Aircraft Takeoff Pitch Guidance With Airspeed Error Transition
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Solution Overview
Problem
Current aircraft guidance systems during takeoff lack efficiency in transitioning from pitch target mode to airspeed error mode, which affects the accuracy and reliability of pitch guidance, impacting takeoff field length and overall aircraft performance.
Innovation Solution
A method and system that transition takeoff pitch guidance from a pitch target mode to an airspeed error mode based on detected transition events, such as weight-off-wheels condition, with time delays and rate changes in pitch targets, using aircraft operating parameters to adjust pitch guidance dynamically.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If pitch guidance is provided using a fixed pitch target mode during takeoff, then the guidance system is simple to operate, but the accuracy and reliability of pitch guidance deteriorates when aircraft conditions change
Solution Approach 1:
The pitch guidance system dynamically transitions between pitch target mode and airspeed error mode based on aircraft conditions (weight-off-wheels detection). This allows the system to adapt to changing aircraft parameters during takeoff, improving reliability without requiring the pilot to manually adjust complex settings
Solution Approach 2:
The guidance system automatically detects transition events (weight-off-wheels) and self-manages the mode transition from pitch target to airspeed error mode. This reduces the cognitive burden on the pilot while maintaining accurate pitch guidance throughout the takeoff phase
2Speed
If the pitch target is changed rapidly during takeoff, then the response to aircraft conditions is fast, but the risk of tail strike increases
Solution Approach 1:
The system prepares for mode transition by monitoring aircraft conditions (weight-off-wheels detection) before the actual pitch target change is needed. This preliminary detection allows for smoother transitions and prevents abrupt pitch changes that could cause tail strikes
Solution Approach 2:
The guidance system implements protective measures by transitioning to airspeed error mode after weight-off-wheels detection, which naturally limits excessive pitch rates. This cushioning effect prevents the harmful scenario of rapid pitch changes that could lead to tail strikes
3Productivity
If pitch guidance is provided without mode transition, then the system is easy to operate, but the takeoff field length increases
Solution Approach 1:
The system automatically transitions between guidance modes based on aircraft conditions, eliminating the need for pilot intervention. This self-managing approach improves takeoff performance through optimal pitch control while maintaining ease of operation
Solution Approach 2:
The dynamic mode transition from pitch target to airspeed error mode optimizes pitch control during different phases of takeoff. This improves takeoff field length performance while the automatic nature of the transition preserves operational simplicity
Data Source
AI summary
The present disclosure provides methods and system for providing takeoff pitch guidance for an aircraft. Takeoff pitch guidance for the aircraft is provided in a pitch target mode at a time of takeoff. The pitch target mode corresponds to determining pitch as a function of a target pitch based on aircraft operating parameters. A transition event is detected while in the pitch target mode. The takeoff pitch guidance for the aircraft is transitioned from the pitch target mode to an airspeed error mode after the transition event is detected and the takeoff pitch guidance is provided in the airspeed error mode. The airspeed error mode corresponds to determining pitch based on a difference between an actual speed and a target speed of the aircraft.