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).
