Tiltable Proprotor Aircraft With Autorotating Central Rotor
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Solution Overview
Problem
Current aircraft, such as helicopters and gyrocopters, face limitations in operating energy efficiency and vertical takeoff capabilities, with helicopters being inefficient and gyrocopters unable to take off vertically due to fixed rotor pitch and autorotation reliance.
Innovation Solution
The design incorporates a fuselage with a mast, rotatable rotor, lateral boom, and tiltable proprotors powered by independent motors, allowing for vertical and horizontal flight modes through adjustable tilt angles and rotor pitch adjustments, enabling efficient transition between flight configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a helicopter uses a fixed vertical shaft with swash plates and links to modify rotor blade pitch, then vertical takeoff and hovering capability is achieved, but operating energy efficiency deteriorates compared to fixed-wing aircraft
Solution Approach 1:
The patent applies dynamics by making the rotor shaft tiltable rather than fixed vertical. The rotor shaft can tilt forward during horizontal flight to enable autorotation like a gyrocopter, reducing energy consumption. The system dynamically adjusts shaft orientation based on flight mode, combining vertical takeoff capability with energy-efficient horizontal flight.
Solution Approach 2:
The patent changes the parameter of rotor shaft orientation from fixed vertical to variable tilt angle. By adjusting the shaft tilt angle, the system transitions between vertical flight mode (shaft vertical) and horizontal flight mode (shaft tilted), optimizing energy efficiency while maintaining vertical takeoff capability.
2Use of energy by moving object
If a gyrocopter uses an unpowered rotor in autorotation to develop lift, then operating energy efficiency improves, but vertical takeoff capability is lost due to fixed rotor pitch and autorotation reliance
Solution Approach 1:
The patent makes the rotor shaft dynamic and tiltable, allowing it to transition from vertical orientation (enabling powered vertical takeoff) to tilted orientation (enabling autorotation). This dynamic adjustment resolves the contradiction by allowing the system to operate in both vertical takeoff mode and energy-efficient autorotation mode.
Solution Approach 2:
The tiltable rotor shaft serves multiple functions: it enables vertical takeoff when positioned vertically with powered rotation, and enables autorotation when tilted forward during horizontal flight. This multi-functionality allows the aircraft to combine the vertical capability of helicopters with the energy efficiency of gyrocopters.
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 configuration enhances flight efficiency, enabling vertical takeoff and landing, hovering, and extended data gathering or observation without requiring a runway, while maintaining stability and maneuverability across various flight modes.
Implementation Method 1
a rotor motor disposed at the upper end of the mast and configured to cause rotation of the rotor in a first direction
Implementation Method 2
a first powered proprotor disposed at a first end of the lateral boom, a second powered proprotor disposed at a second end of the lateral boom
Implementation Method 3
a first proprotor tilt servo configured to control an orientation the first powered proprotor between at least a horizontal tilt angle and a vertical tilt angle
Implementation Method 4
a rotor rotatably coupled to an upper end of the mast opposite the lower end
Data Source
AI summary
Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.