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Based on a kind of pitch channel model of supersonic aircraft w hich is released by America air force research center, a kind of open loop testing method is proposed to testify the actuator effect of a kind of high speed aircraft. The difference between this type of aircraft and other traditional aircraft is that open loop response is unstable so it is not easy to do this kind of actuator test. So a kind of virtual flying condition is assumed to make the simulation can last for a longer time, also it can make the analysis of actuator effect to be more clear and simple. Also the physical meanings of this kind of unstable open loop response is analyzed.

The research on open loop actuator response of high speed vehicle based on constant speed and constant elasticity