be obtained only by numerical integration. However, from an airplane design and from a handling qualities viewpoint there are two special flight conditions for which solutions of these equations are of primary interest: 1. Steady state flight conditions 2.

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