Blended Wing Body Elevon Design for Drag Reduction
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Solution Overview
Problem
Blended wing body aircraft face challenges in aerodynamic control due to the drag created by conventional control surfaces, particularly vortex drag, which complicates fuel savings and noise reduction efforts.
Innovation Solution
The implementation of angular control surfaces with obtuse angle planforms in a unified control scheme for a blended wing body aircraft, minimizing the formation of vortex airflows and drag by eliminating exposed edge gaps, allowing for efficient roll, pitch, and yaw control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional control surfaces are used in blended wing body aircraft, then aerodynamic control is achieved, but vortex drag increases and fuel consumption rises
Solution Approach 1:
The control surface is divided into multiple segments (first control surface segment and second control surface segment) that can move independently relative to each other. This segmentation allows the surface to adapt its configuration to minimize vortex drag while maintaining aerodynamic control effectiveness, thereby reducing fuel consumption without sacrificing control capability.
Solution Approach 2:
The control surface is designed with dynamic movement capability, where the first and second control surface segments can move relative to one another along the leading edge. This dynamic adjustment allows the surface to optimize its aerodynamic properties during different flight phases, reducing vortex drag and associated energy losses while maintaining effective control.
2Object-affected harmful factors
If conventional control surfaces are used in blended wing body aircraft, then aerodynamic control is achieved, but noise levels increase
Solution Approach 1:
By segmenting the control surface into multiple independently movable segments, the design reduces vortex-induced noise while maintaining control effectiveness. The segmented structure allows for optimized airflow management that minimizes noise generation during aerodynamic control operations.
Solution Approach 2:
The dynamic capability of the segmented control surface allows real-time adjustment to minimize noise generation. The segments can move relative to each other to optimize airflow patterns, reducing vortex-induced noise while preserving aerodynamic control performance.
3Ease of operation
If a midship control surface is added for yaw control, then yaw control effectiveness is improved, but device complexity increases
Solution Approach 1:
The control surface system is designed with multi-functionality, where the segmented control surfaces can contribute to multiple aerodynamic control functions. The first and second control surface segments can work in conjunction with the midship control surface to provide integrated control across multiple axes, reducing the need for separate dedicated control surfaces and thereby limiting the increase in 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 solution reduces drag and maintains performance characteristics, enabling more efficient fuel consumption and noise reduction while providing effective control of the aircraft.
Implementation Method 1
minimizing the formation of vortex airflows and drag by eliminating exposed edge gaps
Data Source
AI summary
Aspects relate to airplanes having a blended wing body. A blended wing body may include a fuselage and a port wing and a starboard wing continuously coupled to the fuselage and a nose section. A midship control surface may be disposed on a trailing edge of the blended wing body and centered between the port wing and the starboard wing.