Aircraft Wing-Body Load Alleviation via Control Surface Dynamics
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Solution Overview
Problem
Aircraft maneuverability is limited by wing size, engine power, and maneuver loads, which increase fuel consumption and decrease flight speed, and existing technologies fail to effectively reduce wing-body loads during maneuvers.
Innovation Solution
A computer-implemented method and apparatus for symmetric and anti-symmetric control of aircraft flight control surfaces, shifting wing air-loads inboard by deploying outboard control surfaces and retracting speed brakes, while filtering high gain feedback commands to reduce maximum loads and maintain roll characteristics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If wing size is increased to reduce wing load, then maneuverability improves, but aircraft weight and fuel consumption increase
Solution Approach 1:
The patent applies dynamic control of flight surfaces (ailerons, spoilers, flaperons) to actively manage wing loads during maneuvers. By dynamically adjusting these surfaces based on maneuver conditions, the system reduces peak loads on the wings, allowing for optimized wing design with lower weight while maintaining maneuverability performance.
2Speed
If wing size is increased to reduce wing load, then maneuverability improves, but fuel consumption increases
Solution Approach 1:
The dynamic adjustment of flight surfaces during maneuvers reduces peak wing loads, enabling more efficient aerodynamic operation. This leads to reduced drag and lower fuel consumption during maneuvering flight compared to aircraft with larger, heavier wings designed to handle higher loads.
3Speed
If maneuver loads on wings are increased to improve maneuverability, then aircraft responsiveness improves, but structural strength requirements and weight increase
Solution Approach 1:
The flight control system performs preliminary action by anticipating high-load maneuver conditions and pre-adjusting flight surfaces to optimize load distribution. This proactive control reduces peak structural loads on the wings during maneuvers, allowing for reduced structural strength requirements and lower aircraft weight while maintaining responsive maneuvering capability.
4Reliability
If control surfaces are rapidly deployed to reduce wing loads, then load alleviation effectiveness improves, but control system complexity and response time requirements increase
Solution Approach 1:
The patent employs existing multi-functional flight control surfaces (ailerons, spoilers, flaperons) that serve both primary flight control functions and wing load alleviation functions. This universal use of existing components achieves load reduction effectiveness without adding significant control system complexity or requiring dedicated load-alleviation hardware.
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 solution reduces wing-body loads, allowing for increased maneuverability, reduced fuel consumption, and lighter airframe structures, enhancing aircraft performance and efficiency without affecting handling qualities or requiring special training or hardware.
Implementation Method 1
Control surfaces, also referred to as flight controls or actuators, are airfoils that deflect air in one direction and cause an aircraft to move in the opposite direction
Implementation Method 2
In response to initiation of a positive gravity maneuver, airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform the positive gravity maneuver
Implementation Method 3
In response to a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads
Data Source
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Figure 5
AI summary
A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.