Multi-Functional Flight Control Surface for Aeroelastic Compensation
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Solution Overview
Problem
Modern aircraft with flexible wings, constructed from lightweight materials, face challenges such as increased drag, structural loads, and aerodynamic inefficiencies due to aeroelastic deflections, which affect fuel consumption and structural integrity, and existing flight control systems are limited in simultaneously addressing multiple objectives like drag optimization, load alleviation, and modal suppression.
Innovation Solution
A multi-functional distributed flight control surface system that uses a combination of sensors and advanced control algorithms to dynamically adjust flight control surfaces, integrating drag minimization, gust load alleviation, and aeroservoelastic mode suppression, allowing for simultaneous achievement of multiple flight objectives while responding to pilot inputs and operational conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If modern engineered materials are used to construct aircraft wings, then weight is reduced and strength is improved, but structural rigidity deteriorates leading to aeroelastic deflections
Solution Approach 1:
The patent applies dynamics by implementing active control systems that continuously adjust flight control surfaces in response to real-time wing deformation measurements. Sensors detect aeroelastic deflections and feed this information to control algorithms that dynamically reposition control surfaces to counteract the deformations, transforming a static rigid structure problem into a dynamic active compensation system.
Solution Approach 2:
The patent implements feedback through sensor systems that monitor wing deformation and structural loads, feeding this information back to the flight control system. The control algorithms process this feedback and adjust control surface positions accordingly, creating a closed-loop system that actively compensates for aeroelastic effects and maintains optimal aerodynamic performance throughout flight.
2Loss of energy
If flight control surfaces are used to counteract aeroelastic deflections, then aerodynamic efficiency is improved, but drag increases due to additional control surface movements
Solution Approach 1:
The patent applies partial action by implementing control strategies that make adjustments only when and where necessary to counteract aeroelastic deflections. Rather than continuously moving control surfaces, the system uses sensor-driven algorithms to apply minimal corrective actions only when deflections exceed acceptable thresholds, reducing unnecessary drag while maintaining aerodynamic efficiency.
Solution Approach 2:
The patent employs parameter changes by dynamically adjusting control surface deflection angles, positions, and timing based on real-time flight conditions and measured wing deformations. The control algorithms optimize these parameters to achieve the minimum necessary control input to counteract aeroelastic effects, thereby minimizing drag penalties while maintaining aerodynamic performance.
3Productivity
If multiple flight control objectives are pursued simultaneously, then overall aircraft performance is improved, but control system complexity increases
Solution Approach 1:
The patent applies universality by designing control surfaces that perform multiple functions simultaneously - they not only control aircraft attitude and direction but also actively counteract aeroelastic deflections and optimize aerodynamic efficiency. The same control surfaces used for conventional flight control are also employed for drag reduction and load alleviation, eliminating the need for separate specialized control mechanisms.
Solution Approach 2:
The patent implements merging by integrating multiple control objectives into a unified control framework. The flight control system simultaneously handles attitude control, aeroelastic compensation, drag optimization, and load alleviation through a single integrated control algorithm that coordinates all control surfaces, reducing overall system complexity compared to having separate independent control systems for each objective.
Data Source
AI summary
A flight control system for an aircraft having a multi-functional flight control surface. The aircraft has at least one multi-functional flight control surface formed by a sequence of flaps. The shape of each multi-functional flight control surface may be configured by a flight control to simultaneously adjust a trajectory of the aircraft in two or more of a pitch direction, a roll direction, and a yaw direction. The flight control for operating said the multi-functional flight control surface responds to both pilot commands and machine-generated commands. The machine-generated commands configure the shape of the surface of each multi-functional flight control surface in real-time based, at least in part, upon a set of flight objectives comprising: (a) minimizing drag of the aircraft, (b) aeroelastic modal suppression for the aircraft, and (c) maneuver load alleviation in the aircraft.