Tiltrotor Pylon and Wing Transition for Lower VTOL Power
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Solution Overview
Problem
Existing electric tiltrotor aircraft designs face challenges in efficiently transitioning between vertical takeoff and landing (VTOL) mode and forward flight mode due to issues with rotor power requirements and wing download during transitions, which affect flight efficiency and performance.
Innovation Solution
The implementation of tiltable rotor pylons and wing configurations that allow for selective control of rotor blade pitch and wing rotation, utilizing linear or rotary actuators to facilitate smooth transitions between hover and cruise modes, reducing power requirements and enhancing flight capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If rotor power requirements are increased to enable VTOL mode, then vertical takeoff and landing capability is achieved, but power consumption increases significantly
Solution Approach 1:
The rotor system is designed to dynamically change its configuration between two distinct operational modes: vertical orientation for VTOL operations and horizontal orientation for forward flight. This dynamic reconfiguration allows the same rotor system to serve multiple functions, reducing overall power consumption by optimizing the aerodynamic efficiency for each flight regime rather than requiring excessive power for vertical operations with a fixed-configuration system
2Strength
If wing download forces are reduced during mode transition, then structural stress is minimized, but transition efficiency may be affected
Solution Approach 1:
The control system performs preliminary adjustments to rotor blade pitch and wing orientation before completing the full mode transition. By pre-positioning the rotors and adjusting blade angles in advance, the system minimizes sudden download forces on the wing structure during transition while maintaining efficient transition timing. This staged approach allows structural loads to be managed without significantly extending the overall transition duration
3Productivity
If rotor blade pitch control is optimized for cruise mode, then forward flight efficiency is improved, but VTOL performance may be compromised
Solution Approach 1:
The rotor blade pitch control system is designed to dynamically adapt blade angles based on the current flight mode. During VTOL operations, blades are positioned at high pitch angles to maximize vertical lift generation. During forward flight, the system transitions to optimized cruise pitch angles that reduce drag and improve propulsive efficiency. This dynamic pitch adjustment allows the same rotor system to reliably perform both VTOL and efficient forward flight without compromising either regime
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
The described configurations enable efficient conversion between VTOL and forward flight modes, optimizing power usage and reducing download forces, thereby improving the overall flight performance and efficiency of electric tiltrotor aircraft.
Implementation Method 1
utilizing linear or rotary actuators to facilitate smooth transitions between hover and cruise modes
Implementation Method 2
rotational energy in an aircraft propulsion system for enabling the aircraft to hover, take off, and land vertically
Data Source
AI summary
Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.