Fluid-Vectoring Nozzle Yaw Control Without Vertical Stabilizers
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Solution Overview
Problem
Current flight control systems for aircraft, particularly those aiming for stealth capabilities, face challenges in minimizing radar cross-section while effectively controlling yaw and deceleration without relying on vertical stabilizers or inefficient drag mechanisms.
Innovation Solution
A fluid-vectoring system comprising first and second fluid passageways with control units that manage environmental fluid flow to achieve forward flight, left and right turns, and braking configurations, utilizing door positions to control airflow and induce necessary drag forces without vertical stabilizers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If vertical stabilizers are used for yaw control, then directional control is achieved, but radar cross-section increases
Solution Approach 1:
The patent removes the vertical stabilizer from the aircraft configuration entirely, extracting the problematic component that increases radar cross-section. Yaw control functionality is then achieved through alternative means (fluid-vectoring system using engine exhaust flow), eliminating the radar signature issue while maintaining directional control capability
Solution Approach 2:
The engine exhaust system is given multiple functions: it provides thrust for forward motion and simultaneously serves as the actuator for yaw control through differential thrust or flow direction. This eliminates the need for separate control surfaces like vertical stabilizers, reducing radar cross-section while maintaining control functionality
2Speed
If drag mechanisms are used for deceleration, then speed control is achieved, but energy efficiency decreases
Solution Approach 1:
The patent utilizes the pneumatic system (engine exhaust flow) to achieve deceleration control. By modulating the exhaust flow rate and direction through the fluid-vectoring system, the aircraft can decelerate using the reaction force of the exhaust gases rather than relying on aerodynamic drag, thereby maintaining energy efficiency while achieving speed control
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
Enables efficient directional control and deceleration of aircraft without vertical stabilizers, reducing radar cross-section and enhancing stealth capabilities while maintaining effective flight control.
Implementation Method 1
a first flow of environmental fluid moves downstream along the axis from an environment surrounding the aircraft, through the first fluid cavity, and to the environment
Implementation Method 2
utilizing door positions to control airflow and induce necessary drag forces without vertical stabilizers
Data Source
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AI summary
A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-weight ratio.