Flap Tip Vortex Suppression for Aircraft Noise Reduction
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Solution Overview
Problem
Existing high-lift devices for flight vehicles generate significant aerodynamic noise during takeoff and landing, which is exacerbated by the need for complex pneumatic systems to reduce noise, leading to increased weight and maintenance complexity.
Innovation Solution
A high-lift device with a vortex suppressing portion at the tip end of the flap main body, which modifies the shape to reduce vortex strength and fluctuations, thereby minimizing aerodynamic noise without increasing airframe weight or complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a pneumatic source with a dedicated compressor is applied to eject air currents for noise reduction, then aerodynamic noise is reduced, but the device size and airframe weight increase
Solution Approach 1:
The invention extracts and eliminates the complex pneumatic source system (compressor, pipes, control mechanisms) from the high-lift device. Instead of using external pneumatic power to eject air currents, the solution modifies the flap geometry itself to passively control vortex formation and reduce noise through shape optimization alone.
Solution Approach 2:
The high-lift device uses its own structural geometry to achieve noise reduction without requiring external pneumatic systems. The optimized flap shape naturally controls airflow and vortex formation, making the system self-sufficient and eliminating the need for additional weight-bearing components.
2Object-affected harmful factors
If pipes for air introduction are provided inside the flap to implement pneumatic noise reduction, then aerodynamic noise is reduced, but the device complexity and maintenance workload increase
Solution Approach 1:
The invention removes the complex internal piping system from the flap structure. By eliminating the need for air introduction pipes, valves, and control mechanisms, the design simplifies the overall system while maintaining noise reduction effectiveness through geometric optimization.
Solution Approach 2:
The flap structure achieves noise control through its own geometry rather than requiring embedded pneumatic infrastructure. This self-service approach eliminates maintenance-intensive components while preserving the noise reduction function.
3Object-affected harmful factors
If the flap shape is modified to suppress vortex formation, then aerodynamic noise is reduced, but the lift characteristics may be affected
Solution Approach 1:
The invention applies localized geometric modifications only at the flap tip region where vortex formation occurs, rather than changing the entire flap structure. This targeted approach suppresses harmful vortices while preserving the overall lift-generating geometry and aerodynamic performance of the main flap body.
Solution Approach 2:
The invention modifies specific geometric parameters (such as tip shape, curvature, or local thickness) of the flap to control vortex behavior. By carefully adjusting these parameters, the design reduces vortex-induced noise while maintaining optimal lift characteristics through balanced geometric optimization.
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
Effectively reduces aerodynamic noise generated by the high-lift device without increasing the airframe weight or complicating maintenance, improving practicality and noise reduction efficiency.
Implementation Method 1
a vortex rolling up from a lower surface of a tip end portion of a flap main body of the high-lift device to an upper surface of the tip end portion of the flap main body at the tip end portion of the flap main body exists at a position close to a surface of the tip end portion of the flap
Data Source
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AI summary
A high-lift device (3) of a flight vehicle includes: a flap main body (11) provided at a trailing edge portion of a main wing (2) of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing (2); and a vortex suppressing portion (100, 200, 300, 400, 500, or 600) provided at a tip end portion of the flap main body (11) in a wing span direction of the flap main body (11) and configured to suppress a vortex rolling up from a lower surface of a tip end portion (11a) of the flap main body (11) to an upper surface of the tip end portion (11a).