Aircraft Control via Wingtip Thrust and Swept Elevons
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft designs face challenges in achieving high speed and low speed efficiency simultaneously due to conflicting priorities between drag reduction and handling, with existing technologies often compromising on cost, weight, and complexity, while also failing to address stall-related accidents and fuel efficiency.
Innovation Solution
The design incorporates rearwardly swept lower wings and forwardly swept upper elevons with separate, vertically spaced airfoils positioned above the wingtips to create a downforce, eliminating traditional ailerons and tail structures, and utilizing suction boundary layer control to enhance lift and control, thereby reducing induced and surface drag while preventing stalls.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional ailerons and tail structures are used for aircraft control, then handling at low speeds is improved, but induced drag and surface drag increase
Solution Approach 1:
The patent removes traditional ailerons and horizontal/vertical tail structures from the aircraft design. Instead, it uses differential thrust from two propulsion systems positioned at the wingtips to provide all necessary control functions (roll, pitch, and yaw), thereby eliminating the drag-producing control surfaces while maintaining full maneuverability
Solution Approach 2:
The patent replaces mechanical control surfaces (ailerons, elevators, rudders) with a thrust-vectoring propulsion system. The differential thrust mechanism substitutes for the mechanical aerodynamic control surfaces, providing control through force differentiation rather than surface deflection, thus reducing induced and surface drag
2Loss of energy
If wingspan is increased to reduce induced drag, then aerodynamic efficiency is improved, but material strength requirements and airport infrastructure constraints are exceeded
Solution Approach 1:
The patent achieves the aerodynamic benefits of a large wingspan without physically extending the wing structure. By using distributed propulsion at the wingtips with differential thrust, it copies the control authority and drag-reduction effects of a large span without the associated structural weight and material strength requirements
Solution Approach 2:
The patent changes the control mechanism from aerodynamic surface deflection to thrust differentiation. This parameter change allows the aircraft to achieve span efficiency and control authority equivalent to a larger wingspan while maintaining a compact physical structure that meets airport infrastructure constraints
3Loss of energy
If highly streamlined aircraft design is used to reduce surface drag, then high speed performance is improved, but low speed handling deteriorates
Solution Approach 1:
The patent replaces aerodynamic control surfaces with a thrust-based control system that is independent of airspeed. The differential thrust mechanism provides effective control at all speeds, including low speeds where streamlined aircraft typically struggle, because it relies on propulsion force rather than aerodynamic pressure differential
4Loss of energy
If drag reduction mechanisms are incorporated to achieve high speed efficiency, then fuel economy is improved, but aircraft cost and complexity increase
Solution Approach 1:
The patent makes the propulsion system perform multiple functions: primary thrust generation, all flight control (roll, pitch, yaw), and drag reduction. By integrating these functions into a single system rather than adding separate mechanisms, the aircraft achieves high fuel economy without proportionally increasing complexity or cost
Solution Approach 2:
The patent merges the functions of propulsion and flight control into a unified system. The two wingtip propulsion units serve both to drive the aircraft forward and to provide all necessary control surfaces functionality, eliminating the need for separate control surface mechanisms and reducing overall system complexity
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 achieves high span efficiency and strength with reduced weight, enabling exceptional low-speed handling, improved fuel efficiency, and reduced costs, while preventing stalls and minimizing drag, leading to enhanced safety and performance across a range of speeds.
Implementation Method 1
utilizing suction boundary layer control to enhance lift and control
Implementation Method 2
at least one elevon structure positioned predominantly rearward of said at least one wing and above said at least one wing... having a direction of said aerodynamic force generally opposite to the direction of said positive lift
Data Source
AI summary
An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided by a central plane of reference. The aircraft has inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference. Further, the aircraft contains at least one positive lifting aerodynamic surface configured to affect the flow of air near said at least one positive lifting aerodynamic surface when said aircraft is appropriately moving forward, and at least one elevon structure configured to create negative aerodynamic force when said aircraft is appropriately moving forward. The elevon structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least three-fourths of the distance from said central plane of reference to a tip end of said at least one wing.