Distributed EDF Slat for Aircraft Low-Speed Lift
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Solution Overview
Problem
Current aircraft designs face challenges in achieving short takeoff and landing capabilities due to limitations in lift and control at low speeds, particularly during critical phases of flight such as takeoff, climb, descent, and landing.
Innovation Solution
The integration of a slat/nacelle/EDF assembly on the aircraft's leading edge, comprising a slat supported by two or more electric duct fans housed in nacelles, which accelerates and entrains air at high angles of attack to enhance lift and thrust, improving control and handling during these phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If traditional aircraft designs are used, then the aircraft structure is simple, but the lift and control capabilities at low speeds are insufficient
Solution Approach 1:
The aircraft wing is divided into multiple sections with distributed electric ducted fans positioned at different span locations. Each fan assembly operates independently to provide localized airflow control, enabling segmented lift enhancement across the wing surface while maintaining overall structural simplicity.
Solution Approach 2:
The electric ducted fans serve multiple functions: they provide lift enhancement during low-speed flight, improve control authority at high angles of attack, and can operate as thrust augmentors. This multi-functionality allows a single system to address multiple performance requirements without adding separate dedicated systems.
2Force
If higher lift at low speeds is achieved through conventional means, then the aircraft requires larger wings or high-lift devices, but the takeoff and landing distances remain insufficiently shortened
Solution Approach 1:
The electric ducted fans pre-accelerate the airflow over the wing surface before the aircraft reaches full speed, creating beneficial flow conditions and delaying separation at lower velocities. This preliminary airflow conditioning allows the aircraft to generate adequate lift at lower speeds, directly reducing takeoff and landing distances.
Solution Approach 2:
The system replaces conventional mechanical high-lift devices such as large flaps and slats with an active airflow control system using electric ducted fans. This substitution eliminates the need for complex mechanical linkages and large moving surfaces while achieving comparable or superior lift enhancement.
3Force
If the slat/nacelle/EDF assembly is permanently installed, then the lift and thrust are continuously enhanced, but the aircraft complexity and drag during cruise increase
Solution Approach 1:
The slat/nacelle/EDF assemblies are designed to be movable rather than fixed. The slats can adjust their position and angle dynamically based on flight conditions, and the nacelles can be repositioned along the wing span. This dynamic capability allows the system to optimize performance for different phases of flight while minimizing drag during cruise.
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 configuration significantly increases lift and thrust, enhances low-speed control, reduces loss-of-control situations, and improves handling during gusts and crosswinds, thereby enhancing short takeoff and landing performance.
Implementation Method 1
an electric duct fan (EDF) housed within each of the one or more nacelles, each EDF comprising a fan and a power source to operate the fan, wherein each EDF forces accelerated air through the fan and the gaps
Implementation Method 2
two or more nacelles positioned beneath and connected to a slat, wherein said nacelles are spaced apart to create at least one gap between the slat and the leading edge of the aerodynamic lifting element
Implementation Method 3
this improvement also accelerates and entrains the air between nacelles at high angles of attack, during takeoff, climb out, descent and landing, to enhance the benefits of the prior art
Data Source
AI summary
A powered aerodynamic lift device positioned on a leading edge of an aerodynamic lifting element (ALE), e.g. an airfoil, at least one slat/nacelle/EDF lift assembly comprising: a slat, a two or more nacelles positioned beneath the slat, each nacelle housing an electric ducted fan (EDF). The nacelles are spaced apart to create gaps between the slat and the airfoil for accelerated air to pass through. The lift assembly is under the operational control of and/or further comprises: a master control unit linked to a power source, e.g. batteries to power the EDFs. The device provides the ALE and aircraft with: increased lift and additional thrust during aircraft take offs, climbs, descents, and landings; enhanced low-speed control and reduced loss-of-control during an aircraft's takeoff and landing; improved aircraft handling during gusts and crosswinds. The present invention also comprises an ALE or aircraft with at least one lift assembly installed thereon.