Deformable Nacelle Fairing for VTOL Thrust Vectoring
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
VTOL aircraft with shrouded rotors lack maneuverability in hovering flight, making it difficult to correct altitude and placement, and are prone to discomfort for passengers due to complex and uncomfortable flight corrections.
Innovation Solution
A propulsion system with a nacelle fairing made of deformable shape-memory material and equipped with pneumatic or hydraulic actuators that can independently deform to change the air flow direction, allowing for a lateral thrust component and improved maneuverability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If VTOL aircraft use shrouded rotors with conventional control systems, then rotor protection and noise reduction are improved, but maneuverability and positioning precision deteriorate
Solution Approach 1:
The nacelle fairing transitions from a rigid structure to a dynamic, deformable structure using shape-memory materials. The downstream section can actively change its geometry in real-time under actuator control, enabling the enclosed rotor system to achieve maneuverability comparable to conventional helicopters while maintaining the protective benefits of shrouding.
Solution Approach 2:
The invention changes the physical state and geometric parameters of the nacelle fairing by using shape-memory materials that can alter their form in response to thermal or mechanical stimuli. This allows the fairing to dynamically adjust thrust vectoring angles and outlet geometry, providing precise positioning control without compromising rotor protection.
2Reliability
If VTOL aircraft use shrouded rotors with conventional control systems, then rotor protection and noise reduction are improved, but positioning precision and flight comfort deteriorate
Solution Approach 1:
The deformable downstream section of the nacelle fairing enables dynamic adjustment of the thrust vector direction with high precision. By controlling the shape-memory material actuators, the system can make fine positioning corrections in real-time, achieving accurate altitude and placement control while the aircraft remains enclosed, thereby improving both positioning precision and passenger comfort.
3Strength
If conventional rigid nacelle fairings are used, then structural strength is improved, but thrust vectoring capability and maneuverability deteriorate
Solution Approach 1:
The nacelle fairing employs a hybrid structure where the upstream section maintains rigid material properties for structural strength and engine mounting, while the downstream section uses shape-memory materials that can deform. This local differentiation of material properties allows the fairing to simultaneously provide structural support and active thrust vectoring capability.
Solution Approach 2:
The invention uses composite construction combining rigid materials in the upstream section with shape-memory materials in the downstream section. This composite approach allows the fairing to exhibit both structural rigidity where needed and controlled deformability for thrust vectoring, resolving the contradiction between strength and adaptability.
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 system enhances the maneuverability of VTOL aircraft by providing a lateral thrust component, reducing noise pollution, and ensuring rotor safety, while minimizing weight and aerodynamic losses associated with flight commands.
Implementation Method 1
a downstream section forming an outlet cross-section of the nacelle fairing, said downstream section comprising a radially internal wall and a radially external wall made of a deformable shape-memory material
Implementation Method 2
said downstream end forming the outlet cross-section comprises a plurality of pneumatic or hydraulic actuators, the actuators extending in different consecutive angular sectors about said axis of rotation
Implementation Method 3
said downstream end forming the outlet cross-section comprises a plurality of pneumatic or hydraulic actuators
Implementation Method 4
each actuator being actuatable independently of the other actuators and being configured to deform in a direction which is radial with respect to the axis of rotation and which is angularly centred with respect to the angular sector over which it extends
Data Source
AI summary
The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.