Cook M.'s Flight dynamic principles : a linear systems approach to PDF

By Cook M.

ISBN-10: 0750669276

ISBN-13: 9780750669276

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Additional info for Flight dynamic principles : a linear systems approach to aircraft stability and control

Sample text

The relative angular change in a perturbation is also shown in Fig. 4 where it is implied that the axes have moved with the airframe Systems of Axes and Notation 17 and the motion is viewed at some instant during the disturbance. 5) Choice of axes Having reviewed the definition of aircraft fixed axis systems an obvious question must be: when is it appropriate to use wind axes and when is it appropriate to use body axes? The answer to this question depends on the use to which the equations of motion are to be put.

When dealing with numerical data for an existing aircraft it is not always obvious which axis system has been used in the derivation of the model. 4) and the quoted values of αe and θe it should become obvious which axis system has been used. When it is necessary to make experimental measurements in an actual aircraft, or in a model, which are to be used subsequently in the equations of motion it is preferable to use a generalised body axis system. Since the measuring equipment is installed in the aircraft its location is precisely known in terms of body axis coordinates which, therefore, determines the best choice of axis system.

7 AERODYNAMIC REFERENCE CENTRES With reference to Fig. 12, the centre of pressure, cp, of an aerofoil, wing or complete aircraft is the point at which the resultant aerodynamic force F acts. It is usual to resolve the force into the lift component perpendicular to the velocity vector and the drag component parallel to the velocity vector, denoted L and D respectively in the usual way. The cp is located on the mac and thereby determines an important aerodynamic reference centre. Now simple theory establishes that the resultant aerodynamic force F generated by an aerofoil comprises two components, that due to camber Fc and that due to angle of attack Fα , both of which resolve into lift and drag forces as indicated.

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Flight dynamic principles : a linear systems approach to aircraft stability and control by Cook M.


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