Wing Energy Reutilization System for Drag Reduction
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Solution Overview
Problem
Current aircraft systems fail to effectively recapture wasted energy from induced drag, leading to inefficiencies in energy usage and increased fuel consumption.
Innovation Solution
The implementation of a wing energy reutilization system that captures energy from air vortices using a vortex rotor and converts it into torque through a transmission and drive shaft, which is then used to power a stagnation compressor, reservoir, and jet ejector system to enhance airflow and reduce drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If aircraft operate with conventional wing designs, then simplicity of design is maintained, but energy is wasted through induced drag
Solution Approach 1:
The patent captures the harmful wingtip vortices and induced drag energy and converts it into useful work. The vortex rotor extracts rotational energy from the vortices that would otherwise be wasted, converting it to drive the stagnation compressor and jet ejector system, thereby transforming an energy loss into a beneficial contribution to thrust and drag reduction.
Solution Approach 2:
The patent introduces intermediary devices (vortex rotor, transmission, drive shaft, stagnation compressor, reservoir, jet ejector) that mediate between the wasted vortex energy and the aircraft's propulsion needs. These intermediaries capture, transmit, store, and release energy in a controlled manner to reduce induced drag and enhance thrust.
2Use of energy by moving object
If energy is recaptured from induced drag, then fuel consumption decreases, but device complexity increases
Solution Approach 1:
The system is designed to be self-sustaining by using the waste energy from the aircraft's own operation to power the energy recapture and release mechanisms. The vortex rotor is driven by the aircraft's own wingtip vortices, and the stored energy is released back to the aircraft through the jet ejector, creating a closed-loop system that reduces fuel consumption without requiring external power sources.
3Stress or pressure
If stagnation compressor is used to compress air, then air pressure increases, but energy consumption increases
Solution Approach 1:
The stagnation compressor compresses air in advance and stores it in the reservoir before it is needed for jet ejector operation. This preliminary compression and storage of energy allows the system to have energy available when needed without requiring continuous energy input during the jet ejector's operation, thereby reducing overall energy consumption.
4Force
If jet ejector releases stored energy, then thrust increases, but system complexity increases
Solution Approach 1:
The system operates in periodic cycles: the stagnation compressor compresses air and stores it in the reservoir during one phase, and the jet ejector releases the stored energy to generate thrust during another phase. This periodic operation allows the system to achieve thrust enhancement while managing the complexity of coordinating multiple components in a rhythmic, controlled manner.
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 system reduces pressure drag, increases thrust, decreases fuel consumption, improves stall control, and optimizes the flow field over the aircraft wing, making it more efficient and sustainable.
Implementation Method 1
captures energy from air vortices using a vortex rotor
Implementation Method 2
utilizes energy captured from an air vortex occurring around an aircraft wing tip
Implementation Method 3
converts wind energy captured by the vortex rotor into a particular amount of torque to a drive shaft
Implementation Method 4
compresses air approaching a wing's leading edge, the stagnation compressor increases the air pressure but does not disturb the flow field
Implementation Method 5
The jet ejector is compromised of a series of nozzles that are distributed across the wing span that is in close proximity to the wing's leading edge. In embodiments, the series of nozzles release air in velocities that are higher than the free air stream velocity
Data Source
AI summary
An apparatus, including a vertex rotor. The apparatus includes a transmission system, with the transmission system connected to the vertex rotor. The apparatus includes a drive shaft, with the drive shaft connected to the transmission system. The apparatus includes a first bevel gear and a second bevel gear. The first bevel gear and the second bevel gear are connected to the drive shaft.