In an airplane of tail-controlled aerodynamic missiles, when the control surfaces are deflected to provide an elevator angle with trailing edge upward to produce a positive normal acceleration, this creates a downward increment of force on the tail. The result is that the missile c.g. may drop momentarily during the pitch-up, so the normal acceleration may briefly become negative before it builds up positively. If the accelerometer is located at missile c.g., it will sense a negative normal acceleration and the senses a positive normal acceleration in a manner similar to non-minimum phase system. If the accelerometer is located ahead of the c.g., the normal acceleration measured will change and this depends on
the pitch acceleration about the c.g., so only a positive normal acceleration may be sensed. This paper represents the physical explanation for the non-minimum phase behavior in tailcontrolled aerodynamic missiles, its source, disadvantages and solution for this problem and finally the optimum location for accelerometer in the vehicle.