Vortex-Guided Flying Body Engine for Low-Energy Thrust
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing engines for flying bodies, such as aircraft, lack scalability and efficiency in thrust generation, particularly in providing both lift and propulsion, and often require high energy expenditure for thrust generation.
Innovation Solution
An engine design featuring a vortex guide element and an air deflecting element that work together to generate thrust, where air is drawn in from below and deflected radially outward, utilizing a supporting vortex to enhance efficiency and scalability, with a radial duct and air exit gap configured for low flow resistance and adjustable thrust control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If conventional engines are used for thrust generation, then lift and propulsion can be provided, but energy consumption is high and scalability is limited
Solution Approach 1:
The patent replaces conventional mechanical thrust generation systems with a vortex-based aerodynamic system. The vortex guide element generates a supporting vortex that provides lift and propulsion through aerodynamic forces rather than traditional mechanical means, significantly reducing energy consumption while maintaining thrust capability
Solution Approach 2:
The patent utilizes changes in vortex parameters (strength, radius, rotation speed) to control thrust generation. By adjusting the vortex guide element's geometry and rotation characteristics, the system can scale thrust output without proportionally increasing energy input, enabling both high efficiency and scalability
2Power
If conventional engines are used, then thrust can be generated, but scalability to wide extent is limited
Solution Approach 1:
The vortex guide element is designed with dynamic characteristics that allow continuous adjustment of vortex strength and distribution. This enables the engine to scale thrust generation across a wide range by dynamically modifying vortex parameters rather than requiring complete system redesign, achieving both high power and scalability
Solution Approach 2:
The vortex-based engine design provides multiple functions including lift generation, propulsion, and stability control through a single integrated system. The supporting vortex simultaneously performs these functions, making the engine adaptable to various flight conditions and scalable across different application sizes
3Force
If air is drawn in from below, then lift and stability are provided, but flow resistance increases
Solution Approach 1:
The vortex guide element employs curved, spiral geometry that smoothly guides air intake from below. This curved path reduces flow separation and turbulence compared to straight or angular intake designs, minimizing flow resistance while maintaining the lift and stability forces generated by the supporting vortex
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 engine achieves efficient and scalable thrust generation with low energy consumption, providing lift and stability through a supporting vortex, allowing for energy-efficient operation and adjustable thrust control.
Implementation Method 1
an annular vortex guide element which, seen in section, has an air inlet opening arranged centrally with respect to a longitudinal central axis of the engine and, at a distance from the air inlet opening, an air outlet opening arranged centrally with respect to the longitudinal central axis
Implementation Method 2
the air outlet opening is overlapped by an air deflecting element which is arranged geodetically above the vortex guide element during intended operation of the engine and which extends radially outwards from the air outlet opening so that it defines with the vortex guide element an air exit gap
Data Source
AI summary
The invention relates to an engine (2) for a flying body (1), with an annular vortex guide element (3) which, seen in section, has an air inlet opening (6) arranged centrally with respect to a longitudinal central axis (4) of the engine (2) and, at a distance from the air inlet opening (6), an air outlet opening (7) arranged centrally with respect to the longitudinal central axis (4), which are connected to one another in terms of flow via an intake duct (5) bounded by the vortex guide element (3) and accommodating an air conveying device (8), wherein the air outlet opening (7) is overlapped by an air deflecting element (9) which is arranged geodetically above the vortex guide element (3) during intended operation of the engine (2) and which extends radially outwards from the air outlet opening (7) so that it delimits with the vortex guide element (3) an air exit gap (11) which is in flow connection with the air outlet opening (7). It is provided that the vortex guide element (3) is in the form of a body of rotation which is formed by rotation about an axis of rotation of a closed curve having a continuous course at least on its radially outer side, and in that the air inlet opening (6) opens directly into an outer environment (19) of the engine (2), so that during intended operation of the engine (2) air is conveyed from the side of the engine (2) facing away from the air deflecting element (9) through the air inlet opening (6) into the intake duct (5). The invention further relates to a method for operating an engine (2) for a flying body (1) as well as a flying body (1) with at least one engine (2).