Modular Man-Portable Aircraft Rapid Assembly and VTOL Transition
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Solution Overview
Problem
Current aircraft systems face challenges in transitioning efficiently between thrust-borne lift in VTOL orientation and wing-borne lift in biplane orientation, particularly in terms of rapid assembly and control, especially for man-portable systems that require versatile flight modes and payload handling.
Innovation Solution
A man-portable aircraft system with modular components, including wings, pylons, and propulsion assemblies, that can be rapidly assembled and disassembled using high-speed fastening elements and redundant communication channels, allowing for transition between VTOL and biplane orientations, with a flight control system capable of independent control of propulsion assemblies for various flight modes and payload operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If the aircraft uses modular components for rapid assembly, then assembly time is reduced, but connection reliability may be compromised
Solution Approach 1:
The aircraft is divided into modular components (wings, pylons, propulsion assemblies, payload) that can be independently manufactured, transported, and assembled. Each component has standardized connection interfaces that enable rapid assembly while maintaining structural integrity through precision-engineered mating surfaces and locking mechanisms.
Solution Approach 2:
Connection features are pre-integrated into each modular component during manufacturing, including standardized fastening elements, alignment pins, and interface geometries. This preliminary preparation eliminates the need for complex field assembly operations while ensuring consistent connection quality and reliability across all assemblies.
2Adaptability or versatility
If the aircraft transitions between VTOL and biplane orientations, then flight versatility is improved, but control complexity increases
Solution Approach 1:
The propulsion assemblies are designed with universal control interfaces and thrust vectoring capabilities that enable the same hardware to perform multiple functions across different flight modes. The flight control system uses a unified control architecture that automatically adapts control algorithms based on the current orientation (VTOL or biplane) without requiring separate control systems for each mode.
Solution Approach 2:
The aircraft employs dynamic reconfiguration of control surface effectiveness and thrust distribution based on real-time orientation detection. During transitions between VTOL and biplane modes, the control system dynamically adjusts stabilizer angles, aileron authority, and individual propulsion thrust levels to maintain stable control across the full envelope of flight attitudes.
3Productivity
If high-speed fastening elements are used for component connection, then assembly speed increases, but manufacturing precision requirements increase
Solution Approach 1:
The connection interfaces incorporate localized precision features (alignment pins, tapered mating surfaces, keyed interfaces) at critical connection points while maintaining standard tolerances elsewhere on the components. This concentrates manufacturing precision requirements only where absolutely necessary for rapid connection, rather than requiring high precision across entire component surfaces.
Solution Approach 2:
The fastening system replaces traditional multi-step mechanical fastening with high-speed connection elements that utilize spring-loaded locking mechanisms and cam-actuated clamping. These mechanisms achieve secure structural connections through controlled deformation and friction locking rather than precision thread engagement, significantly reducing assembly time while maintaining connection strength.
Data Source
Figure 1A~1B
Figure 1C~1D
Figure 1E~1F
AI summary
A man portable aircraft system (100) includes first and second wings (14, 16) with first and second pylons (18, 20) couplable between pylon stations (14a-b, 16a-b) thereof to form an airframe. Each of a plurality of propulsion assemblies (24, 26) is couplable to one of a plurality of nacelle stations (14c-f, 16c-f) of the wings (14, 16) to form a two-dimensional distributed thrust array. A flight control system (22) is couplable to the airframe and is operable to independently control each of the propulsion assemblies (24, 26). A payload (30) is couplable between payload stations (18b, 20b) of the first and second pylons (18, 20). A man portable container (102) is operable to receive the wings (14, 16), pylons (18, 20), propulsion assemblies (24, 26), flight control system (22) and payload (30) in a disassembled configuration. The connections between the wings (14, 16), pylons (18, 20), propulsion assemblies (24, 26) and payload (30) are operable for rapid in-situ assembly. In an assembled configuration, the aircraft (10) is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation.