Rotatable Exhaust Nozzle Assembly for High-Altitude Thrust Vectoring
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Solution Overview
Problem
Existing exhaust nozzle assemblies for air vehicles have limited maneuverability and agility due to their inability to significantly alter net axial thrust and generate substantial lateral thrust, resulting in complicated control systems and low maneuverability.
Innovation Solution
The exhaust nozzle assembly features rotatably mounted nozzles that can vary their angle of exhaust gas direction by at least 25 degrees, allowing for versatile thrust direction control, including configurations that provide zero thrust in specific directions, enabling optimized velocity profiles and improved air vehicle efficiency across its flight envelope.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional aerodynamic control surfaces are used, then flight path control is achieved, but effectiveness is rendered insufficient at high altitudes due to low air density
Solution Approach 1:
The patent replaces conventional aerodynamic control surfaces with a nozzle system that generates thrust forces through exhaust gas direction control. This substitution eliminates dependence on air density for control effectiveness, as the nozzle system operates by directing high-velocity exhaust gases rather than relying on atmospheric air for aerodynamic forces.
Solution Approach 2:
The patent changes the fundamental parameter of control from aerodynamic forces (dependent on air density) to thrust forces (dependent on exhaust gas velocity and direction). By controlling the direction of exhaust gas flow through the nozzle assembly, the system achieves effective control at high altitudes where air density is low.
2Ease of operation
If nozzles are mounted with limited deflection angle (e.g., 10 degrees), then structural simplicity is maintained, but maneuverability and lateral thrust generation are insufficient
Solution Approach 1:
The patent employs gimbal mechanisms that allow dynamic adjustment of nozzle orientation in multiple dimensions. The nozzles can be deflected through large angles (up to 45 degrees or more) while maintaining structural integrity, enabling enhanced maneuverability and lateral thrust generation without excessive complexity.
Solution Approach 2:
The patent extends nozzle deflection capability from single-axis rotation to multi-dimensional movement using gimbals. This allows nozzles to pivot in both longitudinal and lateral directions, creating additional degrees of freedom for thrust vector control and significantly improving maneuverability.
3Force
If single nozzle configuration is used, then device simplicity is maintained, but ability to generate substantial lateral thrust and vary net axial thrust is limited
Solution Approach 1:
The patent divides the thrust generation system into multiple independent nozzles (typically three or more) arranged in a specific configuration. Each nozzle can be independently controlled and deflected, allowing the system to generate substantial lateral thrust and vary net axial thrust by coordinating the individual nozzle contributions.
Solution Approach 2:
The patent combines multiple nozzles with different orientations and control mechanisms into a unified assembly body. This merging of multiple thrust vectors enables the system to achieve complex force requirements, including large lateral thrust components and variable axial thrust, while sharing common structural support and control infrastructure.
4Productivity
If fixed nozzle orientation is used, then control system simplicity is maintained, but velocity profile optimization across flight envelope is limited
Solution Approach 1:
The patent employs controllable nozzle assemblies that can dynamically adjust their orientation relative to the air vehicle body. This dynamic capability allows the nozzle system to optimize velocity profiles across different flight conditions and altitudes by directing thrust vectors to match the required flight path and velocity requirements.
Solution Approach 2:
The patent incorporates control systems that monitor flight conditions and adjust nozzle orientation accordingly. This feedback mechanism enables the system to optimize velocity profiles by continuously adapting nozzle directions based on real-time flight data, altitude, and desired performance 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
This design enhances the air vehicle's maneuverability and efficiency by allowing for a wide range of thrust directions, optimizing velocity profiles, and simplifying control systems, particularly useful at high altitudes where conventional control surfaces are ineffective.
Implementation Method 1
each nozzle is arranged to direct the received exhaust gases in a direction corresponding to the nozzle axis at the exit of the nozzle
Data Source
Figure 1a~1d
Figure 1e~1h
Figure 2a~2b
AI summary
The invention provides an exhaust nozzle assembly 200 for an air vehicle, comprising an assembly body 202, defining one or more openings 300 for receiving exhaust, and a plurality of nozzles 210a, 210b, 210c, 210d, each nozzle being arranged to receive exhaust gases at an entrance 240 of the nozzle, and exhaust those exhaust gases from an exit 250 of the nozzle, wherein at least one of the plurality of nozzles is rotatably mounted to the assembly body and rotatable with respect to the assembly body between a first position 214 and a second position 217, wherein a variation of the angle 216 of a nozzle axis at the exit of the rotatably mounted nozzle, between the first and second positions, is at least 25 degrees. The invention also provides other exhaust nozzle assemblies, air vehicles and methods of manufacturing or controlling an air vehicle.