A new dynamic model for aircraft motions is presented. This model can be viewed as intermediate between a point-mass model, in which the body attitude angles are control-like, and a rigid-body model, in which the body-attitude angles evolve according to Newton's Laws. Specifically, consideration is given to the case of symmetric flight, and a model is constructed in which the body roll-rate and the body pitch-rate are the controls. In terms of this body-rate model a minimum-time heading change maneuver is formulated. When the bounds on the body-rates are large the results are similar to the point-mass model in that the model can very quickly change the applied forces and produce an acceleration to turn the vehicle. With finite bounds on these rates, the forces change in a smooth way. This leads to a measurable effect of agility.
Aircraft agility maneuvers
AIAA Atmospheric Flight Mechanics Conference ; 1992 ; Hilton Head Island, SC, United States
1992-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
AIAA | 1992
|Demonstrative Maneuvers for Aircraft Agility Prediction
British Library Conference Proceedings | 2008
|Demonstrative Maneuvers for Aircraft Agility Prediction
AIAA | 2008
|Nonlinear Decoupling Control and Aircraft Agility Maneuvers
British Library Conference Proceedings | 1994
|