Aircraft Anemometric Estimation from Actuator Load and Surface State
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Solution Overview
Problem
Current aircraft systems rely on the pilot static system and air data computer for determining anemometric parameters like calibrated airspeed, angle of attack, and sideslip angle, leading to significant consequences when these systems fail, including loss of autopilot functionality and inaccurate flight envelope protection.
Innovation Solution
A method and system that estimate anemometric parameters by obtaining indications of secondary surface states and actuator positions, using lookup tables generated during a learning phase, to provide reliable calculations of load applied on actuators, thereby determining and displaying or recording the necessary parameters even in the absence of the pilot static system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional pilot static system and air data computer are used for determining anemometric parameters, then measurement precision is maintained under normal conditions, but reliability deteriorates significantly when these systems fail
Solution Approach 1:
The patent introduces intermediary elements (load estimation algorithms, lookup tables, and AI-based processing systems) that mediate between available sensor data (actuator positions, surface states) and the desired anemometric parameters. These intermediaries enable reliable estimation by transforming indirect measurements into accurate parameter predictions even when traditional direct measurement systems fail
Solution Approach 2:
The patent creates a virtual copy of the air data computer functionality through software-based estimation algorithms. By replicating the essential computation functions using alternative data sources (actuator positions, load estimates) and processing methods (lookup tables, AI models), the system maintains measurement precision through a software-based counterpart when hardware systems fail
2Device complexity
If pilot static system is lost, then system complexity is reduced, but flight envelope protection and autopilot functionality are lost
Solution Approach 1:
The patent enables the flight control system to serve itself by using its own internal state information (actuator positions, surface states) to estimate anemometric parameters. This self-service capability allows the system to maintain flight envelope protection using readily available data from the flight control actuators themselves, eliminating dependence on external air data computers
Solution Approach 2:
The patent makes the flight control system multi-functional by enabling it to perform both its primary control function and anemometric parameter estimation function using the same hardware infrastructure. The flight control actuators and sensors serve dual purposes: controlling aircraft surfaces and providing data for airspeed, angle of attack, and sideslip angle estimation
3Reliability
If AI-based lookup tables and load estimation methods are implemented, then reliability is improved during system failures, but device complexity increases
Solution Approach 1:
The patent applies preliminary action by pre-computing and storing lookup tables during a learning phase before actual flight operations. This advance preparation of computational models and data structures enables rapid, reliable parameter estimation during flight without requiring complex real-time computations, thus improving reliability while managing operational complexity
Solution Approach 2:
The patent replaces traditional mechanical and hardware-based air data measurement systems with software-based estimation algorithms and AI models. By substituting physical air data computers with computational methods using available flight control data, the system improves reliability through software redundancy while the complexity is managed through algorithmic efficiency
Data Source
AI summary
A method and system for determining an estimation of an anemometric parameter of an aircraft. The anemometric parameter including an angle of attack, a sideslip angle and a calibrated airspeed. The method including obtaining an indication of a secondary surface state of the aircraft; obtaining a position indication of a horizontal primary surface; obtaining a load applied estimation on a corresponding actuator using the position indication of the horizontal primary surface and the position of the corresponding actuator; accessing a lookup table with the indication of the secondary surface state of the aircraft, the load estimation applied on the corresponding actuator, and the position of the corresponding actuator; obtaining an estimation of the anemometric parameter associated with the horizontal primary surface; providing the estimation of the anemometric parameter associated with the horizontal primary surface and wherein the lookup table is generated during a learning phase.