Thrust Reverser Actuation Linkage Layout for Tight Aircraft Packaging
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Solution Overview
Problem
Existing actuation systems for thrust reversers in aircraft propulsion systems face challenges due to space and packaging constraints, necessitating an improved design that can efficiently manage the movement of components while optimizing space utilization.
Innovation Solution
An actuation system comprising actuators, linkage systems, and gearboxes that include cross-over and side linkage shafts, allowing for synchronized movement of thrust reverser components, with flexible shafts and gearboxes that enable torque transfer and avoid obstacles, while maintaining synchronization among actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If traditional linkage systems are used for thrust reverser actuation, then the system can achieve basic movement functionality, but the space requirements and packaging complexity increase
Solution Approach 1:
The patent implements nesting by placing the cross-over shaft within the gearbox structure, and positioning linkage shafts to pass through or alongside other components. The first and second linkage shafts are arranged to operate within the confined space defined by the gearbox housing and other mechanical components, effectively nesting multiple moving elements within a compact volume.
Solution Approach 2:
The patent utilizes three-dimensional spatial arrangement by offsetting the first and second linkage shafts axially and radially, and positioning the cross-over shaft to transfer torque between different planes. This multi-dimensional arrangement allows the linkage system to achieve complex movement patterns while maintaining a compact footprint.
2Reliability
If multiple linkage shafts are used to synchronize actuator movement, then synchronized operation is achieved, but the system complexity and number of components increase
Solution Approach 1:
The patent merges the functions of multiple linkage shafts with the gearbox structure. The first and second linkage shafts are integrated with the gearbox housing, and the cross-over shaft is positioned to engage with both shafts simultaneously. This merging reduces the number of separate components while maintaining the synchronization function.
Solution Approach 2:
The cross-over shaft acts as an intermediary element that transfers torque between the first and second linkage shafts. This intermediary mechanism ensures synchronized operation of the actuators without requiring direct mechanical coupling between all components, thereby simplifying the overall system architecture.
3Adaptability or versatility
If flexible shafts and gearboxes are used to avoid obstacles, then the system can navigate complex spatial constraints, but manufacturing complexity increases
Solution Approach 1:
The patent employs dynamic spatial arrangement where the linkage shafts and cross-over shaft are positioned to flexibly navigate around obstacles such as the turbine engine and nacelle structures. The shafts are arranged with appropriate clearances and angular orientations that allow for thermal expansion, manufacturing tolerances, and assembly variations while maintaining functional clearance from obstacles.
Data Source
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AI summary
An assembly (66) is provided for an aircraft propulsion system (20). This assembly (66) includes a first actuator (68), a second actuator (68) and a linkage system (70, 72). The linkage system (70, 72) is configured to transfer torque between the first actuator (68) and the second actuator (68). The linkage system (70, 72) includes a first linkage shaft (90), a second linkage shaft (90) and a gearbox (92). The first linkage shaft (90) has a first centerline (94). The second linkage shaft (90) has a second centerline (94) offset from the first centerline (94). The gearbox (92) is coupled to and is between the first linkage shaft (90) and the second linkage shaft (90).