Methods are described for calculating aerodynamic rudder angles of missiles with four independently controllable cruciform rudders and cruciform wings in the same plane or rotated 45 deg. The calculation of the independent angles from the autopilot command angles can only be realized by adding a secondary condition. The only solution obtained by using three different calculation methods shows that the control of the independent rudders takes place following the principle of minimally induced drag, corresponding to the solution realized in practice.
Transformation of Rudder Angles for Vehicles with Cruciform Wings Zur Transformation von Ruderwinkeln bei Kreuzflueglern
1975
16 pages
Report
No indication
English
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