FLAP ADJUSTING SYSTEM OF AN AIRCRAFT WITH A REGULATING FLAP

摘要

The invention pertains to a flap adjusting system of an aircraft that features: - at least one regulating flap (A1, A2; B1, B2) that is respectively mounted on one of the airfoils of an aircraft by means of at least two bearing devices (LS) and movable relative to the airfoil, - at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) for adjusting the regulating flap (A1, A2; B1, B2), wherein each adjusting device features: an actuator (20; 120) and adjusting kinematics (VK) for kinematically coupling the actuator (20; 120) to the regulating flap (A1, A2; B1, B2) with a drive rod (30, 130) that couples the actuator to the regulating flap (A1, A2; B1, B2) by means of a first and a second joint (31, 32; 131, 132), as well as a load sensor (S-K), wherein the adjusting kinematics (VK) are realized in such a way that, at a maximum adjustment travel of the regulating flap (A1, A2; B1, B2; K), the second joint (32; 132) between the drive rod (30; 130) and the regulating flap (A1, A2; B1, B2) is adjusted by an angle that amounts to less than 50% of the angle, by which the first joint (31; 131 ) is adjusted, and wherein the load sensor (S-K) is arranged in at least one of the at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) that is respectively arranged on a regulating flap (A1, A2; B1, B2; K) and in the second joint (32; 132), by means of which the drive rod is coupled to the regulating flap (A1, A2; B1, B2; K), wherein the load sensor (S-K) is realized in such a way that it measures the forces occurring in this load path.