Multirotor Aircraft Fixed Wings and Rotors Energy Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing multirotor aircraft designs face challenges with energy consumption and stability during flight, particularly when relying solely on rotors for lift, leading to uncertain flight attitudes and increased energy use, and are prone to mechanical failures that compromise safety and control.
Innovation Solution
The design incorporates a longitudinal structure with fixed wings generating most lift during cruising and rotary lift surfaces for takeoff and landing, featuring a rigid central framework and contra-rotating rotors to optimize lift and propulsion, reducing energy consumption and enhancing structural integrity and safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If multirotor aircraft use rotors solely for providing lift during cruising flight, then the aircraft can maintain vertical lift capability, but energy consumption increases and range is limited
Solution Approach 1:
The aircraft divides the lift provision function between two separate systems: fixed wings for cruising flight and rotors for vertical lift and maneuvering. This segmentation allows each component to operate in its optimal regime, with fixed wings providing efficient aerodynamic lift during horizontal flight and rotors providing vertical lift when needed.
Solution Approach 2:
The aircraft dynamically transitions between different lift sources based on flight phase. During cruising, fixed wings provide the majority of lift while rotors are reduced to idle or shutdown. During takeoff, landing, or vertical maneuvers, rotors are activated to provide necessary vertical lift. This dynamic adaptation optimizes energy consumption across different flight conditions.
2Adaptability or versatility
If multirotor aircraft use tilting rotor mechanisms to provide both lift and propulsion, then the aircraft can achieve versatile flight modes, but mechanical complexity and weight increase
Solution Approach 1:
The aircraft separates lift generation and propulsion functions into distinct systems. Fixed wings handle lift during cruising, while separate horizontal propellers handle propulsion. This eliminates the need for complex tilting mechanisms that would be required to make rotors perform both functions.
Solution Approach 2:
The fixed wing structure serves multiple purposes: it provides aerodynamic lift during cruising flight and also serves as the mounting structure for the horizontal propellers. This multi-functionality reduces overall system complexity while maintaining flight versatility.
3Ease of manufacture
If multirotor aircraft position rotors directly above fixed wings, then structural integration is simplified, but aerodynamic interference increases and lift generation is reduced
Solution Approach 1:
Instead of positioning rotors in the same vertical plane as the fixed wings (which would cause aerodynamic interference), the rotors are positioned in a different vertical plane - specifically, behind the fixed wings. This spatial separation in the longitudinal dimension eliminates aerodynamic interference while maintaining structural integration.
4Use of energy by moving object
If multirotor aircraft use fewer rotors to reduce weight, then energy consumption decreases, but redundancy and safety are compromised
Solution Approach 1:
The aircraft uses four rotors that can be independently controlled and potentially sacrificed in case of failure. Each rotor is relatively simple and can be shut down individually without compromising the entire aircraft system. This allows for operational redundancy where failed rotors can be replaced or the aircraft can continue operating with reduced rotor functionality.
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 configuration optimizes energy consumption, maintains flight stability, and ensures safe operation by distributing lift and propulsion forces effectively, allowing for redundancy in lift and control functions, thus enhancing the aircraft's mechanical strength and reliability.
Implementation Method 1
a set of fixed lift surfaces having two fixed wings generating the majority of the aerodynamic lift force needed by the aircraft during a cruising stage of flight
Implementation Method 2
a set of rotary lift surfaces having at least six rotors generating the majority of the aerodynamic lift force needed by the aircraft during stages of takeoff and landing
Implementation Method 3
a power plant comprising a plurality of electric motors and at least one electrical energy source: each electric motor driving a respective rotor or else a respective propulsion propeller
Data Source
AI summary
An electrically or hybrid powered multirotor aircraft with complete redundancy on all of its functions of lift, of propulsion, and of control, the aircraft having optimized energy consumption and comprising: a longitudinal structure having two longitudinal beams; a fuselage fastened to the longitudinal structure; two fixed wings serving essentially to provide the aircraft with lift in cruising flight and arranged at respective ends of the longitudinal structure and in a common first plane; at least six rotors serving essentially to provide the aircraft with lift during stages of takeoff and landing, the rotors being arranged in a common second plane distinct from the first plane and parallel to the first plane in such a manner as not to be situated vertically above or below a fixed wing; and two propulsion propellers. An electrical or hybrid power plant serves to drive the rotors and the propulsion propellers in rotation.