Distributed Wing Fans for Lift Control Without Flaps
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Solution Overview
Problem
Aircraft high-lift devices, such as slats and flaps, increase lift but add complexity and mass, making them undesirable for reducing weight and complexity in propulsion systems.
Innovation Solution
A distributed propulsion system with independent control of suction and pressure fan arrays mounted above and below the wing, allowing for localized adjustment of air pressure to optimize lift without the need for traditional high-lift devices.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If traditional high-lift devices (slats, flaps) are used to increase lift, then the lift capability is improved, but the device complexity and mass increase
Solution Approach 1:
The patent divides the wing into multiple sections with distributed suction fans and pressure fans along the span. Each fan array is independently controllable, allowing localized lift control without requiring complex mechanical high-lift devices across the entire wing. This segmentation replaces traditional unified flaps/slats with distributed independent elements.
Solution Approach 2:
The patent replaces mechanical high-lift devices (slats, flaps) with an aerodynamic system using suction and pressure fans. Instead of moving mechanical surfaces to change wing geometry, the system uses fans to actively control boundary layer airflow and pressure distribution, thereby generating lift through aerodynamic forces rather than mechanical configuration changes.
2Force
If traditional high-lift devices (slats, flaps) are used to increase lift, then the lift capability is improved, but the mass increases
Solution Approach 1:
The patent replaces heavy mechanical high-lift devices with lighter aerodynamic fan systems. The suction and pressure fans create aerodynamic forces to generate lift without requiring the mass-intensive mechanical structures, hinges, and actuators of traditional slats and flaps.
Solution Approach 2:
The patent changes the approach from geometric parameter changes (moving flaps and slats to alter wing shape) to flow parameter changes (controlling boundary layer characteristics and pressure distribution through suction and pressure fans). This allows lift generation through aerodynamic parameter control rather than mechanical configuration changes.
3Ease of operation
If hydraulic systems are positioned along the wings to control high-lift devices, then the lift control capability is improved, but the system complexity and mass increase
Solution Approach 1:
The patent replaces hydraulic control systems with an aerodynamic fan control system. Instead of using hydraulic actuators to move mechanical high-lift devices, the system uses electrically controlled fans to directly manipulate airflow and pressure, eliminating the need for complex hydraulic infrastructure along the wings.
4Ease of operation
If hydraulic systems are positioned along the wings to control high-lift devices, then the lift control capability is improved, but the mass increases
Solution Approach 1:
The patent replaces heavy hydraulic systems with lighter aerodynamic fan systems. The mass of hydraulic fluid, pumps, valves, and associated infrastructure is eliminated in favor of electrically controlled fans that generate aerodynamic forces for lift control.
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 solution enables efficient lift control during various flight phases, reducing the need for complex high-lift devices and minimizing weight, while also allowing the pressure fans to generate electrical power through windmilling, enhancing aircraft performance and efficiency.
Implementation Method 1
causing, by the one or more controllable devices, one or more controllable devices of the aircraft to adjust at least one of a first operating point for the one or more fans of the suction fan array and a second operating point for the one or more fans of the pressure fan array so that a pressure ratio of an air pressure below the bottom surface of the wing to an air pressure above the top surface of the wing is changed
Implementation Method 2
windmilling one or more fans of a pressure fan array, the one or more fans of the pressure fan array each being mounted to the wing of the aircraft and each being positioned primarily below a bottom surface of the wing, wherein in windmilling the one or more fans of the pressure fan array, the one or more fans of the pressure fan array are driven about their respective axes of rotation by incoming airflow so that one or more electric machines operatively coupled thereto output electrical power
Data Source
AI summary
An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.