Aircraft VNE Control Unit Using Weight-Based Velocity Profiles
Solution Overview
Problem
Current systems for indicating the Velocity to Never Exceed (VNE) in aircraft capable of hovering provide a default estimate based on air temperature, altitude, and maximum take-off weight, resulting in a reduced flight envelope and increased pilot workload.
Innovation Solution
A control unit and indicator system that calculates the VNE based on actual weight, altitude, and air temperature, using multiple velocity profiles (High_VNE, Medium_VNE, Low_VNE) associated with different weight intervals, to provide a more accurate and dynamic indication of the VNE.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the VNE is indicated based on default estimate (maximum take-off weight), then the indication is simplified, but the flight envelope is reduced and pilot workload increases
Solution Approach 1:
The system dynamically adjusts the VNE indication based on the actual weight of the aircraft, which varies during flight operations. The control unit continuously monitors weight changes and updates the VNE indication accordingly, allowing the system to adapt to changing flight conditions rather than using a static default value.
Solution Approach 2:
The system incorporates feedback mechanisms where the control unit receives weight information from the aircraft's weight and balance system and uses this feedback to adjust the VNE indication. This closed-loop approach ensures that the indicated VNE always reflects the current actual weight of the aircraft, improving both accuracy and reducing pilot workload.
2Measurement precision
If the VNE is indicated based on actual weight, then the flight envelope is enhanced and indication accuracy is improved, but the system complexity increases
Solution Approach 1:
The control unit performs multiple functions: it monitors aircraft weight, calculates VNE based on actual weight, and provides dynamic indications to the pilot. By consolidating these functions into a single control unit that already exists in the aircraft system, the patent avoids adding separate dedicated hardware while still achieving the desired accuracy improvement.
Solution Approach 2:
The control unit utilizes existing weight and balance data from the aircraft's own systems to automatically calculate and display the correct VNE indication. The system serves itself by using the aircraft's inherent weight monitoring capabilities rather than requiring external input or complex additional measurement systems.
Data Source
AI summary
A control unit for an aircraft capable of hovering or for a flight simulation system of the aircraft is described, the control unit is programmed to receive at input at least a first signal associated with real or simulated flight parameters of the aircraft and to provide at output a second signal associated with a forward velocity to never exceed of the aircraft; the control unit is programmed to process a third signal associated with an actual or simulated weight of the aircraft; to associate plurality of tables to respective intervals of values of the third signal; each table associating a plurality of values of the second signal with a respective first signal; and to process the second signal, based on the table associated with the relative interval of the third signal and the respective first signals.