THE EFFECT OF AERODYNAMIC NON-LINEARITIES AND CROSS-COUPLINGS ON THE PERFORMANCE OF A CRUCIFORM MISSILE
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
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The effect of aerodynamic non-linearities and cross-couplings on the performance of a cruciform guided missile were studied, including the effects of such aerodynamic characteristics on stability and homing. Aerodynamic data, obtained from wind tunnel tests of the English Electric D.4 configuration used to develop THUNDERBIRD, and of W.2 V.R.725 together with control and guidance system data, were employed to construct the mathematical model. TRIDAC and Mercury computers were used. In spite of awkward aerodynamic characteristics assumed, a cruciform missile provided with a suitable feedback control system can function satisfactorily up to large body incidences 30 degrees and need not become unstable. The main difficulty is the rolling behaviour because it causes the missile to have preferred planes of incidence. Roll rate stabilization may result in considerable rolling during homing, with some increase in miss distance. A slow rate of roll, demanded continuously to smooth out the effects of fortuitous bias, also tended to increase miss distance when applied to a missile without bias. Roll position stabilization leads to mainly smaller miss distances than does roll rate stabilization in homing on targets turning off course at a steady rate.
- Operations Research
- Guided Missile Dynamics, Configurations and Control Surfaces
- Guided Missiles
- Air Navigation and Guidance