Autonomous Flight Mode Selection for Low-Altitude Sensor Dead Zones
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Solution Overview
Problem
Existing electric aircraft systems face inaccuracies in altitude sensing near the ground, leading to potential catastrophic damage during takeoff, landing, and flight, due to 'dead zones' in altitude sensor readings.
Innovation Solution
A system and method for autonomous flight control with mode selection in electric aircraft, utilizing an altitude-related sensor and computing device to detect altitude values, determine flight modes, and automatically enact aircraft adjustments, thereby overcoming sensor inaccuracies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single altitude sensor is used, then the device complexity is reduced, but the measurement precision deteriorates near the ground due to dead zones
Solution Approach 1:
The patent divides the altitude measurement function into multiple sensors with different measurement ranges. One sensor (e.g., ultrasonic) is optimized for low altitude measurements, while another sensor (e.g., barometric) handles higher altitudes. This segmentation allows each sensor to operate in its optimal range, eliminating the dead zone problem while keeping the overall system manageable.
Solution Approach 2:
The patent implements a multi-functional sensor system where different sensors serve different altitude ranges. The system can switch between or combine readings from multiple sensors depending on the current altitude, making the system universally applicable across the entire flight envelope while maintaining high precision in each specific range.
2Measurement precision
If multiple sensors are used to cover different altitude ranges, then the measurement precision is improved, but the device complexity increases
Solution Approach 1:
The patent merges the functionality of multiple sensors into a unified altitude measurement system. The computing device integrates data from multiple sensors, automatically selecting or combining readings based on altitude range. This merging approach maintains high measurement precision across all altitudes while managing system complexity through centralized control logic.
Solution Approach 2:
The patent implements dynamic sensor selection and switching based on current altitude conditions. The system adaptively changes which sensor is active or how sensor data is weighted, optimizing measurement precision for the current flight phase while minimizing the computational burden by only processing relevant sensor data at any given time.
3Reliability
If autonomous flight control with mode selection is implemented, then the reliability is improved during critical phases, but the device complexity increases due to additional computing requirements
Solution Approach 1:
The patent implements preliminary action by pre-defining flight modes and altitude thresholds for different phases of flight (takeoff, landing, cruise). The computing device is programmed with predetermined response protocols for each mode, allowing it to automatically execute appropriate control actions when entering specific altitude ranges, thereby improving reliability without requiring complex real-time decision-making algorithms.
Solution Approach 2:
The patent employs feedback mechanisms where the computing device continuously monitors altitude sensor readings and automatically adjusts flight mode based on current conditions. This closed-loop control system improves reliability by ensuring the aircraft responds appropriately to altitude changes during critical phases, while the feedback logic remains relatively simple by relying on predefined thresholds and mode transitions.
Data Source
AI summary
A system and method for autonomous flight control with mode selection an electric aircraft is illustrated. The system comprises an altitude-related sensor and a computing device. The altitude-related sensor is coupled to the electric aircraft and is configured to detect an altitude value. The computing device is communicatively connected to the altitude-related sensor and is configured to receive the altitude value from the altitude-related sensor, to determine a flight mode as a function of the altitude value and an altitude threshold, to determine an aircraft adjustment as a function of a determine flight mode, and to generate an autonomous function configured to enact the determined flight mode and an aircraft adjustment automatically.