Autogyro Fuselage Stabilizer Extension for Drag Reduction
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Solution Overview
Problem
Gyroplanes face increased air resistance and impaired stability and maneuverability due to turbulence behind the propeller, leading to higher fuel consumption and reduced flight performance.
Innovation Solution
The design incorporates a horizontal stabilizer extension that forms a streamlined outer contour with the fuselage and propeller extension, decoupling vibrations between the horizontal stabilizer and propeller, and using a damping element to maintain constant spacing, thereby reducing turbulence and improving airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the horizontal stabilizer is directly connected to the fuselage behind the propeller, then the stabilizer can be supported structurally, but turbulence arises in the air flow leading to increased air resistance and impaired stability
Solution Approach 1:
A streamlined extension is introduced as an intermediary element between the fuselage and the horizontal stabilizer. This extension acts as a mediator that guides the air flow smoothly from the fuselage to the stabilizer, preventing direct turbulence while maintaining structural support. The extension is spaced from both the fuselage and stabilizer to allow air flow passage, thus resolving the contradiction between structural support and turbulence reduction.
2Ease of operation
If the horizontal stabilizer is positioned behind the propeller for stabilization, then control functions are achieved, but vibrations from the propeller are transferred to the stabilizer impairing flight smoothness
Solution Approach 1:
The streamlined extension serves as a vibration-isolating intermediary between the propeller and horizontal stabilizer. By positioning the extension spaced from both components and allowing air flow to pass through, it prevents direct vibration transfer while maintaining the stabilizer's control functions. The extension absorbs and dampens vibrations before they reach the stabilizer, improving flight smoothness.
3Reliability
If the horizontal stabilizer extension is spaced from the fuselage end, then vibrations are decoupled and airflow is improved, but structural support and positioning become more complex
Solution Approach 1:
The extension is designed with a streamlined, curved contour that tapers smoothly from the fuselage toward the horizontal stabilizer. This aerodynamic shaping not only improves airflow but also provides inherent structural strength, reducing the need for additional complex support structures. The curved form naturally guides air flow while maintaining positional stability.
4Loss of energy
If a streamlined outer contour is formed by spacing the extension from fuselage and stabilizer, then turbulence is reduced and fuel consumption decreases, but manufacturing precision requirements increase
Solution Approach 1:
The extension features a streamlined curved contour that is spaced from both the fuselage and horizontal stabilizer to form a smooth outer contour. This curved design naturally guides air flow with minimal turbulence, significantly reducing drag and fuel consumption. The consistent spacing and aerodynamic shaping achieve energy efficiency while the modular design facilitates manufacturing.
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 configuration results in reduced fuel consumption, enhanced stability, and smoother flight behavior by minimizing turbulence and vibrations, leading to improved flight performance and reduced wear on components.
Implementation Method 1
a rotor (4), which can be arranged in a rotatable manner in the area of the end of the mast and can be set in autorotation by an air flow
Implementation Method 2
The rotor can be displaced by an air flow in autorotation, such that lift of the gyroplane is generated
Implementation Method 3
a propeller (6) that is arranged and drivable in the rear area of the fuselage, which produces the propulsion of the gyroplane
Implementation Method 4
The horizontal stabilizer extension (9), together with the fuselage (2) and the propeller extension (14), forms a streamlined outer contour
Implementation Method 5
This configuration results in reduced fuel consumption, enhanced stability, and smoother flight behavior by minimizing turbulence and vibrations
Implementation Method 6
The strut (8) forms a primary load path, which relays the weight and the air loads of the horizontal stabilizer (7) to the fuselage (2) through at least one strut (8)
Implementation Method 7
The horizontal stabilizer extension (9), together with the fuselage (2) and the propeller extension (14), forms a streamlined outer contour. The horizontal stabilizer (7) and the propeller (6) are mutually decoupled from vibrations through the indirect connection of the horizontal stabilizer to the fuselage by means of the at least one strut
Data Source
AI summary
The invention related to an autogyro (1) comprising a body (2), a mast (3) arranged in the upper region of the body, a rotor (4) which is rotatably arranged in the region of the end of the body (3) and which can be put into autorotation by an air flow, a drivable propeller (6) which is arranged in the region of a rear body end (5) and which generates a propulsion of the autogyro (1), a guide mechanism (7) arranged behind a propeller (1), and at least one brace (8) which extends past the propeller in the longitudinal direction of the autogyro at a radial distance from the propeller (6) in an outwards direction and which connects the guide mechanism (7) to the body (2). According to the invention, the guide mechanism (7) has a guide mechanism protrusion (9) which is arranged coaxially to the rear body end (5) and which extends forwards from the guide mechanism (7) in the direction of the rear body end (5) at a distance therefrom. Furthermore, at least the region of the rear body end (5) of the body (2) and the guide mechanism protrusion (9) together form a streamlined outer contour. The invention further relates to an autogyro in which the mast (3) is designed, in particular the mast is arranged and/or inclined relative to the propeller (6), such that when rotating, the blades (17) of the propeller (6) always only partly overlap with the mast (3) in a respective overlap region (21) when viewing the autogyro (1) from the rear.