Mechanical Droop for Aircraft Spoiler Operation
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Solution Overview
Problem
Existing systems for operating aircraft wing control surfaces, such as flaps and spoilers, are complex due to their overlapping ranges of motion and require independent control mechanisms, which can lead to operational failures and increased component load.
Innovation Solution
A mechanical system that includes a torque tube coupled to a control surface, a gearing assembly to reduce rotation rates, and a linear actuator with an eccentric attachment point, allowing coordinated movement of control surfaces via a torque tube-driven mechanism, reducing the complexity and potential for independent operation failures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If independent control mechanisms are used for flaps and spoilers, then each control surface can be operated independently, but the system complexity increases and operational failures may occur
Solution Approach 1:
The patent combines the control of flaps and spoilers into a single integrated system. The torque tube and gearing assembly mechanically link both control surfaces, causing them to move together in a coordinated manner. This merging eliminates the need for separate independent control mechanisms while maintaining the ability to control both surfaces through a single actuator, thereby reducing system complexity while preserving operational capability.
2Stability of the object's composition
If complex systems are used to move control surfaces in unison, then coordinated operation is achieved, but the risk of operational failures increases
Solution Approach 1:
The mechanical linkage system is designed to automatically coordinate the movement of flaps and spoilers through pure mechanical means. The torque tube rotation automatically drives the gearing assembly, which in turn moves both control surfaces without requiring complex electronic control systems or multiple actuators. This self-service mechanical coordination reduces the number of potential failure points while maintaining stable coordinated operation.
3Ease of operation
If multiple control mechanisms are used, then precise control is achieved, but the component load and potential for failure increase
Solution Approach 1:
The torque tube serves multiple functions: it directly rotates the flap control surface, simultaneously drives the gearing assembly through mechanical engagement, and coordinates the spoiler movement. This multi-functional design consolidates what would otherwise require multiple separate control mechanisms into a single component, reducing the overall component load while maintaining precise control capability through the inherent mechanical geometry of the system.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This system simplifies the operation of aircraft wing control surfaces, reduces the risk of independent operation failures, and maintains aerodynamic performance by enabling synchronized movement of flaps and spoilers, enhancing lift and reducing drag.
Implementation Method 1
a torque tube coupled to a control surface of the aircraft wing, where the torque tube is rotatable at a first rate of rotation to cause a downward rotation of the control surface relative to the aircraft wing
Implementation Method 2
a gearing assembly coupled to the torque tube, where the gearing assembly comprises an output shaft, and where the torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation that is less than the first rate of rotation of the torque tube
Implementation Method 3
a linear actuator with a first end and a second end, where the first end of the linear actuator is coupled to the rotational member at a forward attach point, where the forward attach point is eccentric to the rotational center of the rotational member, and where the rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing
Data Source
AI summary
A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.