Aircraft Rear Propulsion Speed Synchronization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing management of rear propulsion systems in aircraft leads to disruptions and operability issues with lateral propulsion systems, as the power supplied by the rear system is not optimally controlled, affecting fuel consumption and system longevity.
Innovation Solution
A method to adjust the rotation speed of the rear propulsion system based on specific formulas relative to the lateral propulsion systems' speed during different flight phases, such as cruise, climb, idle, and take-off, to synchronize and optimize the performance of both systems, while limiting fuel consumption and preventing surge phenomena.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the power of the rear propulsion system is maximized to reduce fuel consumption, then fuel efficiency is improved, but disruptions and surge problems of the lateral propulsion systems occur
Solution Approach 1:
The patent applies dynamics by making the rotation speed of the rear propulsion system adjustable and variable according to flight phase, rather than operating at constant power. The control method dynamically adapts the rear propulsion system's contribution to match lateral system capabilities, resolving the contradiction between maximizing fuel efficiency and preventing disruptions.
Solution Approach 2:
The patent changes the operational parameters of the rear propulsion system by establishing specific rotation speed relationships (N3=a*N2) different for each flight phase. This parameter adjustment allows the system to optimize fuel consumption during stable phases while limiting power contribution during phases vulnerable to disruptions.
2Productivity
If the rotation speed of the rear propulsion system is increased to improve propulsion efficiency, then propulsion performance is improved, but surge problems and disruptions of lateral propulsion systems worsen
Solution Approach 1:
The patent applies preliminary action by pre-defining rotation speed relationships and control strategies for each flight phase before operation. By establishing the formula N3=a*N2 and determining appropriate constant values in advance for each phase, the system prevents surge problems before they occur rather than reacting to them.
Solution Approach 2:
The control method incorporates feedback by continuously monitoring the flight phase and adjusting the rear propulsion system's rotation speed accordingly. The system uses information about lateral propulsion system operation to regulate rear system power, creating a closed-loop control that prevents harmful surge effects.
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 method optimizes the performance and longevity of both rear and lateral propulsion systems by synchronizing their speeds, reducing fuel consumption, and preventing disruptions during various flight phases, thereby enhancing overall aircraft efficiency and reliability.
Implementation Method 1
the boundary layer is formed at the surface of the fuselage. In a boundary layer, the maximum velocity of the air flow is equal to 99% of the free velocity. Consequently, the air flow of the boundary layer is displaced more slowly than the free air flow.
Data Source
AI summary
A method for managing the propulsive power of an aircraft, the aircraft extending longitudinally along an axis X from the rear forwards and comprising at least two lateral propulsion systems each comprising a fan, each lateral propulsion system having a fan rotation speed N2 and at least one rear propulsion system configured to ingest a boundary layer of said aircraft, the rear propulsion system comprising a fan having a fan rotation speed N3, the management system comprising, during a cruising phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system according to the following formula N3=a*N2 in which a is a constant.