| 摘要 |
PURPOSE:To reduce a bending moment applied on a fuselage by a method wherein a missile is provided with a mechanism supplementing gas to the low-pressure side of a fuselage upon flying so as to be capable of unifying a pressure distribution about the fuselage. CONSTITUTION:Two venting holes 1 are provided at the top 3 of a fuselage 11, whereat a pressure difference between the upstream side and the dlowstream side of air becomes large, while two venting holes are connected by a ventilating pipe 2. The top 3 of the fuselage 11 is also provided with 8 pieces of venting holes 1 in the peripheral direction thereof and the venting holes 1 are connected by a hoop-type ventilating pipe 2. The fuselage accommodates a gas bomb 6 and an induction computer 13 and the peripheral external pressure of the top 3 of the rocket 11 is detected by a pressure sensor 12 while a valve 5 at a part whereat the external pressure is lower is opened to discharge the gas in the gas bomb 6 to the side of the fuselage 11 whereat the pressure around the fuselage 11 is lower based on the result of comparison effected by the induction computer 13. Gas is supplemented to the side of the fuselage 11 such as the downstream side of airflow and the like whereat a pressure is lower in such a manner whereby a pressure distribution about the fuselage 11 may be unified. |
