VTOL Winged Aircraft With Angled Rotors for Torque-Assisted Control
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Solution Overview
Problem
Existing quadrotor aerial vehicles face challenges in achieving efficient vertical take-off and landing (VTOL) with optimal control and reduced power requirements, as their propellers are often large and cumbersome, limiting maneuverability and increasing weight.
Innovation Solution
The design incorporates angled motors and propellers on each end of the wing, angled between 5 to 35 degrees from the longitudinal axis, providing a lateral thrust component that creates a torque additive, allowing for controlled movements without changing propeller pitches, and utilizing fixed pitch propellers to reduce weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If large propellers are used in quadrotor to provide appropriate control, then control precision is improved, but device weight increases and maneuverability decreases
Solution Approach 1:
The aircraft is divided into multiple functional modules: fixed-wing section for forward flight, vertical stabilizer for attitude control, and multiple rotor assemblies for vertical flight and maneuvering. This segmentation allows each component to be optimized independently, enabling precise control with smaller, lighter rotors rather than requiring one large propeller system.
Solution Approach 2:
The rotors serve multiple functions: providing vertical lift during takeoff and landing, enabling hover control, assisting in transition phases, and contributing to maneuverability. This multi-functionality allows smaller rotors to achieve control precision that would otherwise require much larger single propellers, thereby reducing overall weight.
2Use of energy by moving object
If large propellers are used in quadrotor to reduce power required, then energy efficiency is improved, but device complexity and size increase
Solution Approach 1:
The aircraft utilizes dynamic transition between vertical and horizontal flight modes. During forward flight, the fixed wing generates lift efficiently, reducing power consumption. During vertical flight and transitions, the rotors provide necessary thrust. This dynamic operation allows the system to use smaller, less complex rotors while maintaining energy efficiency across different flight phases.
Solution Approach 2:
The aircraft changes operational parameters by transitioning between different flight modes (vertical, hover, forward, transition). This allows the system to optimize power consumption for each phase using appropriate lift generation methods (rotors for vertical, wing for forward), avoiding the need for oversized rotors that would be required if only rotor-based flight were used.
3Ease of operation
If angled motors are used to provide torque additive for controlled movement, then maneuverability is improved, but device complexity increases
Solution Approach 1:
The motor assemblies are positioned asymmetrically relative to the aircraft centerline, with specific offsets in the spanwise direction. This asymmetric positioning, combined with selective motor activation, provides efficient torque generation for rolling and yawing maneuvers without requiring complex mechanical tilting mechanisms, thus improving maneuverability while controlling complexity.
Solution Approach 2:
The aircraft uses multiple identical motor-rotor assemblies positioned at different locations. By activating different combinations of these replicated units, the system generates various torque components for controlled movement. This approach simplifies the control system compared to using single complex articulated motors, as each replicated unit can be controlled independently to achieve desired maneuvering effects.
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 enables efficient VTOL operations with improved maneuverability, reduced power consumption, and enhanced durability by leveraging angled motors and fixed pitch propellers, facilitating transitions between vertical and horizontal flight.
Implementation Method 1
each motor may be angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement may apply a resulting torque additive to a resulting torque created by rotating the propellers
Implementation Method 2
each motor may be angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement may apply a resulting torque additive to a resulting torque created by rotating the propellers
Data Source
AI summary
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.