| This paper introduced six different methods which are given by MIL-STD-1797 offers for evaluating short-term pitch response. According to these methods, Flying qualities for aircraft short-term response are calculated and analyzed by equivalent system. The results indicate that there are both regions of agreement and regions of conflict in these methods. Sequential Quadratic Programming is used to solve the pilot modelin the Neal-Smith criterion. And then, the criteria of ωspTθ2,ζsp,τθ aremapped to Neal-Smith criteria for short-term pitch to determine regions of agreement and regions of conflict. In order to provide better selections for the parameters of flying qualities on the design of a new aircraft, an experiment and a test- fly, the effects and the varying trends of the parameters are analyzed and evaluated. Finally, Based on the definition of moderate amplitude roll attitude quickness criteria for fighter aircraft, The roll attitude quickness is calculated by Euler method for 19 types aircraft configurations in the paper. The results of the simulation calculation are compared with the pilots simulation experiment on aggressive maneuvering in roll, The conclusions are obtained that roll attitude quickness is closely related to the flying qualities, such as the roll-mode constant, the roll control sensitivity, aileron control effectiveness and control system augment etc. Requirements for moderate amplitude maneuvering roll attitude changes are not completely involved in MIL-STD-1797A. |
