Analysis of Relaxed Static Stability and Maneuver Load Control Applications to a Large Bomber.
Final rept. 8 Mar 71-28 Feb 72,
NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
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Application of two control configured vehicle concepts, relaxed static stability and maneuver load control, is made using a large bomber as the test configuration. The objectives are to obtain vehicle weight reduction andor performance benefits resulting from the relaxation of normal vehicle design constraints made possible by application of control techniques. In the longitudinal axis, both static stability margins and horizontal tail size reductions are examined. In the directional axis, vertical tail size reductions are assessed. Acceptability criteria are based on MIL-F-8785B flying qualities requirements and both maneuver and upset conditions. The maneuver load control study aims to reduce wing weight by reducing wing bending moment during discrete load conditions. Wing lift distribution is modified by deflection of wing mounted control devices such that the wing center of pressure moves inboard. Author