Method for missile flight simulation based on navigation sensor data and apparatus

摘要

An embodiment of the present invention relates to a synthetic flight testing method of a navigation sensor information based guided missile, comprising: a navigation output information acquisition step for acquiring navigation output information including the speed, position, and attitude of the guided missile at a first time point from a nonvolatile memory in which a guidance steering system software is stored; a driving command calculation step for calculating a position which the guided missile has to reach at a second time point and a driving command for reaching the position by applying the obtained navigation output information to a preset guidance steering algorithm; and a command transfer control step for controlling the calculated driving command to be transmitted to a driving device controlling the driving of the guided missile.