Stopped-Rotor Pitch Control for Aircraft Fuselage Force Management
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Solution Overview
Problem
Existing control devices for aircraft fail to effectively manage the forces acting on the fuselage when rotor rotation is stopped, particularly during cruising, which can lead to inefficiencies and energy wastage.
Innovation Solution
A control device that controls the pitch of each blade and the stopped state rotation angle of the rotors to manage lift and drag forces on the fuselage, even when rotor rotation is stopped, by utilizing a combination of inner and outer rotors positioned strategically around the center of gravity to apply forces efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If rotor rotation is stopped during cruising, then energy consumption is reduced, but the ability to control forces on the fuselage deteriorates
Solution Approach 1:
The patent changes the operational parameters of the rotors by controlling the pitch angle of blades and the rotation angle of the rotor assembly itself, allowing the rotors to generate aerodynamic forces while stationary. This enables force control without requiring continuous rotation, thus maintaining control capability while reducing energy consumption.
Solution Approach 2:
The rotors serve multiple functions: they can generate lift during rotation for vertical movement, and they can also generate aerodynamic forces in a stopped state through pitch and rotation angle control for horizontal force application. This multi-functionality allows the same components to fulfill different control roles without requiring separate systems.
2Loss of energy
If rotor rotation is stopped during cruising, then energy wastage is reduced, but the response speed of force control deteriorates
Solution Approach 1:
By enabling the rotors to generate forces through parameter changes (pitch angle and rotation angle) rather than requiring rotation, the system achieves instantaneous force control capability. The control device can adjust these parameters rapidly to respond to changing flight conditions without the delay associated with accelerating rotor blades from rest.
3Productivity
If the rotors are positioned strategically around the center of gravity, then the efficiency of force application is improved, but the device complexity increases
Solution Approach 1:
The rotors are arranged asymmetrically around the center of gravity at specific positions and orientations. This asymmetric configuration allows the rotors to generate moments and forces more efficiently by creating asymmetric aerodynamic loading, improving the overall efficiency of force application while maintaining a manageable structural complexity through purposeful rather than random arrangement.
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 approach allows for improved control of forces on the fuselage, reduces energy consumption, and enhances response speed by optimizing the lift and drag generated by the rotors, even when they are not rotating.
Implementation Method 1
a plurality of rotors (12) each including one or more blades (26) and configured to generate lift by rotating about a rotation shaft (24)
Implementation Method 2
at least one fixed wing (18, 20) configured to generate lift when a fuselage (16) has an airspeed
Implementation Method 3
the control device controls a pitch of each of the blades (26) and a stopped state rotation angle of each of the rotors (12) to control a force generated in each of the rotors (12) in a state where rotation of the rotors (12) is stopped, thereby applying a force to the fuselage (16)
Data Source
AI summary
In a state where lift is generated in a front wing and a rear wing, a control device for an aircraft controls the pitch of each blade and the stopped state rotation angle of each VTOL rotor to control the force generated in each VTOL rotor in a state where rotation of the VTOL rotor is stopped, thereby applying a force to a fuselage.