Spherical Thrust Vectoring Nozzle for VTOL Aircraft
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Solution Overview
Problem
Current systems for vectoring the exhaust of aircraft lift engines, particularly in VTOL aircraft, face limitations in efficiently deflecting airflow in multiple radial directions, which affects control during landing, takeoff, and hovering.
Innovation Solution
A thrust-vectoring nozzle system with a cylindrical case and a rotatable flow director having a circular profile, allowing rotation about two perpendicular axes, enables efficient airflow deflection in any radial direction, integrated with a lift fan assembly for enhanced control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single-direction swiveled nozzle is used for airflow vectoring, then the structure is simple, but the ability to deflect airflow in multiple radial directions is limited
Solution Approach 1:
The nozzle is divided into two independent flow directors, each capable of deflecting airflow in perpendicular directions. The first flow director deflects airflow in a first radial direction, while the second flow director deflects airflow in a second radial direction perpendicular to the first. This segmentation allows multi-directional airflow control without requiring a complex multi-axis swiveling mechanism.
Solution Approach 2:
The invention transitions from single-direction vectoring to two-dimensional radial vectoring by introducing a second flow director perpendicular to the first. This dimensional expansion enables airflow deflection in any radial direction around the central axis, significantly enhancing adaptability while maintaining relatively simple structural implementation through the use of two independent but perpendicular flow director units.
2Adaptability or versatility
If fixed vanes are used at the nozzle exit, then the structure is simple, but the airflow deflection angle and direction are limited
Solution Approach 1:
The flow directors are designed with rotational capability about the central axis, transforming the static fixed vane structure into a dynamic adjustable system. Each flow director can rotate independently to change the deflection angle and direction of airflow, enabling continuous adjustment of thrust vectoring in multiple radial directions while maintaining a relatively simple mechanical rotation mechanism.
3Adaptability or versatility
If a D-shaped nozzle with telescoping sections is used, then forward and aft thrust deflection is provided, but deflection in other radial directions is limited
Solution Approach 1:
The nozzle structure is segmented into multiple independent flow director units arranged perpendicular to each other around the central axis. Each flow director handles deflection in its specific radial direction, and the combination of these segmented units provides comprehensive three-dimensional thrust vectoring capability. This segmentation approach achieves full radial deflection coverage without requiring a complex telescoping D-shaped mechanism.
Solution Approach 2:
The flow directors are designed with universal rotational capability about the central axis, allowing each unit to deflect airflow in any radial direction within its plane. This multi-functional design enables the same basic flow director structure to provide deflection in multiple directions when combined with perpendicular arrangements, achieving comprehensive radial thrust vectoring without requiring different specialized mechanisms for each direction.
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 provides reliable and robust airflow deflection capabilities, stabilizing the aircraft during vertical operations by enabling control forces in multiple directions, improving landing, takeoff, and hovering performance.
Implementation Method 1
A thrust-vectoring nozzle provides a reliable and robust system for efficiently vectoring air flow at an angle to a central axis of the air flow in any radial direction from the central axis
Implementation Method 2
The flow director is disposed within the case such that the circular portion of the outer surface of the flow director adjoins the circular portion of the inner surface of the case such that the flow director is able to rotate about the first and second axes
Data Source
AI summary
A thrust-vectoring nozzle is disclosed that includes a cylindrical case and a flow director. The flow director includes a cylindrical ring having a dimension to fit within the cylindrical case. The cylindrical ring has an inner wall and an outer wall and a plurality of fixed vanes are coupled to the inner wall of the ring. The flow director is configured to rotate about first and second mutually perpendicular axes.