Dual Rotor Helicopter Control System for Counteracting Rotor Moments
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Solution Overview
Problem
Dual-rotor helicopters face control issues and potential clearance problems due to opposing rotor moments during maneuvers, which can lead to stress and aerodynamic inefficiencies.
Innovation Solution
A control system that senses angular velocity and acceleration, comparing data to control parameters to adjust the cyclic pitch of rotors via control servos, counteracting rotor moments and reducing stresses between rotors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If dual-rotor helicopters perform maneuvers, then maneuvering capability is improved, but rotor moments produce control problems and clearance issues
Solution Approach 1:
The control system applies preliminary anti-action by detecting angular velocity and acceleration during maneuvers, then preemptively adjusting cyclic pitch to counteract rotor moments before they cause control problems or clearance issues. The system calculates required pitch changes based on maneuver parameters and applies them in advance to prevent harmful effects.
Solution Approach 2:
The invention implements feedback control by continuously monitoring angular velocity and angular acceleration sensors, comparing actual values against desired maneuver parameters, and adjusting cyclic pitch accordingly. This closed-loop feedback system ensures precise control during maneuvers while maintaining rotor clearance and preventing control problems.
2Strength
If rotor moments are not counteracted, then helicopter structure experiences stress, but adding control systems increases device complexity
Solution Approach 1:
The control system performs multiple functions using integrated components: sensors detect both angular velocity and acceleration, the computer processes both parameters to determine pitch adjustments, and the control servos execute cyclic pitch changes. This multi-functionality reduces the need for separate specialized components, thereby limiting the increase in device complexity while providing comprehensive rotor moment counteraction.
Solution Approach 2:
The control system acts as an intermediary between the helicopter's natural rotor moment generation and the structural components that would otherwise experience stress. By introducing this intermediate control layer that processes sensor data and generates corrective pitch commands, the system protects the structure from excessive stress while maintaining manageable complexity through automated control rather than mechanical reinforcement.
3Loss of energy
If rotor moments act on rotors during maneuvers, then aerodynamic inefficiencies occur, but reducing rotor moments requires additional control mechanisms
Solution Approach 1:
The feedback control system continuously monitors maneuver parameters through sensors and adjusts cyclic pitch in real-time to minimize rotor moments during aerodynamic maneuvers. This active feedback control maintains optimal aerodynamic efficiency by dynamically counteracting moment generation rather than relying on fixed geometric configurations or additional mechanical control mechanisms.
Solution Approach 2:
The system improves aerodynamic efficiency by dynamically changing rotor pitch parameters in response to detected angular velocity and acceleration. Rather than adding mechanical control mechanisms, the invention optimizes aerodynamic performance by adjusting pitch parameters through electronic control, thereby reducing rotor moments and energy loss without proportionally increasing device complexity.
Data Source
AI summary
A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment.