Deformable Nacelle Fairing for VTOL Thrust Vectoring
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Solution Overview
Problem
VTOL aircraft with shrouded rotors lack maneuverability in hovering flight, experiencing complex positioning corrections and discomfort for passengers due to inadequate lateral thrust control, while existing solutions fail to implement three-dimensional vector thrust technology in nacelle fairings.
Innovation Solution
A propulsion system with a nacelle fairing made of deformable shape-memory material and actuator mechanisms using cylinders to vary the air outlet shape, allowing for lateral thrust component control, enhancing maneuverability and reducing noise and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If shrouded rotors are used in VTOL aircraft, then noise reduction and rotor protection are improved, but maneuverability in hovering flight deteriorates
Solution Approach 1:
The nacelle fairing is made dynamically adjustable through shape-memory material walls that can change their configuration in response to control signals. The radially external wall includes actuator mechanisms with cylinders that can deform the wall to vary the outlet cross-section shape, enabling dynamic thrust vectoring for improved maneuverability while maintaining the noise-reducing shrouded structure.
Solution Approach 2:
The invention changes the physical parameters of the nacelle fairing by using shape-memory material that can alter its shape and stiffness characteristics. By controlling the deformation of the radially external wall through actuator mechanisms, the outlet cross-section parameters (area, shape, orientation) can be varied to optimize thrust direction for different flight conditions, resolving the maneuverability limitation.
2Stability of the object's composition
If complex positioning corrections are implemented for hovering flight, then flight stability is improved, but passenger comfort deteriorates
Solution Approach 1:
Instead of using complex sequential corrections that cause aircraft tilting and passenger discomfort, the invention implements dynamic thrust vectoring through the deformable nacelle fairing. The actuator mechanisms can rapidly adjust the outlet cross-section shape to provide precise lateral thrust control, achieving positioning stability through direct thrust modulation rather than aircraft attitude changes.
3Ease of operation
If lateral thrust control is added to improve maneuverability, then ease of operation is improved, but device complexity increases
Solution Approach 1:
The nacelle fairing structure serves multiple functions: it provides noise reduction (original shroud function), rotor protection, and now also enables lateral thrust control through its deformable geometry. The same shape-memory material walls and actuator mechanisms that modify the outlet cross-section shape also serve to direct the thrust vector, eliminating the need for separate lateral control mechanisms.
Solution Approach 2:
The invention uses flexible shape-memory material walls in the nacelle fairing, particularly the radially external wall, that can be deformed by actuator mechanisms to change the outlet cross-section shape. This flexible approach enables lateral thrust control through geometric modification rather than rigid mechanical linkages, 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
Improves VTOL aircraft maneuverability during low-speed flights like take-offs and landings, minimizing noise and ensuring rotor safety by providing precise lateral thrust control, while maintaining structural integrity and aerodynamic efficiency.
Implementation Method 1
the radially external wall comprises a plurality of actuator mechanisms with at least one cylinder, each actuator mechanism being operable independently of the other actuator mechanisms and being configured to cooperate with means embedded in an internal surface of the radially external wall so as to deform the radially external wall in a radial direction with respect to the axis of rotation
Data Source
AI summary
A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.