PURPOSE: To obtain the ideal acceleration of a body, which is nearer to an acceleration command from a navigation operating unit, by a method wherein a temperature sensor is provided near the wing of a missile and the distribution of a steering angle in accordance with the flow of air near the wing is effected based on the temperature information of the temperature sensor.

CONSTITUTION: An acceleration command 1 from a navigation operating unit is producted by first to fourth gains 2-5 at first. Next, a value, producted by the fourth gain 5, is inputted into a steering angle mixing 6 to obtain a steering angle command 7 for respective wings. Subsequently, respective rudders are steered by a steering device 8 based on the steering angle command 7. Thereafter, the attitude and the position of a fuselage 9, which are changed in accordance with the steering, are detected by a rate gyro 12 and an accelerometer 13 while the detected values are fed back to a flight control system. In this case, a temperature information 11 of the temperature sensor 10, provided near the wing, is also inputted into the steering angle mixing 6. Then, the distributing amount of steering angle for the wings, which is deteriorated, is reduced to obtain the necessary acceleration of the fuselage 9.