Flap system for an aircraft high lift system or an engine actuation and method for monitoring a flap system
First Claim
1. A method for monitoring an aircraft high lift system or an engine actuator having a rotary shaft and a first and a second load path from the rotary shaft, the method comprising the steps of:
- arranging at least a first and a second redundant load path from a rotational shaft, the first and second load paths comprising a first and a second respective rotational transmission having a first and a second respective output shaft;
positioning a first and a second respective torque sensor (7a, 7b) on the first and second output shafts, reading the output torque values of the first and second output shafts from the first and second torque sensors of the first and second transmissions according to a predefined cycle, and determining the difference in torque output from the first and second rotational transmissions;
providing a predefined torque threshold value or range and according to the predefined cycle, determining whether the difference, if any, between the output-side torque values at the first and second rotational transmissions of the at least two load paths exceeds the predefined torque threshold value and/or lies within the defined range; and
generating a signal representing whether the cyclically measured difference in the torque value output from the first and the second rotational transmissions exceeds the threshold or range, and transmitting the signal to a control unit.
1 Assignment
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Accused Products
Abstract
The invention relates to a flap system for an aircraft high lift system or an engine actuation with a rotary shaft system, one or more drive stations as well as elements for transmitting the drive energy from the rotary shaft system to the one or more drive stations, wherein at least one drive station includes at least two independent load paths with at least one rotational transmission each for actuating the flap kinematics, and per load path at least one mechanically coupling-free synchronization unit is provided for compensating regular load fluctuations between the load paths. The invention furthermore relates to a method for monitoring a flap system with at least two redundant load paths which each comprise at least one rotational transmission, wherein it is cyclically checked whether the difference of the output-side torques of the at least two load paths exceeds a defined threshold value and/or lies within a defined limit range.
7 Citations
9 Claims
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1. A method for monitoring an aircraft high lift system or an engine actuator having a rotary shaft and a first and a second load path from the rotary shaft, the method comprising the steps of:
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arranging at least a first and a second redundant load path from a rotational shaft, the first and second load paths comprising a first and a second respective rotational transmission having a first and a second respective output shaft; positioning a first and a second respective torque sensor (7a, 7b) on the first and second output shafts, reading the output torque values of the first and second output shafts from the first and second torque sensors of the first and second transmissions according to a predefined cycle, and determining the difference in torque output from the first and second rotational transmissions; providing a predefined torque threshold value or range and according to the predefined cycle, determining whether the difference, if any, between the output-side torque values at the first and second rotational transmissions of the at least two load paths exceeds the predefined torque threshold value and/or lies within the defined range; and generating a signal representing whether the cyclically measured difference in the torque value output from the first and the second rotational transmissions exceeds the threshold or range, and transmitting the signal to a control unit. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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Specification