Rotorcraft Takeoff Pitch Control for Engine Failure Acceleration
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Solution Overview
Problem
Piloting a helicopter during takeoff is challenging, especially with engine failure, as existing systems fail to optimize single-engine performance and adjust takeoff safety speed effectively, leading to insufficient acceleration and climb rates.
Innovation Solution
A method and device that control pitch attitude to vary acceleration profiles during takeoff based on elapsed time and engine state, with distinct acceleration values for normal and single-engine operations, allowing for optimized climb speed achievement and immediate adjustment of takeoff safety speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Extent of automation
If a standard autopilot mode is used for takeoff, then the procedure is automated and certification is easier, but the acceleration is insufficient in single-engine operation
Solution Approach 1:
The patent implements dynamic acceleration profiles that automatically adjust based on engine operation status. The system transitions from a fixed autopilot mode to a dynamic control system that modifies acceleration commands in real-time, applying higher acceleration values when operating on a single engine while maintaining standard profiles for twin-engine operation.
Solution Approach 2:
The invention changes the acceleration parameter dynamically based on engine state detection. The system monitors engine operational status and automatically adjusts the acceleration profile parameters, applying distinct acceleration values (A1, A2 for twin-engine; A3, A4 for single-engine) to optimize performance under different operating conditions.
2Ease of operation
If pitch attitude control is used to manage takeoff, then the procedure is simplified, but full advantage of helicopter performance is not taken
Solution Approach 1:
The patent replaces traditional pitch attitude-based control with a direct acceleration control system. Instead of relying on the pilot to manually manage pitch attitude to optimize performance, the system directly commands acceleration, substituting the mechanical pitch control approach with an automated acceleration management system that optimizes takeoff performance while maintaining ease of operation.
3Stability of the object's composition
If takeoff safety speed is fixed, then the procedure is standardized, but it cannot be optimized for different weights and conditions
Solution Approach 1:
The system implements a dynamic takeoff safety speed that adjusts in real-time based on detected engine operational status and flight conditions. Rather than using a fixed standardized speed, the system dynamically modifies the safety speed threshold to optimize performance for twin-engine versus single-engine operation while maintaining appropriate safety margins.
Data Source
AI summary
The invention relates to a method of piloting a rotorcraft having a plurality of engines for driving at least one lift and propulsion rotor, in which method, so long as the rotorcraft has not reached an optimum climb speed (OCS), a pitch attitude control signal (Upitch) is determined that is adapted so that the rotorcraft accelerates in application of a profile (P1, P2, P3) that varies as a function of the elapsed time and as a function of the operating state of the engines (OEI/AEO).