| 摘要 |
A construction intended for a carrier rocket or a satellite, comprising a first construction part ( 21 ), which is made of a composite material comprising two essentially parallel walls ( 23, 24 ) and a core ( 25 ) arranged between these walls, a second construction part ( 22 ) and means ( 26, 31; 26', 31, 39 ) for joining the first and the second construction parts ( 21, 22 ). Said means ( 26, 31; 26', 31, 39 ) comprising a first fastening element ( 26 ) provided with several threads ( 27 ), or several first fastening elements ( 26, 26 ') provided with at least one thread ( 27 ) each, said first fastening element/elements ( 26; 26 ') being arranged between the walls ( 23, 24 ) of the first construction part ( 21 ) in such a way that the threads ( 27 ) are accessible via the end surface ( 28 ) of the first construction part that faces the second construction part ( 22 ). Said first fastening element/elements ( 26; 26 ') further being so arranged that the centre axis of the respective thread ( 27 ) extends essentially in parallel with the walls ( 23, 24 ). Said means further comprising several second fastening elements ( 31 ) provided with a thread ( 33 ), which second fastening elements extend through cavities ( 30 ) in the second construction part ( 22 ) and are screwed into said first fastening element/elements ( 26; 26 ') so as to secure the two construction parts ( 21, 22 ) to each other. The invention also relates to a method for joining a first construction part ( 21 ) and a second construction part ( 22 ). |
