Rotor Torque Assembly with Damping Member for Blade Pitch Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing rotor control systems for rotary wing aircraft, such as those used in UAVs and helicopters, face limitations in controlling blade pitch angles without swash plates and servos, leading to vibrations and reduced maneuverability, especially when operating outside nominal torque or RPM conditions.
Innovation Solution
A thrust-generating rotor assembly with a cyclic pitch control system, featuring a rotor torque assembly connected to a rotor blade assembly via spring members and a damping member, which transfers torque changes into rotational offsets and tilting moments to control blade pitch angles, minimizing vibrations and maintaining stability across varying torque conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a connecting member made of flexible material is used to cyclically control blade pitch angle without swash plate and servos, then device complexity is reduced, but vibrations increase when operating outside nominal torque or RPM conditions
Solution Approach 1:
The patent introduces a damping member that changes the dynamic parameters of the control system. The damping member is configured to provide damping force that counteracts vibrations caused by parameter variations in torque and RPM, allowing the flexible connecting member to function effectively across a wider operating range without excessive vibrations
Solution Approach 2:
The damping member acts as an intermediary between the rigid rotor blade assembly and the flexible connecting member. It mediates the transmission of torque changes while filtering out harmful vibrations, enabling the system to maintain control precision without the complexity of traditional swash plate and servo mechanisms
2Ease of operation
If the connecting member is adjusted to fit a certain rotor torque, then blade pitch control is achieved, but maneuverability is reduced when torque varies from nominal values
Solution Approach 1:
The patent makes the control system dynamic by introducing a damping member that adapts to varying torque conditions. The damping member's force characteristics allow the system to maintain effective blade pitch control across a range of torque values, enabling the aircraft to maneuver effectively whether torque is above, below, or at nominal values
Solution Approach 2:
The damping member is designed with specific damping coefficients that compensate for parameter changes in rotor torque. This allows the connecting member to effectively transfer torque changes to blade pitch changes across varying operating conditions, maintaining both control precision and maneuverability
3Measurement precision
If spring members are used to transfer torque changes into rotational offsets, then blade pitch angle control precision is improved, but device complexity increases
Solution Approach 1:
The patent segments the control system into distinct functional components: the connecting member for torque transmission, the spring members for precise rotational offset generation, and the damping member for vibration control. This segmentation allows each component to be optimized for its specific function while maintaining overall system manageability
Solution Approach 2:
The spring members act as intermediaries between the torque assembly and the rotor blades, converting torque changes into precise rotational offsets that control blade pitch angles. The damping member serves as an intermediary that filters harmful vibrations from this control mechanism
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 system enables precise control of blade pitch angles, reducing vibrations and maintaining stability, even in challenging conditions like wind or turbulence, and allows for predictable tilting moments to adjust blade pitch, enhancing maneuverability and flight control.
Implementation Method 1
at least one spring member connected between the rotor torque assembly and the rotor blade assembly is adjusted to transfer changes in rotor torque into proportional changes in rotational offset
Implementation Method 2
a damping member, interacting with a pitch arm, is adjusted to transfer said changes in rotational offset into substantial tilting moments about said rotor blade axis at rapid changes in rotor torque and to cancel or limit said tilting moments at slow or permanent changes in rotor torque
Data Source
AI summary
The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.