Aircraft Recovery Flight Path Calculation via Dynamic Angle Integration
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Solution Overview
Problem
High-performance aircrafts require significant computational power to calculate and compare zenith and nadir recovery flight paths to avoid ground collisions, leading to potential contradictions and increased risk during evasive maneuvers.
Innovation Solution
A method that calculates a single recovery flight path that turns sideways based on the dive and roll angles, reducing the need for computational power by integrating zenith and nadir paths, eliminating the need to calculate and compare two separate paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If two separate recovery flight paths (zenith and nadir) are calculated and compared, then the reliability of collision avoidance is improved, but the computational power requirement increases significantly
Solution Approach 1:
The patent merges the calculation of zenith and nadir recovery flight paths into a single unified calculation that determines an intermediate flight path based on the aircraft's current dive angle and roll angle. This eliminates the need to calculate and compare two separate paths, significantly reducing computational power requirements while maintaining collision avoidance reliability through continuous adaptation to the aircraft's actual attitude.
Solution Approach 2:
The invention introduces a dynamic calculation approach where the recovery flight path is continuously adjusted based on the aircraft's instantaneous dive angle and roll angle. Instead of pre-calculating fixed zenith and nadir paths, the system dynamically determines the optimal intermediate path, allowing the flight path to adapt in real-time to changing aircraft attitudes without requiring multiple separate calculations.
2Adaptability or versatility
If two different recovery flight paths are calculated and compared, then the adaptability to different dive scenarios is improved, but the device complexity increases
Solution Approach 1:
The patent creates a universal calculation system that handles all dive scenarios (both zenith and nadir cases) through a single unified algorithm. The system uses the aircraft's current dive angle and roll angle as inputs to determine the appropriate intermediate flight path, making the calculation device versatile across all scenarios without requiring separate calculation modules for different flight path types.
Solution Approach 2:
The invention changes the approach from calculating multiple discrete flight paths to continuously adjusting a single flight path based on parameter changes in dive angle and roll angle. By using these angular parameters to dynamically determine the intermediate path, the system achieves adaptability to different dive scenarios while simplifying the calculation device structure.
3Loss of time
If the nadir recovery flight path is used for steep dives, then the response time is improved, but the risk of ground collision increases due to steeper initial descent
Solution Approach 1:
The patent introduces an intermediate flight path that serves as a mediator between the zenith and nadir recovery paths. This intermediate path provides a balanced solution that responds quickly like the nadir path while avoiding its excessive initial descent, thereby reducing ground collision risk. The intermediate path is determined by the aircraft's current attitude parameters, allowing it to function as an adaptive mediator that optimizes both response time and safety.
Data Source
AI summary
The invention relates to a method for calculating a flight path avoiding a collision with the ground when an aircraft dives towards the ground. The method includes receiving signals including information of a dive angle of the aircraft in relation to the imaginary ground plane, and a present roll angle of the aircraft, and calculating a flight path that avoids collision with the ground on the basis of the information. The calculation includes calculating a need for rolling the aircraft based on the present roll angle, and calculating a need for changing the direction of the velocity vector of the aircraft so that the change has a component in an upward direction in relation to the reference frame of the aircraft. The calculation of the need for rolling the aircraft is also based on the dive angle so that the calculated flight path turns sideways when the dive angle surpasses a specified dive angle and when the present roll angle is larger than zero degrees, and so that the flight path continues in a forward direction when the dive angle is below the specified dive angle. The invention also relates to a ground collision calculating unit, a computer program, and a computer readable medium.