Rotatable VTOL Pod and Wing Layout for Compact Takeoff Footprint
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Solution Overview
Problem
Existing VTOL aircraft face challenges in achieving a large wingspan for efficiency in forward flight while minimizing the ground area required for takeoff and landing, and they suffer from inefficiencies in propulsion systems that limit range and endurance.
Innovation Solution
The aircraft design incorporates rotatable pods and wings that transition between a compact stowed configuration for takeoff and landing to a large wingspan configuration for forward flight, using a pusher propeller and adjustable turbojet engines for efficient thrust and lift, with rotatable vertical stabilizers and stowable landing gear to reduce drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the aircraft uses a fixed large wingspan design, then forward flight efficiency is improved, but the ground area required for takeoff and landing increases
Solution Approach 1:
The wings are designed to be movable rather than fixed, allowing them to rotate between a stowed position during vertical takeoff and landing, and a deployed position during forward flight. This dynamic configuration enables the aircraft to optimize its wing span according to the operational mode, resolving the contradiction between forward flight efficiency and ground area requirements.
Solution Approach 2:
The aircraft structure is divided into separable components, with the wings being independent movable elements that can be positioned separately from the fuselage. This segmentation allows the wings to be stowed close to the fuselage during vertical operations, minimizing ground area, and deployed outward during forward flight to maximize aerodynamic efficiency.
2Area of stationary object
If the aircraft uses a compact configuration for takeoff and landing, then ground area is minimized, but wingspan for forward flight efficiency is reduced
Solution Approach 1:
The movable wing design allows the aircraft to transition from a compact configuration during vertical operations to an extended wingspan configuration during forward flight. The wings rotate about the fuselage, enabling the aircraft to minimize ground area when needed while achieving large wingspan for efficient forward flight when required.
Solution Approach 2:
The wings are positioned in a different spatial dimension during vertical takeoff and landing (close to the fuselage) compared to their position during forward flight (extended outward). This dimensional transformation allows the aircraft to optimize its footprint on the ground while maintaining the capability for large wingspan in forward flight mode.
3Device complexity
If traditional VTOL aircraft use fixed propulsion systems, then structural simplicity is maintained, but range and endurance are limited
Solution Approach 1:
The propulsion system is designed with multi-functionality, where the same engines and propellers can operate effectively in both vertical takeoff and landing modes and forward flight modes. The pusher propeller configuration and adjustable turbojet engines provide universal propulsion capability across different flight regimes, extending range and endurance without requiring separate specialized propulsion systems for each mode.
Solution Approach 2:
The propulsion system utilizes adjustable parameters, including variable engine thrust settings and propeller pitch adjustments, to optimize performance across different flight conditions. By changing operational parameters rather than physical configuration, the aircraft achieves extended range and endurance while maintaining relatively simple structural design.
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 design enhances flight efficiency, range, and endurance by optimizing wing span and propulsion systems, while minimizing logistical and safety issues associated with traditional VTOL aircraft.
Implementation Method 1
The pod aft portion rotates, together with the outboard wing and the vertical stabilizer, about a centerline of the pod relative to the pod forward portion
Implementation Method 2
using a pusher propeller and adjustable turbojet engines for efficient thrust and lift
Implementation Method 3
adjustable turbojet engines for efficient thrust and lift
Implementation Method 4
rotatable vertical stabilizers and stowable landing gear to reduce drag
Data Source
AI summary
A VTOL aircraft includes a pod having a pod forward portion and a pod aft portion. The pod forward portion is connected to an inboard wing of the VTOL aircraft and the pod aft portion is connected to an outboard wing and a vertical stabilizer of the VTOL aircraft. The pod aft portion rotates, together with the outboard wing and the vertical stabilizer, about a centerline of the pod relative to the pod forward portion.