Pivotable Exhaust Vane for Yaw Thrust Vectoring
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Solution Overview
Problem
Aircraft designers face limitations in maneuverability due to the complexity, weight, and cost of existing thrust vectoring nozzles, which are essential for high-speed military aircraft to enhance control and evade anti-aircraft missiles, while also increasing radar vulnerability.
Innovation Solution
Aircraft gas turbine engine yaw vectoring exhaust nozzle with a sideways pivotable exhaust vane in the divergent section, allowing for efficient thrust vectoring by pivoting the exhaust flow, featuring contoured or articulated vane designs to minimize flow separation and maintain performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional thrust vectoring nozzles are used, then maneuverability is improved, but device complexity increases
Solution Approach 1:
The exhaust vane is divided into multiple independent sections (first vane section, second vane section, third vane section) that can pivot separately about different axes. This segmentation allows complex three-dimensional flow vectoring to be achieved through simpler, independent rotational movements of each section, reducing overall system complexity while maintaining maneuverability.
Solution Approach 2:
The nozzle employs dynamically adjustable vane sections that can pivot about multiple axes (first pivot axis, second pivot axis, third pivot axis) to change the direction of exhaust flow in real-time. This dynamic capability enables the nozzle to adapt to various flight conditions and maneuvering requirements without requiring a completely complex fixed structure.
2Ease of operation
If traditional thrust vectoring nozzles are used, then maneuverability is improved, but weight increases
Solution Approach 1:
By dividing the exhaust vane into separate pivotable sections rather than using a single heavy mechanical thrust vectoring mechanism, the overall weight is reduced. Each section can be optimized independently and uses simpler pivot mechanisms rather than complex mechanical linkages.
Solution Approach 2:
The design replaces traditional mechanical thrust vectoring systems with a streamlined vane-based flow diversion approach. The vane sections pivot to redirect exhaust flow using aerodynamic forces rather than heavy mechanical thrust redirection mechanisms, significantly reducing weight while maintaining effectiveness.
3Ease of operation
If traditional thrust vectoring nozzles are used, then maneuverability is improved, but cost increases
Solution Approach 1:
The segmented vane structure allows each section to be manufactured separately using standard fabrication processes, then assembled together. This modular approach reduces manufacturing complexity and cost compared to producing a single complex integrated thrust vectoring nozzle, while still achieving the desired maneuverability performance.
4Ease of operation
If aircraft control surfaces are used, then maneuverability is provided, but radar signature increases
Solution Approach 1:
The invention extracts the thrust vectoring function from traditional external control surfaces and integrates it into the exhaust nozzle system. By moving the maneuverability control to the nozzle itself, the aircraft can maintain a sleeker airframe without large external control surfaces, thereby reducing radar cross-section and improving stealth characteristics.
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 provides enhanced maneuverability without the complexity, weight, or expense of traditional thrust vectoring systems, while reducing radar signature and maintaining cruise efficiency across various flight conditions.
Implementation Method 1
an exhaust vane (26) disposed in a divergent section (13) of the nozzle and is sideways pivotable about a vane pivot axis (28) extending transversely between upper and lower surfaces (35, 37) of an outer wall (23) of the nozzle
Data Source
AI summary
An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.