Landing gear assembly of aircraft

A landing gear assembly of an aircraft comprising:

• a control system configured to output an amount of operation corresponding to an operated physical amount;
• a wheel;
• a landing gear supported by an aircraft frame, and configured to rotatably support the wheel;
• a plurality of detection sensors, each configured not to output a detection signal if the aircraft flies in air, and to output the detection signal if the aircraft stays on ground;
• and
• a steering system configured to steer the wheel using the amount of operation as the command value if the plurality of detection sensors output the respective detection signals, and orient rotation of the wheel in a longitudinal direction of the aircraft in disregard of the amount of operation if speed of the aircraft is higher than a first limitation speed,
• wherein the steering system is configured to orient the rotation of the wheel in the longitudinal direction of the aircraft in disregard of the amount of operation if outputs of the plurality of detection sensors are not identical and the speed of the aircraft is higher than a second limitation speed, and
• the second limitation speed is lower than the first limitation speed.

A landing gear assembly of an aircraft comprising:

• a control system configured to output an amount of operation corresponding to an operated physical amount;
• a wheel;
• a landing gear supported by an aircraft frame, and configured to rotatably support the wheel;
• a plurality of detection sensors, each configured not to output a detection signal if the aircraft flies in air, and to output the detection signal if the aircraft stays on ground;
• and
• a steering system configured to orient the rotation of the wheel in a longitudinal direction of the aircraft in disregard of the amount of operation if the plurality of detection sensors do not output the respective detection signals, and steer the wheel using the amount of operation as a command value if the plurality of detection sensors output the respective detection signals,
• wherein the steering system is configured to steer the wheel using the amount of operation as the command value if outputs of the plurality of detection sensors are not identical and speed of the aircraft is lower than a second limitation speed.