Multi-Rotor Pitch Control for Redundant Autorotation Flight
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Solution Overview
Problem
Conventional rotorcraft lack advanced technical capabilities for improved maneuverability, redundancy, and energy efficiency, particularly in emergency situations and during cruising flight, due to limitations in rotor system control and propulsion systems.
Innovation Solution
The rotorcraft design features a fuselage with at least three rotor systems, each with individually controllable collective and cyclic pitch, a flight control system, and a forward propulsion unit, enabling advanced steering and autorotation capabilities, including freewheel arrangements for emergency landings and efficient cruising.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional rotorcraft use a single rotor system with basic pitch control, then the device complexity is low, but the maneuverability and steering capability are insufficient
Solution Approach 1:
The rotorcraft is divided into multiple independent rotor systems (at least three), each with its own mast, rotor blades, and pitch control mechanisms. This segmentation allows independent control of each rotor system, enabling advanced maneuverability and steering capabilities while distributing the complexity across multiple modular units rather than a single complex system
Solution Approach 2:
Each rotor system is equipped with individually controllable collective pitch and cyclic pitch mechanisms, allowing dynamic adjustment of blade angles during flight. This dynamic control capability enables the rotorcraft to perform complex maneuvers, transition between flight phases, and maintain stability through real-time pitch adjustments without requiring an overly complex mechanical structure
2Reliability
If conventional rotorcraft lack individually controllable cyclic pitch on multiple rotor systems, then the device complexity is reduced, but the flight redundancy and safety in emergency situations deteriorate
Solution Approach 1:
The rotorcraft is designed with at least three rotor systems, each equipped with individually controllable collective and cyclic pitch, creating built-in redundancy before emergencies occur. This allows the aircraft to maintain controlled flight even if one or more rotor systems fail, as the remaining systems can compensate through differential pitch control. The overlapping flight phases capability ensures safe transitions are maintained even with reduced rotor functionality
Solution Approach 2:
The flight control system dynamically adjusts pitch parameters (collective and cyclic) across multiple rotor systems to maintain stability and control. By changing pitch parameters individually on each rotor system, the aircraft can compensate for failures, redistribute loads, and maintain safe operation across all flight phases including hover, transition, and forward flight
3Use of energy by moving object
If conventional rotorcraft use basic propulsion systems without forward propulsion units, then the device complexity is low, but the energy efficiency during cruising flight is insufficient
Solution Approach 1:
The rotorcraft integrates multiple rotor systems that can serve dual functions: providing lift during vertical flight phases and providing forward thrust during cruising flight. The forward propulsion unit complements the rotor systems to enable efficient forward flight. This multi-functionality allows the same rotor systems to contribute to both vertical and horizontal propulsion, improving overall energy efficiency without requiring entirely separate propulsion systems
Solution Approach 2:
The rotor systems maintain continuous useful action across all flight phases by transitioning smoothly between vertical lift generation and forward thrust production. The overlapping flight phases capability ensures that there is always at least one rotor system contributing effectively to propulsion, whether in hover, transition, or forward flight, maximizing energy utilization without interruption or waste
4Reliability
If conventional rotorcraft lack overlapping flight phases capability, then the device complexity is reduced, but the safety during transitions and emergency landings deteriorates
Solution Approach 1:
The rotorcraft employs dynamic pitch control on at least three rotor systems, each with individually controllable collective and cyclic pitch, enabling smooth transitions between different flight phases. The flight control system continuously adjusts pitch parameters to maintain stability during transitions from hover to forward flight and during autorotation maneuvers, ensuring safe operation without requiring overly complex mechanical transition mechanisms
Solution Approach 2:
The flight control system dynamically changes pitch parameters across multiple rotor systems to enable and control overlapping flight phases. By adjusting collective and cyclic pitch on individual rotor systems, the aircraft can transition between hover, forward flight, and autorotation while maintaining controlled, safe operation throughout the transition process
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 design enhances flight redundancy, energy efficiency, and maneuverability, allowing safe flight and landing even in case of power failures, with overlapping flight phases that eliminate risks during transitions and ensure safe operation across all flight phases.
Implementation Method 1
an electric rotor motor coupled to the mast for driving the mast
Implementation Method 2
whereupon the rotor blades act as a rotating rotor disc
Implementation Method 3
a main motor coupled to the main mast via a freewheel mechanism for driving the main mast such that the main mast can freewheel autorotate without being driven by the main motor
Data Source
AI summary
Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.