Aircraft Motion Observer Torque Control via State Inconsistency
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Solution Overview
Problem
Monitoring and adjusting the states of flight components to optimize aircraft torque during flight is challenging due to the complexity of aircraft motion and the impact on performance.
Innovation Solution
A system and method for an aircraft motion observer that includes a command model, actuator model, and plant model, which detect predicted and measured state data of flight components, generate performance data, and apply torque to adjust inconsistencies, ensuring optimal performance by matching predicted and actual states.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a motion observer system with multiple models is implemented to monitor flight component states, then measurement precision and reliability are improved, but device complexity increases
Solution Approach 1:
The motion observer system is segmented into distinct functional models: a command model for detecting predicted state data, an actuator model for generating performance data, and a plant model for generating inconsistency data. Each model handles a specific aspect of the monitoring task, allowing the complex measurement function to be divided into manageable, specialized components that improve precision without overwhelming system complexity.
Solution Approach 2:
The command model acts as an intermediary between the pilot inputs and the actuator model, translating measured state data into predicted state data. This intermediary layer processes and refines the raw input data before it reaches the performance calculation stage, improving measurement precision through systematic data transformation and validation.
2Stability of the object's composition
If real-time monitoring and adjustment of flight component states is performed, then flight stability and performance are improved, but loss of time for data processing increases
Solution Approach 1:
The command model performs preliminary processing of pilot inputs by generating predicted state data before the actual actuation occurs. This preliminary action prepares the expected state information in advance, allowing the actuator and plant models to quickly compare predicted versus actual states without extensive real-time computation, thus maintaining flight stability while reducing processing time delays.
Solution Approach 2:
The system implements continuous feedback by comparing the predicted state data from the command model with the actual performance data from the actuator model. The plant model generates inconsistency data that feeds back into the control system, enabling real-time stability adjustments. This feedback loop maintains flight stability through systematic correction while optimizing processing efficiency by focusing computational resources on detecting and correcting deviations rather than continuous full-state analysis.
3Productivity
If torque adjustment is applied based on inconsistency data, then flight efficiency is improved, but device complexity increases
Solution Approach 1:
The motion observer system performs self-service by automatically generating inconsistency data and applying torque adjustments without requiring external intervention. The plant model continuously monitors the difference between predicted and actual states and autonomously generates correction commands, enabling the system to self-regulate and optimize flight efficiency while managing its own control complexity through automated decision-making algorithms.
Data Source
AI summary
A command model connected to plurality of flight components of an electric aircraft and comprises a circuitry configured to detect a predicted state and a measured state datum, transmit predicted state datum to an actuator model, and transmit measured state datum to a plant model. An actuator model connected to the sensor configured to receive the predicted state datum and generate a performance datum. A plant model connected to the sensor configured to receive measured state datum and performance datum from the actuator model, transmit a feedback path to controller, and generate an inconsistency datum as a function of the measured state datum and the performance datum. A controller communicatively connected to the sensor, wherein the controller is configured to receive the inconsistency datum from the plant model and apply a torque to the aircraft as a function of the inconsistency datum.