Aerospace Vehicle with Three High Aspect Ratio Wings
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft designs face challenges in achieving fuel efficiency, reducing emissions, and minimizing production costs due to the complexity and weight of traditional materials, while also needing to operate from limited spaces and meet stringent environmental regulations.
Innovation Solution
The design incorporates a fuselage made of at least 50% composite materials with a high fineness ratio, featuring three high aspect ratio wings and a V-tail stabilizing unit, along with vertically stacked turbofan engines to reduce thrust asymmetry and drag, optimizing fuel efficiency and structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional materials and single-wing design are used, then structural simplicity is maintained, but fuel efficiency and emissions are worsened
Solution Approach 1:
The aircraft is divided into multiple modular barrel sections that can be manufactured separately and then assembled. This segmentation allows for simplified manufacturing of individual sections while achieving the overall complex efficient aerodynamic shape, resolving the contradiction between fuel efficiency requirements and manufacturing complexity
Solution Approach 2:
The patent employs composite materials in the construction of the fuselage and wings to reduce overall weight while maintaining structural integrity. This material substitution improves fuel efficiency without significantly increasing manufacturing complexity, as composite materials can be formed in large sections suitable for aircraft construction
2Use of energy by moving object
If multiple lifting surfaces are added, then fuel efficiency is improved, but device complexity increases
Solution Approach 1:
The lifting surface is segmented into multiple wings distributed across the fuselage barrels. This segmentation creates multiple smaller lifting surfaces that collectively provide improved fuel efficiency while each individual wing maintains a manageable complexity level, avoiding the need for a single extremely complex wing structure
Solution Approach 2:
Multiple wings are combined with multiple fuselage barrels to create a distributed lifting system. The merging of these elements achieves superior fuel efficiency through reduced induced drag, while the modular nature of the combination keeps the overall device complexity manageable through standardized repeating units
3Weight of moving object
If composite materials are used, then weight is reduced and fuel efficiency improves, but manufacturing precision requirements increase
Solution Approach 1:
The composite structure is divided into separate barrel sections and wing components that can be manufactured with controlled precision requirements for each segment. This segmentation allows for quality control and precision management at the component level rather than requiring entire aircraft-level precision, reducing the overall manufacturing precision burden while maintaining weight benefits
4Reliability
If vertically stacked engines are used, then thrust asymmetry is reduced, but engine mounting complexity increases
Solution Approach 1:
The engine mounting employs an asymmetric vertically stacked configuration on each side of the fuselage. This asymmetric arrangement within each pod, when mirrored on both sides, creates overall symmetry in thrust production while the vertical stacking itself is an asymmetric solution to the traditional side-by-side horizontal arrangement, improving thrust symmetry reliability
Solution Approach 2:
Multiple engines are merged into vertically stacked pods mounted on the fuselage. This merging of engines into compact vertical units reduces the lateral distance between engines, improving thrust symmetry. The pod structure combines engine mounting, exhaust routing, and structural support into an integrated assembly, managing the complexity through functional integration
Data Source
AI summary
Various aerospace vehicle systems and methods are disclosed. In one embodiment, a fuel efficient, low emissions aerospace vehicle includes a fuselage having a fineness ratio of equal to or greater than 8. The fuselage is comprised of at least 50% composite materials. The aerospace vehicle also includes a first wing, a second wing, and a third wing coupled to the fuselage, each wing having an aspect ratio of equal to or greater than 35. The wings each have a span within 10% of one another and an aspect ratio within 10% of one another. Each wing is comprised of at least 50% composite materials. The aerospace vehicle also includes at least one stabilizing unit coupled to the fuselage. The stabilizing unit includes first and second stabilizer surfaces configured in a V-tail configuration. The aerospace vehicle further includes at least one propulsion system.