Aircraft Landing Approach Stabilization Flight Path Optimization
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Solution Overview
Problem
Current methods for planning an aircraft's landing approach lack the ability to economically optimize the approach and adapt to predetermined optimization goals and marginal conditions, failing to efficiently adjust the aerodynamic profile configuration to achieve optimal landing performance.
Innovation Solution
A method that defines configuration change conditions and measures on a stabilization flight path section, adjusting the drag-lift ratio of airfoils by changing the overall aerodynamic profile configuration, allowing for real-time adjustments to ensure a final approach flight status is met, including the use of configuration change points, flight statuses, and time specifications to optimize speed profiles and fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the aerodynamic profile configuration is adjusted during the stabilization flight path section, then the drag-lift ratio is optimized and fuel consumption is reduced, but the device complexity and control system requirements increase
Solution Approach 1:
The patent implements dynamic adjustment of the aerodynamic profile configuration during the stabilization flight path section. The configuration change conditions and measures are defined to allow real-time modification of the drag-lift ratio based on flight status, enabling optimal fuel consumption while maintaining adaptability through a program-controlled device that automatically manages the complexity.
Solution Approach 2:
The patent changes physical parameters of the aerodynamic profile configuration during flight. By adjusting configuration parameters such as flap positions and airfoil shapes at defined configuration change points, the drag-lift ratio is optimized for fuel efficiency while the program-controlled device manages the parameter changes systematically.
2Reliability
If real-time adjustments of aerodynamic configuration are implemented, then the final approach flight status is optimized, but the time and complexity of planning the landing approach increase
Solution Approach 1:
The patent performs preliminary definition of configuration change conditions and measures during the planning phase. By pre-defining the stabilization flight path section, configuration change points, and associated measures, the system prepares optimization strategies in advance, reducing real-time decision complexity while ensuring reliable final approach status through pre-planned adaptive adjustments.
3Productivity
If the aerodynamic profile configuration is changed to optimize landing approach, then fuel consumption and flight time are reduced, but the manufacturing precision and operational complexity increase
Solution Approach 1:
The patent employs dynamic reconfiguration of the aerodynamic profile during the stabilization flight path section. By allowing the airfoil configuration to change adaptively based on defined conditions and measures, the system optimizes landing approach efficiency and fuel consumption while the program-controlled device manages the precision requirements through automated control.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enables an economically optimal landing by adjusting the aerodynamic profile configuration in real-time, ensuring the aircraft reaches the required final approach flight status within predefined limits, optimizing flight time, fuel consumption, and thrust usage.
Implementation Method 1
a drag-lift ratio of the airfoils is adjusted due to a changed adjustment of the overall aerodynamic profile configuration of airfoils of the aircraft
Data Source
AI summary
A method and computer program product for planning a landing approach of an aircraft based on an actual position or first nominal position of the aircraft during its approach for landing on a runway, including providing a stabilization flight path section and stabilization region and/or stabilization point defined by an altitude profile by at least one configuration change point in the stabilization flight path section with a change of the overall profile configuration of the airfoils and with a predetermined final approach flight status of the aircraft, and checking or changing position of the at least one configuration change measure in a change and/or the addition of an additional configuration change measure to the stabilization flight path section and by changing a speed profile along the stabilization flight path section so that the aircraft reaches the predetermined final approach flight status in the stabilization region or at the stabilization point.