Synchronized Propeller Cooling Flaps With Single-Actuator Linkage
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Solution Overview
Problem
The existing cooling devices for aircraft propulsion assemblies have a high number of actuators, leading to increased onboard mass and energy consumption, and lack synchronized movement of intake and exhaust flaps, impacting aerodynamic performance.
Innovation Solution
A cooling device with synchronized movement of intake and exhaust flaps via a shared actuator, using a kinematic chain, and configured with slide and pivoting connections to reduce the number of actuators and enhance mass efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If separate actuators are used for each intake and exhaust flap, then each flap can be controlled independently, but the number of actuators increases leading to increased onboard mass and energy consumption
Solution Approach 1:
The patent combines multiple flap control functions into a single actuator that can simultaneously control both intake and exhaust flaps. This merging of control functions reduces the total number of actuators from multiple separate units to a single integrated actuator, thereby reducing onboard mass while maintaining the ability to control each flap independently through the shared actuator's coordinated operation.
Solution Approach 2:
The single actuator is designed with multi-functionality to control both intake and exhaust flaps. This universal actuator can perform multiple control tasks that previously required separate dedicated actuators, reducing the overall actuator count and associated mass while preserving independent control capability through programmed coordination.
2Ease of operation
If separate actuators are used for each intake and exhaust flap, then each flap can be controlled independently, but the number of actuators increases leading to increased energy consumption
Solution Approach 1:
By merging multiple actuator control functions into a single actuator unit, the total energy consumption is reduced. The single actuator consumes less energy than multiple separate actuators would consume individually, while still providing independent control of each flap through coordinated operation controlled by a single control unit.
Solution Approach 2:
The universal actuator performs multiple control functions with a single energy source, eliminating the redundant energy consumption that would occur with multiple separate actuators. This multi-functional design reduces overall energy usage while maintaining full control capability over all flaps.
3Device complexity
If only an intake flap is used without a synchronized exhaust flap, then the actuator count is reduced, but aerodynamic performance is impacted due to lack of synchronized movement
Solution Approach 1:
The patent merges the control of intake and exhaust flaps into a single actuator system that coordinates both flaps simultaneously. This merging approach maintains low device complexity with only one actuator while ensuring synchronized movement of both flaps to minimize aerodynamic disturbances, thus resolving the contradiction between simplicity and aerodynamic performance.
Solution Approach 2:
The control unit monitors and coordinates the position of both intake and exhaust flaps to ensure they move in a synchronized manner. This feedback mechanism ensures that aerodynamic performance is maintained through proper coordination, even though only a single actuator is used to control both flaps.
Data Source
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AI summary
The invention relates to a cooling device for an aircraft propulsion system comprising: - at least one cooling circuit having at least one air inlet equipped with an intake flap (64) movable between closed and open positions, and at least one air outlet equipped with an exhaust flap (66) movable between closed and open positions; - at least one actuator (76) coupled by at least one kinematic chain (78, 78') to the intake and exhaust flap pair (64, 66) such that said intake and exhaust flaps (64, 66) move in synchronized fashion and simultaneously occupy the closed or open position. This solution makes it possible to reduce the number of actuators and, ultimately, the aircraft's onboard mass.