Tailsitting Coaxial Rotor Aircraft Thrust Vectoring
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Solution Overview
Problem
Current VTOL aircraft lack the efficiency and forward airspeed of fixed-wing aircraft, and tiltrotor and tiltwing designs face inefficiencies during vertical takeoff and landing due to downwash and control complexities.
Innovation Solution
A tailsitting biplane aircraft with a counter-rotating coaxial rotor system that transitions between thrust-borne lift in VTOL orientation and wing-borne lift in biplane orientation, utilizing a gimbal assembly for omnidirectional thrust vectoring and independent control of rotor assemblies for efficient flight modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If tiltrotor aircraft use fixed wing and proprotors with horizontal plane of rotation for vertical takeoff and landing, then vertical lift capability is achieved, but downwash inefficiencies occur due to interference from the fixed wing
Solution Approach 1:
The rotor system transitions from a horizontal plane of rotation (tiltrotor configuration) to a vertical plane of rotation (tiltwing configuration), changing the dimensional orientation of the rotating wings. This allows the slipstream to strike the wing on its smallest dimension, eliminating downwash inefficiencies while maintaining vertical lift capability
2Loss of energy
If tiltwing aircraft rotate the wing to vertical orientation for vertical takeoff and landing, then vertical thrust efficiency is improved, but control becomes more difficult during hover due to large surface area exposed to crosswinds
Solution Approach 1:
The wing rotation mechanism dynamically adjusts the wing orientation from vertical to horizontal plane, and the proprotors dynamically change from providing vertical thrust to providing forward thrust. This dynamic reconfiguration allows the system to optimize for vertical thrust efficiency during takeoff/landing while maintaining controllability during hover through active adjustment of the rotating wing and propeller configuration
3Productivity
If fixed-wing aircraft use wings to generate lift responsive to forward airspeed, then flight efficiency is achieved, but a long runway is required for takeoff and landing
Solution Approach 1:
The rotating wing-propropeller assembly serves multiple functions: it can generate vertical lift for VTOL operations, provide forward thrust for efficient wing-borne flight, and transition between these modes. This multi-functionality allows the aircraft to combine the runway-independent vertical takeoff capability of helicopters with the high efficiency of fixed-wing aircraft, eliminating the need for long runways while maintaining flight efficiency
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 landing, high-speed forward flight, and improved control authority through omnidirectional thrust vectoring and independent rotor control, addressing the inefficiencies of existing VTOL designs.
Implementation Method 1
A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly.
Implementation Method 2
A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation with the first rotor assembly counter-rotating relative to the second rotor assembly.
Implementation Method 3
A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.
Data Source
AI summary
A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.