Aircraft Vane Air Circuits for Bidirectional Flow Control
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Solution Overview
Problem
Existing aircraft vertical stabilizers lack efficient air management systems that can enhance maneuverability, reduce drag, and optimize airflow for propulsion systems, while also providing structural support and noise reduction.
Innovation Solution
The implementation of a vane with integrated air circuits and door assemblies that regulate airflow direction and exhaust, allowing for controlled airflow patterns to enhance lift, reduce drag, and manage boundary layer air, thereby improving aircraft performance and maneuverability without traditional rudders.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional rudders are used for maneuverability, then structural simplicity is maintained, but airflow management and drag reduction capabilities are limited
Solution Approach 1:
The vertical stabilizer is designed to perform multiple functions simultaneously: it provides structural support, acts as a noise attenuator, manages boundary layer air, and enables controlled airflow patterns for maneuverability without requiring separate traditional rudders. The door assemblies allow the same structure to serve both as a stabilizer and an airflow control mechanism.
Solution Approach 2:
The invention uses pneumatic principles by incorporating air circuits and door assemblies that can regulate and direct airflow. The door assemblies can open or close to control air exhaust, creating controlled airflow patterns that enhance maneuverability while managing boundary layer air effects.
2Productivity
If boundary layer air is not managed, then structural simplicity is maintained, but drag increases and lift is reduced
Solution Approach 1:
The invention extracts and removes boundary layer air from the airflow path through dedicated air circuits and door assemblies. By selectively opening doors to exhaust boundary layer air, the system cleans up the airflow over the wings and fuselage, reducing drag and improving lift without requiring complex additional structures.
Solution Approach 2:
The door assemblies act as intermediaries between the boundary layer air and the external environment. They regulate and control the exhaust of boundary layer air, mediating the interaction between the airflow and the aircraft surfaces to optimize aerodynamic performance.
3Ease of operation
If air circuits are integrated into the vertical stabilizer, then airflow management is improved, but manufacturing complexity increases
Solution Approach 1:
The air management system is segmented into discrete components: air circuits, door assemblies, and exhaust outlets. This segmentation allows each component to be manufactured and tested separately before assembly, reducing overall manufacturing complexity while enabling precise airflow regulation through the coordinated operation of individual segments.
4Adaptability or versatility
If door assemblies are used to direct airflow, then maneuverability is enhanced, but device complexity increases
Solution Approach 1:
The door assemblies are designed as dynamic components that can change their position between open and closed states to control airflow direction. This dynamic capability allows the same structure to adapt to different flight conditions and maneuver requirements, enhancing versatility while managing complexity through a relatively simple mechanical actuation 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
The system provides enhanced lift and maneuverability by directing airflow to increase camber, reduces drag by managing boundary layer air, and optimizes airflow to propulsion systems, while also serving as a structural divider and noise attenuator.
Implementation Method 1
The first door assembly is configured to direct the flow of air exhausted from the first circuit outlet longitudinally towards the leading edge during the first mode of operation. The first door assembly is configured to direct the flow of air exhausted from the first circuit outlet longitudinally towards the trailing edge during the second mode of operation.
Implementation Method 2
The air system is configured to exhaust a flow of air out of the first air circuit through the first circuit outlet during a first mode of operation and a second mode of operation
Data Source
AI summary
A system for an aircraft includes a vane and an air system. The air system includes a first air circuit and a first door assembly. The first air circuit extends in the vane to a first circuit outlet at a first side of the vane. The first door assembly is arranged at the first circuit outlet. The air system is configured to exhaust a flow of air out of the first air circuit through the first circuit outlet during a first mode and a second mode. The first door assembly is configured to direct the flow of air exhausted from the first circuit outlet longitudinally towards a leading edge of the vane during the first mode. The first door assembly is configured to direct the flow of air exhausted from the first circuit outlet longitudinally towards a trailing edge of the vane during the second mode.