Hinged Flight Control Surface Structural Model
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The design and testing of actuation systems for aircraft flight control surfaces are complex and computationally intensive, requiring time-consuming and expensive finite element models and physical test rigs, which can be inefficient and costly.
Innovation Solution
A structural model representing a hinged flight control surface system with actuation branches, a massless connector, and a load mass, allowing for efficient modeling and simulation of dynamic behavior, which can also serve as a specification for fabricating a physical test rig.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If finite element models are used for modeling actuation systems, then modeling accuracy is improved, but computational complexity and time consumption increase
Solution Approach 1:
The patent segments the complex finite element model into a simplified structural model with discrete components (actuation branches, massless connector, load mass) that captures essential dynamics without requiring full finite element complexity. This segmentation maintains sufficient accuracy for system identification while dramatically reducing computational burden.
Solution Approach 2:
The patent extracts only the critical dynamic characteristics from the full finite element model, creating a reduced-order structural model that focuses on the essential mass, stiffness, and damping properties needed for control system design and analysis, eliminating unnecessary computational complexity.
2Measurement precision
If finite element models are used for modeling actuation systems, then modeling accuracy is improved, but time consumption increases
Solution Approach 1:
By segmenting the modeling approach into a simplified structural model with explicit mass, stiffness, and damping matrices, the patent eliminates the time-consuming mesh generation and solution processes of full finite element analysis, achieving rapid model development and simulation.
Solution Approach 2:
The patent changes the parameter representation from detailed finite element parameters (mesh density, element types) to aggregated structural parameters (equivalent mass, stiffness, damping) that can be determined analytically or through simple testing, dramatically reducing the time required for model creation and modification.
3Measurement precision
If physical test rigs are developed for testing actuation systems, then testing accuracy is improved, but development cost and time increase
Solution Approach 1:
The patent creates a simplified structural model that serves as a virtual copy of the actuation system, capturing essential dynamic behavior without requiring a full-scale physical replica. This virtual model can be used for initial design validation and system identification before physical testing.
Solution Approach 2:
The patent uses parameter identification techniques to determine equivalent mass, stiffness, and damping values from limited physical tests or operational data, allowing the simplified structural model to accurately represent the physical system without requiring a complex physical test rig.
Data Source
AI summary
Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.