Compound Rotorcraft Polyhedral Wing Landing Gear Integration
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Solution Overview
Problem
Existing compound rotorcrafts face inefficiencies at high speeds and inadequate main landing gear integration due to suboptimal fixed wing arrangements, which hinder operational efficiency and ground stability.
Innovation Solution
A compound rotorcraft design featuring a polyhedral and multi-sweep lower wing configuration with a kinked layout, allowing for improved aerodynamic efficiency, main landing gear integration, and reduced structural weight, along with a bi-plane wing structure for enhanced lift and thrust capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a conventional fixed wing arrangement is used, then the structure is simple, but aerodynamic efficiency at high speeds is poor
Solution Approach 1:
The lower wing is divided into two distinct sections: an inboard section connected to the fuselage and an outboard section connected to the upper wing. This segmentation allows each section to be optimized independently for its specific aerodynamic function, improving overall efficiency while managing complexity through modular design
Solution Approach 2:
The wing configuration transitions from a conventional planar arrangement to a three-dimensional polyhedral structure with multiple sweep angles and dihedral angles. The outboard section features a different sweep angle than the inboard section, creating a multi-dimensional geometry that optimizes airflow patterns for high-speed operation
2Weight of moving object
If the fuselage is narrowed to reduce weight, then structural weight is reduced, but ground stability is compromised
Solution Approach 1:
The main landing gear is positioned at the sections interconnection region rather than directly under the fuselage. This lateral displacement in the transverse dimension, combined with the polyhedral wing geometry, creates a wider effective base of support that maintains ground stability even with a narrowed fuselage
Solution Approach 2:
The separation of the lower wing into inboard and outboard sections creates distinct structural zones. The inboard section provides structural support and landing gear mounting, while the outboard section contributes to aerodynamic stability, allowing the fuselage to be narrowed without compromising overall stability
3Weight of moving object
If the main landing gear is integrated into the wing structure, then structural weight is reduced, but integration complexity increases
Solution Approach 1:
The main landing gear is integrated into the inboard section of the lower wing, merging the landing gear structure with the wing structure. This integration eliminates separate landing gear support structures and reduces overall weight, while the modular section design simplifies the integration process
Solution Approach 2:
The lower wing is segmented into inboard and outboard sections, with the inboard section specifically designed to accommodate the main landing gear. This segmentation isolates the integration complexity to a specific module rather than the entire wing structure, making the integration process more manageable
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 design enhances aerodynamic efficiency, reduces main landing gear weight by 10%, and maintains ground stability with a narrower fuselage while allowing for easier integration and retraction of landing gears, improving overall performance and efficiency at high speeds.
Implementation Method 1
at least one main rotor that is at least adapted for generating lift in operation
Implementation Method 2
at least one propeller that is at least adapted for generating forward thrust in operation
Implementation Method 3
at least one upper wing that is arranged at an upper wing root joint area provided at an upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at a lower side of the fuselage
Data Source
AI summary
A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.