Tailless VTOL Aircraft Control via Differential Thrust
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Solution Overview
Problem
Existing electrically powered aerial vehicles, particularly VTOL vehicles, are complex due to the need for articulating engines or rotatable wings for vertical and horizontal flight, and lack efficient control systems without control surfaces.
Innovation Solution
A tailless aerial vehicle design with stacked wings and a control system that differentially varies the rotational energy of electric motors to alter orientation, using multiple thrust-producing elements grouped into quadrants for control, and incorporates a battery energy monitoring system to manage power for efficient flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If articulating engines or rotatable wings are used for vertical and horizontal flight, then the vehicle can achieve versatile flight modes, but the device complexity increases
Solution Approach 1:
The vehicle divides its thrust production system into multiple independent thrust-producing elements (at least three, preferably four or more) distributed across the structure. Each element can be independently controlled by separate electric motors, allowing the system to achieve various flight modes (vertical takeoff, horizontal flight, hovering, maneuvering) through differential thrust control without requiring mechanical articulation or rotation of entire wings or engines.
Solution Approach 2:
The patent replaces mechanical articulation systems and rotatable wing mechanisms with an electrically controlled thrust vectoring system. Instead of mechanically moving engines or wings to change flight orientation, the system uses multiple electric motors to independently control the thrust magnitude and direction of fixed-position thrust-producing elements, substituting complex mechanical motion with electrical control.
2Ease of operation
If control surfaces are used for orientation control, then the vehicle can achieve precise maneuvering, but the device complexity increases
Solution Approach 1:
The patent extracts and eliminates traditional control surfaces (ailerons, elevators, rudders) from the vehicle design. Instead of using aerodynamic control surfaces that require hinges, linkages, and mechanical actuation systems, the invention achieves orientation control solely through differential thrust modulation of the multiple electric motors driving the thrust-producing elements, thereby simplifying the control system while maintaining maneuverability.
Solution Approach 2:
The patent substitutes mechanical control surface actuation systems with an electrically controlled thrust differential system. Orientation control is achieved by varying the rotational speed and thrust output of individual electric motors, replacing the need for mechanical linkages, hinges, and aerodynamic control surfaces with an all-electric control architecture.
3Measurement precision
If multiple thrust-producing elements with independent motor control are used, then the orientation control precision improves, but the device complexity increases
Solution Approach 1:
The patent designs the control system to universally manage multiple electric motors through a unified control architecture. The same control mechanism differentially varies the rotational energy of all motors to achieve both propulsion and orientation control functions simultaneously, allowing the system to maintain precise maneuvering capability while avoiding the need for separate control mechanisms for each motor, thereby managing complexity through functional integration.
Solution Approach 2:
The control system dynamically adjusts the rotational energy of individual motors based on real-time flight conditions and desired orientation changes. By continuously varying motor speeds and thrust outputs in response to control inputs, the system achieves precise orientation control without requiring complex mechanical control surfaces, using dynamic electrical control instead of static mechanical linkages.
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 and horizontal takeoff and flight without control surfaces, providing stable orientation control and energy management, enhancing the operational simplicity and efficiency of electrically powered aerial vehicles.
Implementation Method 1
a plurality of electric motors for driving the thrust producing elements
Implementation Method 2
differentially varying the thrust of the thrust producing elements thereby altering the orientation of the vehicle
Implementation Method 3
take a first measurement of the voltage in the battery at an initial epoch under a substantially no-load condition, take a second measurement of voltage in the battery and a measurement of current flow into or out of the battery at a subsequent epoch, integrate the second measurement of voltage and the current flow measurement with respect to time
Data Source
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AI summary
An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.