| 摘要 |
The launching device has a first launching container (11) which can be mounted on the aircraft and has a plurality of launching tubes (17) in which rockets (14) are accommodated. The front end of the first launching container (11) is closed by an aerodynamic cap (16). Mounted on the first launching container (11) is a second launching container (12) which is closely joined to the first launching container and, with said first launching container, forms an aerodynamically favourable circumferential surface. The assembly consisting of the two launching containers is closed at the front end by an aerodynamic outer cap (13). After the rockets (15) have been fired from the second launching container (12), said container can be ejected, so that the drag of the aircraft is reduced, while the first launching container (11) is still on the aircraft. <IMAGE>
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