Deployable Vortex Generators for Aircraft Wake Attenuation
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Solution Overview
Problem
Aircraft with rear shapes featuring rapid section reduction generate intense vortex wakes that interfere with airdrop operations, causing safety issues and material loss, and existing solutions like side deflectors and upsweep strakes are ineffective in significantly reducing vortex intensity or modifying their trajectory.
Innovation Solution
Deployable aerodynamic appendages, such as delta-wing shaped vortex generators, are positioned symmetrically downstream of the wing to interact with and dissipate the vortex wake, modifying its trajectory and intensity by creating a series of eddy structures that interact with the natural upsweep vortices, reducing their impact on the aircraft and airdropped materials.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the rear fuselage is designed with rapid section reduction (upsweep) to enable airdrop operations, then the aircraft can perform high-rate drops and equipment extraction, but intense vortex wakes are generated that cause safety issues and operational problems
Solution Approach 1:
The patent introduces vortex-generating aerodynamic appendages as intermediary elements that create controlled vortex structures to interact with and attenuate the harmful upsweep vortices. These appendages serve as mediators between the fuselage geometry and the wake flow, generating counter-rotating vortex structures that reduce the intensity and modify the trajectory of the harmful vortices through vortex-vortex interaction
Solution Approach 2:
The patent converts the harmful vortex wake into a beneficial effect by using vortex-generating appendages that create controlled vortex structures. These artificial vortices interact with the natural upsweep vortices to attenuate them, thereby converting the problematic vortex flow into a mechanism for vortex wake mitigation while maintaining the necessary airdrop capabilities
2Object-affected harmful factors
If fixed upsweep strakes are positioned at the rear of the fuselage to reduce vortex impact, then some vortex mitigation is achieved, but the devices are positioned far downstream where vortices have already reached maximum intensity, reducing effectiveness
Solution Approach 1:
The patent applies preliminary action by positioning the vortex-generating aerodynamic appendages upstream in the upsweep zone where the vortices are still forming and have not yet reached their maximum intensity. This allows the appendages to interact with the vortices at an earlier stage, preventing them from developing to full strength rather than attempting to mitigate them after they have already formed
3Object-affected harmful factors
If fixed appendages are added to the rear fuselage to mitigate vortices, then vortex control is attempted, but the appendages pose safety risks to personnel and equipment during airdrop operations
Solution Approach 1:
The patent applies dynamics by making the aerodynamic appendages deployable rather than fixed. The appendages can be deployed to generate vortex structures for wake mitigation when needed, and retracted or folded to clear the airdrop path when airdrop operations are conducted, thereby eliminating the safety risks associated with fixed appendages while maintaining vortex control capabilities
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
The solution effectively reduces the intensity and modifies the trajectory of vortex wakes, enhancing the precision and safety of airdrop operations, minimizing material loss and ensuring safer drops for personnel and equipment.
Implementation Method 1
at least two vortex-generating aerodynamic appendages capable of being deployed between a folded position and a deployed position, the deployed position being calculated to generate vortex structures
Implementation Method 2
generate vortex structures having an intensity and trajectory that modify the local pressure field in order to interact with the vortex wake to attenuate it
Data Source
Figure 1~3
Figure 2b
Figure 4a~4b
AI summary
The present invention relates to a device for attenuating the vortex wake generated in the tail section of an aircraft (100), the aircraft having at least one wing (108) and an afterbody (106) with an asymmetric cross-section that sharply decreases towards the top of the rear fuselage (112). The device is positioned downstream of the wing (108) of the aircraft (100), symmetrically relative to the longitudinal plane of the latter. The device comprises aerodynamic vortex-generating appendages (200) suitable for being deployed between a folded position where the aerodynamic appendages are folded substantially in the direction of the fuselage (110) and a deployed position calculated to generate vortex structures having an intensity and following a path that modify the local pressure field in order to interact with the vortex wake and attenuate it, and to move the upsweep vortices away from the longitudinal plane of the aircraft (100).