VTOL Aircraft Control Device for Stationary Rotor Forces
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Solution Overview
Problem
Existing aircraft control systems face challenges in effectively managing the forces acting on the fuselage when rotor rotation is stopped, particularly in controlling lift, drag, and moments around the center of gravity.
Innovation Solution
The aircraft employs a control device that manages lift and drag generation in VTOL rotors by controlling the stopped state rotation angle and pitch of the blades, utilizing a power supply system and control mechanisms to optimize force application on the fuselage, even when rotors are not rotating.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the rotor rotation is stopped to reduce energy consumption, then energy efficiency is improved, but the control precision of forces acting on the fuselage deteriorates
Solution Approach 1:
The patent changes the operational parameters of the rotor blades by adjusting their pitch angles and rotation stop positions. By controlling the pitch of each blade and the stopped state rotation angle, the system generates precise lift and drag forces even when the rotor is stationary, enabling accurate force control without continuous rotation and thus reducing energy consumption while maintaining control precision.
2Use of energy by moving object
If the rotor rotation is stopped to improve energy efficiency, then energy consumption is reduced, but the response speed of force control deteriorates
Solution Approach 1:
The patent implements dynamic control of the rotor blades by independently adjusting the pitch of each blade and the stopped state rotation angle. This dynamic adjustment mechanism allows the system to respond quickly to control requirements while maintaining the rotor in a stopped state, thereby achieving both fast response speed and energy efficiency simultaneously.
3Measurement precision
If the stopped state rotation angle and blade pitch are controlled to generate precise forces, then control precision is improved, but the device complexity increases
Solution Approach 1:
The patent makes the rotor blade system multi-functional by enabling it to perform both rotational flight functions and stationary force generation functions. The same blade structure, when controlled in stopped state through pitch and rotation angle adjustment, can generate precise lift and drag forces, thereby expanding the system's functionality without adding separate control mechanisms, which helps manage device complexity while improving control precision.
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 precise control of forces and moments on the fuselage, improving response speed and reducing energy consumption by managing lift, drag, and moments, even when rotors are stationary, enhancing overall aircraft performance.
Implementation Method 1
rotors that generate lift by rotating
Implementation Method 2
the control device controls a pitch of each of the blades
Implementation Method 3
the control device controls a stopped state rotation angle of each of the rotors to control a force generated in each of the rotors in a state where rotation of the rotors is stopped
Data Source
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AI summary
A control device (48) for an vertical take-off and landing (VTOL) aircraft (10) with at least a fixed wing (18, 20) and a plurality of rotors (12) is provided. In a state where lift is generated in the wing (18, 20), said control device (48) controls the pitch of each blade (26) and the stopped state rotation angle of each VTOL rotor (12) to control the force generated in each VTOL rotor (12) in a state where rotation of the VTOL rotor (12) is stopped, thereby applying a force to a fuselage (16).