Air to air active refuelling system for a tanker aircraft, the system comprising: - a hose suitable for driving fuel inside, - a coupling arranged at a hose-end (4.1) of the hose and comprising a drogue, the drogue being configured to be coupled to a probe of a receiver aircraft in a refuelling operation, - a hose-end control unit "HCU" located at the hose-end (4.1), the HCU comprising • at least three grid fins, each grid fin located on a fin shaft, whose axis intersects a longitudinal axis along which the HCU is arranged, these grid fins being configured to be folded or deployed when the system requires, so that when these grid fins are in a deployed state: ∘ the plurality of grid fins is further configured to rotate with respect to the longitudinal axis, and ∘ each grid fin adapts their deflection angle (α) by means of the independently rotation of each grid fin around its respective fin shaft; • an inertial measurement unit "IMU" configured to measure the acceleration of the hose-end (4.1); - first sensing means configured to measure the relative position between the first sensing means location and the probe of the receiver aircraft; and - a processing unit connected to the HCU, the IMU and the first sensing means, this processing unit being configured to process the measurements from the IMU and the first sensing means; wherein the HCU of the system, based on the measurements from the IMU and the first sensing means, actuates the deflection angle (α) in each grid fin independently and the rotation of the at least three grid fins in order to provide aerodynamic radial loads at the hose-end (4.1). - a hose suitable for driving fuel inside, - a coupling arranged at a hose-end (4.1) of the hose and comprising a drogue, the drogue being configured to be coupled to a probe of a receiver aircraft in a refuelling operation, - a hose-end control unit "HCU" located at the hose-end (4.1), the HCU comprising • at least three grid fins, each grid fin located on a fin shaft, whose axis intersects a longitudinal axis along which the HCU is arranged, these grid fins being configured to be folded or deployed when the system requires, so that when these grid fins are in a deployed state: ∘ the plurality of grid fins is further configured to rotate with respect to the longitudinal axis, and ∘ each grid fin adapts their deflection angle (α) by means of the independently rotation of each grid fin around its respective fin shaft; • an inertial measurement unit "IMU" configured to measure the acceleration of the hose-end (4.1); • at least three grid fins, each grid fin located on a fin shaft, whose axis intersects a longitudinal axis along which the HCU is arranged, these grid fins being configured to be folded or deployed when the system requires, so that when these grid fins are in a deployed state: ∘ the plurality of grid fins is further configured to rotate with respect to the longitudinal axis, and ∘ each grid fin adapts their deflection angle (α) by means of the independently rotation of each grid fin around its respective fin shaft; ∘ the plurality of grid fins is further configured to rotate with respect to the longitudinal axis, and ∘ each grid fin adapts their deflection angle (α) by means of the independently rotation of each grid fin around its respective fin shaft; • an inertial measurement unit "IMU" configured to measure the acceleration of the hose-end (4.1); - first sensing means configured to measure the relative position between the first sensing means location and the probe of the receiver aircraft; and - a processing unit connected to the HCU, the IMU and the first sensing means, this processing unit being configured to process the measurements from the IMU and the first sensing means;