Aircraft nose landing gear assembly

An aircraft nose landing gear assembly, comprising:

• two wheels being a first wheel and a second wheel, the two wheels being separated by a steering axis and each being independently rotatable about a rotation axis in a rotation direction;
• a first electromotive device associated with the first wheel, the first electromotive device being configured to selectively engage and supplement rotation of the first wheel in the rotation direction, and to selectively engage and resist rotation of the first wheel in the rotation direction;
• a second electromotive device associated with the second wheel, the second electromotive device being configured to selectively engage and supplement rotation of the second wheel in the rotation direction, and to selectively engage and resist rotation of the second wheel in the rotation direction;
• a controller arranged to, during a turning event, based on an indication to the controller of rotation of the two wheels in the rotation direction, cause the first electromotive device to engage the first wheel and supplement rotation, and the second electromotive device to engage the second wheel and resist rotation, such that said engagement of the electromotive devices causes the two wheels to pivot about the steering axis;
• wherein the aircraft comprises one or more propulsion systems separate from the nose landing gear which are arranged to propel the aircraft along the ground when taxiing and capable of causing the aircraft to taxi along flat and level ground in a manner that would maintain a speed greater than or equal to the typical taxiing speed;
• wherein each of the first and second electromotive devices is selectively and independently operable by the controller to selectively either function as a motor to supplement rotation or as a brake to resist rotation of the respective wheel of the nose landing gear.