Dynamic Airspeed Reference Control for Landing Approach Throttling
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Solution Overview
Problem
Current aircraft control systems face inaccuracies in airspeed reference values during landing approaches due to unpredictable weather conditions, requiring manual adjustments by pilots, which can be arbitrary and not optimal.
Innovation Solution
A method and system that utilize a processing circuit to calculate a dynamic airspeed reference value by integrating airspeed error values with programmed error values, using thresholds and asymmetric characteristics to adapt the airspeed reference in real-time to environmental changes, thereby improving the accuracy and reliability of automatic throttling systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a fixed airspeed reference value is used during landing approach, then the automatic throttling system operates simply, but the airspeed reference becomes inaccurate when weather conditions change
Solution Approach 1:
The patent transforms the static airspeed reference value into a dynamic one that automatically adapts to changing weather conditions. The system continuously monitors actual airspeed and weather parameters, then dynamically adjusts the reference value through programmed error values that account for wind changes and turbulence, eliminating the need for fixed reference values
Solution Approach 2:
The system implements feedback by continuously comparing actual airspeed measurements with the dynamic reference value. The airspeed error signal is fed back into the system to generate programmed error values, creating a closed-loop control mechanism that automatically corrects for weather-induced deviations without pilot intervention
2Adaptability or versatility
If pilots manually adjust the airspeed reference value, then the system can adapt to weather changes, but the adjustments become arbitrary and may not be optimal
Solution Approach 1:
The system performs self-service by automatically detecting weather-related airspeed deviations and generating appropriate reference value adjustments without pilot intervention. The programmed error values are computed based on actual airspeed measurements and weather parameters, enabling the system to self-correct for wind changes, turbulence, and thermal activity
Solution Approach 2:
The patent changes the airspeed reference parameter dynamically based on measured weather conditions. Instead of manual adjustment, the system computes programmed error values that modify the reference parameter in real-time according to actual airspeed deviations caused by wind, turbulence, and thermal effects, ensuring optimal precision
3Reliability
If the airspeed reference value is increased nominally to account for weather, then safety margin is improved, but the reference value becomes conservative and may not be optimal
Solution Approach 1:
The system replaces conservative static increases with dynamic adjustments that respond to actual weather conditions. The programmed error values provide safety margins only when needed, based on real-time airspeed measurements, allowing optimal approach speeds rather than uniformly conservative values
Solution Approach 2:
Instead of applying excessive conservative increases to all approaches, the system applies partial corrections only when weather conditions actually cause airspeed deviations. The programmed error values provide just enough safety margin to counteract measured wind and turbulence effects, avoiding unnecessary conservatism
Data Source
AI summary
A system for an airborne platform includes a sensing device, an automatic throttling system, and a processing circuit. The sensing device is configured to measure a current airspeed of an aircraft. The processing circuit is configured to receive a control input comprising a current airspeed value, an airspeed reference value, a maximum adder threshold, and a minimum adder threshold. The processing circuit is further configured to calculate an airspeed error value based on the control input. The processing circuit is further configured to determine a programmed error value based on the calculated airspeed error value. The processing circuit is further configured to calculate an adder value by applying an integration function to the determined programmed error value and to determine a dynamic airspeed reference value based on the calculated adder value. The processing circuit is further configured to transmit the dynamic airspeed reference value to the automatic throttling system.