Aeronautical Control System with Local Gain Compensation
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Solution Overview
Problem
Complex aeronautical equipment devices, such as turboprop engines, face challenges in precise regulation due to numerous variable parameters and non-linear relationships, making it difficult to determine an acceptable transfer function for the regulator, especially when involving non-linearities.
Innovation Solution
A regulation system with a compensation module and a local gain determination module that accounts for the inverse of the local gain to compensate for non-linearities, allowing for control of the regulated parameter by freeing it from these complexities, and includes a corrector and a dynamic compensation chain to achieve desired dynamics and precision.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If conventional regulation techniques are used for complex aeronautical devices with multiple variable parameters, then the regulator design becomes complicated or impossible, but the device still requires precise and safe regulation
Solution Approach 1:
The patent segments the regulator into multiple independent modules: a differentiation module that calculates the error derivative, a gain module that provides variable gain based on operating conditions, and a compensation module that handles non-linearities. This segmentation allows each module to be designed and tuned independently, making the overall regulator design manageable despite the complexity of the controlled device
Solution Approach 2:
The patent implements a dynamic regulation approach where the gain is not fixed but varies according to the operating conditions of the device. The gain module adjusts the amplification factor based on real-time parameters, allowing the regulator to adapt to changing conditions and maintain precision across different operating regimes without requiring a completely different design for each condition
2Manufacturing precision
If the device has numerous variable parameters and non-linear relationships, then conventional transfer function determination becomes inapplicable, but precise control is still required
Solution Approach 1:
The patent implements a derivative feedback mechanism where the differentiation module continuously calculates the rate of change of the error signal. This feedback on the error derivative allows the system to respond to changing conditions in real-time, effectively handling non-linear relationships without requiring a complete transfer function model of the complex device
Solution Approach 2:
The patent changes the regulatory approach from using a fixed transfer function to using variable parameters including time-varying gain and derivative-based error correction. This parameter adaptation allows the regulator to maintain effectiveness despite the non-linear and time-varying nature of the controlled device, eliminating the need for conventional transfer function determination
3Ease of manufacture
If a fixed gain regulator is used, then the design is simple, but it cannot adapt to varying operating conditions and non-linearities
Solution Approach 1:
The patent transforms the static gain into a dynamic parameter that varies with operating conditions. The gain module receives input signals representing the current operating state and adjusts the gain accordingly, enabling the simple regulator structure to adapt to varying conditions and non-linearities without becoming complex
Data Source
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AI summary
The invention concerns a control system (1) for controlling a controlled parameter (Y) of an aeronautical equipment device (2), said controlled parameter being governed by an operating law linking said controlled parameter to a command (U) and to a plurality of input parameters (X1, X2, X3), said control system comprising a control loop controlling said controlled parameter to a setpoint (yc) by means of the control of the device by the command, the system comprising an operating law compensation module (7) and a determination module (8) determining a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of said controlled parameter in response to a variation in said command in a stabilised operating regime of said operating law, said operating law compensation module using the inverse of said local gain.