tail end of the rocket 11 after leaving the launch canister are not readily available for conversion to rudders or control surfaces for trajectory control since in order to do so it would be necessary to intervene in the rocket structure in the region in which the fins are mounted and it would consequently also be necessary to intervene in the function of the rocket motor 12 therefore the region which can be subjected to a high mechanical loading behind the front main bulkhead 23 in the ogive or nose cone of the rocket 11 is selected for mounting the control system whereby the control rudders or control surfaces 25 are in the form of canard members the control rudders 25 engage with shaft portions 26 thereof into the nose cone casing 27 radially oriented with respect to the longitudinal axis 28 of the rocket and are respectively mounted at that location in front of a control transmission arrangement 29 on a respective pin 30 the latter of which is supported by the tubular internal structure 31 in the region of the warhead of the rocket 11 in the interest of obtaining a good control performance and high dynamics the arrangement provides for the control system 17 four control surfaces 25 which can be actuated independently of each other and which are disposed orthogonally relative to each other and thereby four servo drives 32 which are mounted between the control transmission arrangements 29 and an additionally installed intermediate bulkhead 33 on the tubular internal structure 31 ahead of the electronic section that.