Aircraft steering angle warning system
First Claim
1. A steering angle warning system comprising a rotation-measuring unit completely located on an aircraft, the rotation-measuring unit being arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage, and an alarm unit arranged to generate an alarm, for the purpose of preventing damage to the nose landing gear, the alarm being generated in dependence on the first signal, when the steering angle is greater than a predetermined value, wherein the predetermined value is close or equal to an angle beyond which there is significant risk of damage occurring to the nose landing gear.
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Accused Products
Abstract
A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres.
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Citations
30 Claims
- 1. A steering angle warning system comprising a rotation-measuring unit completely located on an aircraft, the rotation-measuring unit being arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage, and an alarm unit arranged to generate an alarm, for the purpose of preventing damage to the nose landing gear, the alarm being generated in dependence on the first signal, when the steering angle is greater than a predetermined value, wherein the predetermined value is close or equal to an angle beyond which there is significant risk of damage occurring to the nose landing gear.
- 13. An aircraft comprising a nose landing gear and an aircraft steering system comprising a rotation-measuring unit, the rotation-measuring unit being arranged to output, during use, a first signal, dependent on the steering angle to an interface, the interface being so arranged to enable an alarm unit to receive from the interface a signal that enables the alarm unit, when so arranged, to generate during use an alarm for the purpose of preventing damage to the nose landing gear when the steering angle is greater than a predetermined value, wherein the predetermined value is close or equal to an angle beyond which there is significant risk of damage occurring to the nose landing gear.
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21. A method of warning against excessive steering angle on an aircraft, the method comprising the steps of:
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(i) outputting, from a rotation-measuring unit located on the aircraft, a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage, (ii) determining, in dependence on the first signal, whether the steering angle is greater than a predetermined value which is close or equal to an angle beyond which there is significant risk or damage occurring to the nose landing gear, and if the steering angle is greater than the predetermined value, iii) generating an alarm for the purpose of preventing damage to the nose landing. - View Dependent Claims (22, 23, 24)
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25. In a towing vehicle for towing an aircraft by engaging a nose landing gear, the improvement comprising an alarm unit arranged to receive a first signal from a rotation-measuring device on the aircraft, the alarm unit being further arranged to generate an alarm, for the purpose of preventing damage to the nose landing gear in dependence on the first signal, when the aircraft steering angle is greater than a predetermined value, wherein the predetermined value is close or equal to an angle beyond which there is a significant risk of damage occurring to the nose landing gear.
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26. In combination, an aircraft and a steering angle warning system, wherein the aircraft comprises
(i) a nose landing gear, and (ii) a rotation-measuring unit completely located on the aircraft, which is arranged to output a first signal dependent on the steering angle between the nose landing gear and the longitudinal axis of the aircraft fuselage, and the steering angle warning system (a) comprises the rotation-measuring unit, (b) is arranged to alert the driver of a tow vehicle, when such a tow vehicle is attached to the aircraft for towing the aircraft on the ground, when there is a risk of damage occurring to the aircraft nose landing gear because of excessive steering angle when towing, (c) includes an alarm unit that is suitable for alerting the driver of such a tow vehicle, and (d) is arranged to activate the alarm unit, for the purpose of preventing damage to the nose landing gear, the alert being generated in dependence on the first signal, when the steering angle is greater than a predetermined value, wherein the predetermined value is close or equal to an angle beyond which there is significant risk of damage occurring to the nose landing gear.
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30. A method of warning the driver of an aircraft towing vehicle that there is a risk of damage to the aircraft as a result of excessive steering angle to the nose landing gear of the aircraft being towed, the method comprising the steps of:
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(i) providing an aircraft having a fuselage and a nose landing gear, the nose landing gear including a rotation-measuring unit which is completely located on the aircraft and which is arranged to measure the steering angle between the nose landing gear and the longitudinal axis of the aircraft fuselage, (ii) providing a manually operated tow vehicle, (iii) connecting the tow vehicle to the aircraft, (iv) towing the aircraft by means of a human driver operating the tow vehicle, (v) using the rotation-measuring unit to determine whether the steering angle between the nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage is greater than a predetermined value, and (vi) if the steering angle is greater than the predetermined value, alerting the driver of the tow vehicle by means of generating an alarm for the purpose of preventing damage to the nose landing gear.
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Specification