Segmented Forebody Bleed Actuation for Vortex Load Control
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Solution Overview
Problem
Existing technologies struggle to effectively control aerodynamic loads on aircraft and missiles due to the asymmetric evolution and detachment of forebody vortices, which cause significant side forces and yawing moments, affecting flight stability and maneuverability.
Innovation Solution
A system with an outer and inner shell, each having apertures, and an actuator that controls the rotational alignment of the inner shell relative to the outer shell to alter aerodynamic bleed through the apertures, using motors, inflatable actuators, or piezoelectric plates to manage fluid flow and vortex dynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If aerodynamic bleed is used to control forebody vortices, then side forces and yawing moments are reduced, but the complexity of the actuation system increases
Solution Approach 1:
The aerodynamic bleed system is segmented into multiple independently controllable actuators distributed around the forebody. Each actuator can be controlled individually to address specific vortex asymmetries, allowing precise control of side forces and yawing moments while maintaining system modularity and manageable complexity
Solution Approach 2:
The bleed actuation system employs dynamic control where the magnitude and timing of bleed flow are continuously adjusted based on real-time vortex behavior and flight conditions. This dynamic adaptation allows the system to effectively counter asymmetric vortex evolution without requiring excessive actuator complexity
2Stability of the object's composition
If azimuthally-controlled aerodynamic bleed is implemented, then flight stability is improved, but the device complexity increases
Solution Approach 1:
The azimuthally-controlled bleed system incorporates feedback mechanisms that monitor vortex asymmetry and flight stability parameters, then adjust bleed flow distribution accordingly. This closed-loop control achieves enhanced flight stability while keeping the control system complexity manageable through intelligent feedback-based actuation
Solution Approach 2:
The system deliberately introduces asymmetric bleed flow patterns to counteract asymmetric vortex development. By applying aerodynamic bleed asymmetrically across different azimuthal positions on the forebody, the system stabilizes flight conditions without requiring complex symmetric actuation mechanisms
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 effectively stabilizes flight by nullifying side forces and yawing moments, enabling precise control of aerodynamic loads and enhancing maneuverability by altering vortex patterns and fluid flow characteristics.
Implementation Method 1
an actuator configured to control a rotational alignment of the inner shell and the outer shell to alter aerodynamic bleed through at least a portion of at least one aperture of the outer shell
Implementation Method 2
The interactions between the actuation and the cross flow and their coupling to the stability of the near wake were investigated... asymmetric rollup of the forebody counter-rotating vortices at high angles of attack induces corresponding strong side forces
Data Source
AI summary
The present disclosure generally relates to systems and methods for controlling aerodynamic loads on an aerostructure. The present disclosure can include a system including an outer shell, the outer shell including at least one aperture, and an inner shell having an aperture therethrough. The at least one aperture of the outer shell can be part of an array of apertures azimuthally distributed on the outer shell. The system can further include an actuator configured to control a rotational alignment of one of the inner shell and the outer shell to alter aerodynamic bleed through a portion of the at least one aperture of the outer shell. The actuator can be configured alter the rotational alignment of the inner shell and the outer shell based at least in part on a desired steering direction of the aerostructure.