Aircraft Rear End Section With Boundary Layer Ingestion Thrust Vectoring
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft designs fail to effectively combine boundary layer ingestion (BLI) propulsion with thrust vectoring, limiting propulsive efficiency and increasing energy consumption.
Innovation Solution
A rear end section for an aircraft featuring a v-tail configuration with a thruster assembly that ingests fuselage boundary layer air and uses a control surface to divert the engine slipstream for vector thrust, incorporating an array of propulsion devices and a casing to manage airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a conventional engine is used for propulsion, then the aircraft can achieve basic thrust, but the propulsive efficiency is low and energy consumption is high
Solution Approach 1:
The propulsion system is divided into multiple independent propulsion devices (fans or rotors) arranged in an array, allowing each device to independently ingest boundary layer air and generate thrust. This segmentation enables optimized airflow management and improved overall propulsive efficiency while reducing energy consumption compared to a single conventional engine.
Solution Approach 2:
The system utilizes pneumatic principles by employing fans or rotors to ingest and compress boundary layer air, converting it into useful thrust. The airflow is managed through ducts and control surfaces, utilizing fluid dynamics to optimize the conversion of kinetic energy from the boundary layer into propulsive force, thereby improving energy efficiency.
2Productivity
If a BLI engine is used to ingest boundary layer air, then propulsive efficiency increases, but thrust vectoring capability is limited
Solution Approach 1:
The propulsion array is designed to perform multiple functions: it can operate in conventional forward thrust mode by ingesting boundary layer air, and it can also provide thrust vectoring by deflecting the exhaust flow through control surfaces. This multi-functionality allows the same propulsion system to achieve both improved propulsive efficiency and enhanced adaptability for various flight control requirements.
Solution Approach 2:
The system incorporates movable control surfaces that can dynamically adjust the exhaust flow direction from the propulsion devices. This dynamic capability allows the thrust vector to be adjusted in real-time, providing both forward propulsion and vectoring control, thereby enhancing the versatility of the BLI engine while maintaining improved propulsive efficiency.
3Weight of stationary object
If the empennage size is reduced to minimize weight and drag, then the aircraft becomes more efficient, but the available space for propulsion devices is limited
Solution Approach 1:
The propulsion devices are integrated within the rear fuselage structure, utilizing the available volume efficiently. The array of fans or rotors is arranged to fit within the constrained space of the modified empennage, with ducts and control surfaces nested around the propulsion elements. This nesting approach allows the propulsion system to be compact while maintaining adequate space for all necessary components, thereby reducing overall weight and drag.
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 solution enhances propulsive efficiency, reduces fuel consumption, and minimizes the size and weight of the empennage by leveraging BLI for both propulsion and thrust vectoring.
Implementation Method 1
a propulsion device installed to ingest the air from the boundary layer formed over the fuselage of the aircraft
Implementation Method 2
the air outlet is designed for directing the airflow exhausted from the propulsion device towards the control surface, to divert said airflow in order to provide vectoring thrust for the aircraft
Data Source
Figure 1~2
Figure 3~4
AI summary
The invention refers to a rear end section (1) for an aircraft, having a fuselage (4), a v-tail (2), and a thruster assembly (3) comprising: at least one propulsion device (5) installed to ingest and consume air forming a fuselage boundary layer, a control surface (6) attached at the rearmost section of the rear end, and a casing (7) covering at least part of the propulsion device (5) such that an air inlet (8) and an air outlet (9) are defined between the casing (7) and the propulsion device (5), the air inlet (8) being designed for the passage of the fuselage boundary layer towards the propulsion device (5), and the air outlet (9) being designed for directing the airflow exhausted from the propulsion device (5) into the control surface (6), to divert said airflow and provide vectoring thrust for the aircraft.