STOL Aircraft Flap Assembly with Embedded Propellers
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Solution Overview
Problem
Current Short Take Off and Landing (STOL) fixed wing aircraft are limited in their ability to operate on very short runways, necessitating the development of enhanced technologies to improve takeoff and landing capabilities, particularly in scenarios like pandemic response where access to remote areas is critical.
Innovation Solution
The integration of an enhanced flap assembly and aileron system with remotely operable propellers driven by electric motors, which increase wing surface area and lift, and a digital control system managing propeller operation based on airspeed and attitude to optimize takeoff and landing sequences.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of stationary object
If conventional STOL aircraft designs are used, then takeoff and landing capabilities are achieved, but the runway length required is still too long for very remote areas
Solution Approach 1:
The patent implements dynamically adjustable flaps that can change position and configuration during flight phases. The flaps are movable and can be extended or retracted based on flight conditions, allowing the wing geometry to adapt dynamically. This dynamic adjustment optimizes lift characteristics for short runway operations while maintaining conventional STOL reliability.
Solution Approach 2:
The wing is divided into multiple independent flap segments that can be controlled separately. Each flap portion can be adjusted independently to create optimal lift distribution across the wing span. This segmentation allows precise control of aerodynamic characteristics to minimize runway length while ensuring reliable takeoff and landing performance.
2Length of stationary object
If flap surface area is increased to enhance lift, then takeoff distance is reduced, but drag increases affecting cruise performance
Solution Approach 1:
The flaps are designed to be dynamically adjustable rather than fixed. During takeoff and landing phases, the flaps extend to increase surface area and generate maximum lift, reducing takeoff distance. During cruise flight, the flaps retract to minimize surface area and reduce drag, optimizing energy efficiency. This dynamic configuration allows the system to achieve both short takeoff distance and low cruise drag.
3Force
If propellers are exposed to provide airflow over flaps, then lift is increased, but the aircraft structure becomes more complex
Solution Approach 1:
The propeller system is integrated directly into the flap structure itself. The propellers are mounted within the flap assemblies, combining the flap function with the propeller-driven airflow generation function. This merging eliminates the need for separate, complex external mechanisms to expose propellers, reducing overall structural complexity while still providing the lift-enhancing airflow over the flaps.
Solution Approach 2:
The flap assembly serves multiple functions: it acts as both a lift-generating surface and a housing for the propeller system. The same structural elements that form the flap also support and protect the propellers. This multi-functionality reduces the number of separate components needed, simplifying the overall aircraft structure while achieving enhanced lift through propeller-driven airflow.
4Force
If multiple electric motors and batteries are added to drive propellers, then lift and control are enhanced, but weight increases
Solution Approach 1:
The power system is segmented into distributed electric motors and batteries integrated within the flap structures themselves. Rather than having a single heavy centralized power system, the power components are distributed and embedded within the flaps. This segmentation allows the weight of the power system to be closely coupled with the components it directly supports (the propellers and flaps), improving weight distribution and reducing overall structural weight requirements.
Solution Approach 2:
The electric motors and batteries are nested within the flap assemblies. The power components are housed inside the flap structures, with the motors and batteries contained within the same space that houses the propeller mechanisms. This nesting arrangement eliminates the need for separate external mounting structures for the power system, reducing overall aircraft weight while still providing enhanced lift through the propeller-driven flap 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
Enables STOL aircraft to operate on significantly shorter runways by enhancing lift and control during takeoff and landing, reducing the distance required for both operations and improving the aircraft's ability to deliver vaccines and medications to remote areas.
Implementation Method 1
with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing
Implementation Method 2
a first electric motor... driving a propeller shaft
Implementation Method 3
the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing
Data Source
AI summary
A flap assembly for a fixed wing aircraft, comprising first and second flap portions, a compartments in the flap portions enclosing rechargeable batteries, motor controllers and electric motors, vertically-oriented slots in the first flap portion with propellers operable through a sidewall of the slot, such that the propeller in operation extends both over and under the top and bottom walls of the flap portion. With the flap assembly retracted in the wing the propeller is entirely enclosed in the length of the slot, and wherein the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing, exposing the slot, and with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing.