Adaptive VTOL Propulsion System with Variable Nozzle Geometry
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Solution Overview
Problem
Designing a propulsion system for Vertical Take-off and Landing (VTOL) aircraft that efficiently transitions between VTOL/hover and cruise phases while minimizing weight and complexity, and achieving high-speed capabilities.
Innovation Solution
A fluidic propulsion system (FPS) that uses a fan or compressor to compress air for thrust augmentation in VTOL and hover phases, and transitions to a turbofan configuration for cruise, allowing for high-speed forward flight and efficient fuel use.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If large engines are used to produce sufficient thrust for VTOL and hover phases, then thrust capability is improved, but weight increases
Solution Approach 1:
The patent employs variable geometry nozzles that dynamically adjust their expansion ratio based on flight phase. During VTOL and hover, the nozzles are configured for maximum thrust output. During cruise, the nozzles transition to a smaller effective area, reducing engine weight requirements. This dynamic adaptation allows the propulsion system to optimize thrust-to-weight ratio across different operating conditions.
Solution Approach 2:
The invention changes the operational parameters of the propulsion system by using the same engine at different power settings and nozzle configurations. The engine operates at high power with expanded nozzles for vertical flight, and at lower power with reduced nozzle area for horizontal flight. This parameter variation enables a single engine to replace what would traditionally require multiple engines of different sizes.
2Productivity
If separate propulsion systems are used for lift and cruise phases, then thrust efficiency is improved, but device complexity increases
Solution Approach 1:
The patent makes the propulsion system universal by enabling a single engine-nozzle system to perform multiple functions: vertical lift, hover, transition, and horizontal cruise. The variable geometry nozzles allow the same engine to efficiently produce thrust in both vertical and horizontal directions, eliminating the need for separate lift engines and cruise engines that would otherwise be required.
Solution Approach 2:
The invention merges the lift propulsion system and cruise propulsion system into a single integrated engine-nozzle assembly. By combining what would traditionally be separate systems into one unified propulsion unit with adjustable geometry, the patent reduces overall system complexity while maintaining the thrust efficiency benefits of specialized propulsion for each flight phase.
3Force
If the propulsion system is sized for VTOL phase, then vertical thrust capability is improved, but cruise efficiency deteriorates
Solution Approach 1:
The variable geometry nozzles dynamically adjust their configuration to optimize exhaust flow for each flight phase. During VTOL, the nozzles expand to maximize vertical thrust. During cruise, the nozzles reduce their effective area and redirect exhaust flow to improve propulsive efficiency and reduce fuel consumption. This dynamic adjustment prevents the energy waste that would occur with fixed-geometry nozzles sized for vertical flight.
4Use of energy by moving object
If engine size is reduced for cruise conditions, then energy efficiency is improved, but VTOL thrust capability deteriorates
Solution Approach 1:
The invention changes the physical parameters of the nozzle geometry to decouple the relationship between engine size and thrust capability. A single engine can produce sufficient VTOL thrust when paired with fully expanded nozzles, while maintaining cruise efficiency through reduced nozzle area during horizontal flight. This parameter change in nozzle geometry allows the engine to effectively scale its output without physical resizing.
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
The FPS system enables efficient thrust augmentation in VTOL and hover, while allowing for high-speed cruise operations with reduced fuel consumption and increased maneuverability, thus addressing the challenges of weight, complexity, and speed in existing VTOL designs.
Implementation Method 1
a source of compression such as a fan or compressor of fluids including air
Implementation Method 2
a dual capability to switch from an augmented thrust in vertical flight (VTOL+hover) and a separate turbofan configuration in cruise
Data Source
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AI summary
A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.