VTOL Aircraft Thrust Differential Control for Transition
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Solution Overview
Problem
Current vertical takeoff and landing (VTOL) aircraft configurations require separate systems for vertical takeoff and horizontal flight, lacking efficient control mechanisms for attitude and transition between these modes.
Innovation Solution
An aerial vehicle utilizing ducted fans driven by electric motors, with thrust differentials in two dimensions to control attitude during takeoff and landing, and transitioning to horizontal flight by altering wing position and thrust direction, allowing for continuous control using the same set of thrust-producing elements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If separate systems are used for vertical takeoff and horizontal flight, then control precision is improved, but device complexity increases
Solution Approach 1:
The patent applies multi-functionality by using the same thrust-producing elements (ducted fans) for both vertical takeoff and horizontal flight operations. The system transitions between flight modes by altering the orientation and thrust direction of these elements rather than switching between separate systems, thereby reducing device complexity while maintaining control precision through differential thrust management.
Solution Approach 2:
The patent implements dynamics by enabling the thrust-producing elements to change orientation and thrust direction continuously between vertical and horizontal configurations. This dynamic adjustment allows the same components to perform multiple functions across different flight phases, resolving the contradiction between control precision and system complexity.
2Ease of operation
If thrust differentials are used for attitude control, then ease of operation is improved, but device complexity increases
Solution Approach 1:
The patent applies self-service by using the thrust-producing elements themselves for attitude control during takeoff and landing, rather than requiring separate control surfaces or mechanisms. The differential thrust from the ducted fans directly controls vehicle attitude, simplifying the control system while improving ease of operation through integrated thrust-based control.
3Reliability
If motors and wings remain stationary relative to each other, then reliability is improved, but adaptability decreases
Solution Approach 1:
The patent resolves this contradiction by making the relative positioning of motors and wings dynamic rather than static. The ducted fans can change their orientation and thrust direction relative to the wings, allowing the system to adapt to different flight modes (vertical takeoff, horizontal flight, transition phases) while maintaining reliable operation through controlled differential thrust rather than mechanical reconfiguration.
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
Enables efficient vertical takeoff and transition to horizontal flight without relative motion of motors and wings, maintaining attitude control through differential thrust and wing positioning, enhancing safety, reliability, and reducing noise.
Implementation Method 1
An aerial vehicle utilizing ducted fans driven by electric motors, with thrust differentials in two dimensions to control attitude during takeoff and landing
Implementation Method 2
maintaining attitude control through differential thrust and wing positioning
Data Source
AI summary
An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.