VTOL Engine Module Tilting for Speed Without Rotor Energy Penalty
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Solution Overview
Problem
Current VTOL vehicles face limitations such as high operational costs, complex infrastructure requirements, noise pollution, and restricted speed and endurance due to energy-intensive rotor-based lift systems, while land vehicles are constrained by speed and accessibility.
Innovation Solution
A VTOL vehicle design featuring pivotally mounted engine modules on lifting surfaces and fuselage, allowing transition between vertical and horizontal flight modes, with independent control for each engine module to optimize lift and thrust, eliminating the need for traditional aerodynamic control surfaces and enabling autonomous or remote-controlled operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If rotor-based lift systems are used in conventional VTOL aircraft, then vertical take-off and landing capability is achieved, but speed and endurance are restricted due to high energy consumption
Solution Approach 1:
The patent employs dynamically adjustable engine module tilting mechanisms that allow the vehicle to transition between vertical and horizontal flight modes. The engine modules can be tilted independently to optimize thrust vectoring for different flight phases, enabling the vehicle to achieve high speeds in horizontal mode while maintaining VTOL capability, thus resolving the contradiction between speed and energy consumption.
Solution Approach 2:
The system changes the operational parameters of the engine modules by adjusting their tilt angles and thrust output. During vertical take-off, engines operate at high thrust with vertical orientation; during horizontal flight, engines transition to forward thrust with optimized tilt angles. This parameter adjustment allows the vehicle to achieve high speeds during horizontal flight while consuming less energy compared to continuous rotor-based vertical lift.
2Adaptability or versatility
If traditional VTOL aircraft designs are used, then vertical flight capability is achieved, but operational costs are high and complex infrastructure is required
Solution Approach 1:
The patent divides the propulsion system into multiple independent engine modules, each capable of independent control and tilting. This segmentation allows the vehicle to achieve complex flight maneuvers and mode transitions without requiring a single complex rotor system, thereby reducing infrastructure requirements while maintaining flight adaptability.
Solution Approach 2:
The engine modules serve multiple functions: they provide vertical lift during take-off, forward thrust during horizontal flight, and can be independently controlled for maneuvering. This multi-functionality eliminates the need for separate rotor systems and complex control mechanisms, reducing overall device complexity and infrastructure requirements while maintaining versatility.
3Quantity of substance
If conventional VTOL aircraft are used, then payload transport capability is achieved, but noise footprint is high
Solution Approach 1:
The patent replaces traditional rotor-based mechanical lift systems with engine modules that can operate in both vertical and horizontal modes. The engine modules use directed thrust rather than continuous rotor rotation, significantly reducing noise generation during horizontal flight while maintaining payload transport capability. The modular design allows for optimized noise reduction in each engine unit.
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 speed, accessibility, and maneuverability, reduces operational costs, and minimizes noise and infrastructure needs, while improving range and payload capacity compared to conventional VTOL aircraft and land vehicles.
Implementation Method 1
at least one engine module located rearward of each wing of the first lifting surface and coupled or mounted to a rear portion of the rear section of the fuselage
Implementation Method 2
each engine module is pivotable about a tilt axis defined by the support strut to which the respective engine module is coupled or mounted and is independently controllable for transitioning between a vertical mode of flight and a horizontal mode of flight
Implementation Method 3
a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage
Data Source
Figure 1a
Figure 1b~1c
Figure 1d~1e
AI summary
Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing and/or fuselage section comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and/or fuselage and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.