Deployable VTOL Lifters for Fixed-Wing Aircraft Energy Efficiency
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing VTOL fixed-wing aircraft designs face inefficiencies in energy usage due to conflicting requirements for rotary wings during vertical take-off and landing versus horizontal thrust, limiting load capacity, airborne time, and range, especially for unmanned aerial vehicles.
Innovation Solution
A deployable supporting mechanism with an 'X' shaped structure comprising two supporting arms and vertical lifters that can be extended or retracted to optimize lift and thrust efficiency, allowing for vertical take-off and landing while achieving high-speed cruise mode with enhanced aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If rotary wings are designed for vertical take-off and landing with larger diameter and larger pitch, then vertical lift capability is improved, but horizontal thrust efficiency deteriorates
Solution Approach 1:
The rotary wings are designed with adjustable pitch angles that can be dynamically changed between vertical and horizontal flight modes. During vertical take-off and landing, the rotary wings operate at higher pitch angles to generate maximum vertical lift. During horizontal flight, the pitch angle is reduced to optimize thrust efficiency, allowing the same rotary wing structure to serve both functions effectively without the energy penalty of a fixed design
2Force
If fixed-wing aircraft uses large rotary wings for vertical operations, then vertical lift is improved, but horizontal cruise efficiency deteriorates due to increased drag and weight
Solution Approach 1:
The rotary wings can be repositioned and reconfigured dynamically. During vertical operations, they are positioned to provide maximum lift. During horizontal cruise, the rotary wings are tilted forward and operated at reduced pitch angles to function as propellers, minimizing their drag contribution and allowing the fixed-wing aircraft to achieve high-speed cruise efficiency
Solution Approach 2:
The rotary wings serve multiple functions: they provide vertical lift during take-off and landing, transition to horizontal thrust during cruise, and can be reconfigured to minimize drag during high-speed flight. This multi-functionality eliminates the need for separate vertical lift and horizontal thrust systems, reducing overall weight and drag
3Duration of action of moving object
If battery capacity is increased to extend airborne time and range, then flight duration is improved, but weight increases which reduces energy efficiency
Solution Approach 1:
The aircraft dynamically optimizes its energy consumption by adjusting rotary wing pitch angles and operational modes based on flight phase. During vertical operations, maximum power is used for brief periods. During horizontal cruise, the system transitions to efficient propeller mode with reduced pitch angles, significantly lowering power consumption and extending airborne time without requiring proportionally larger batteries
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 solution enables optimal energy efficiency in both vertical and horizontal flight modes, improving load capacity, airborne time, and range by utilizing the lifters outside the storage room during vertical operations and retracting them for high-speed cruise to maximize fixed-wing aerodynamics.
Implementation Method 1
fixed-wing aircraft can generate a lift force itself by its wings moving through airflow
Implementation Method 2
the rotary plane of the rotary wings tilts to a vertical direction so that the thrust force is generated by the rotary wings
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
The present invention discloses a vertical take-off and landing fixed-wing aircraft and the flight control method thereof, the fixed-wing aircraft comprises a fuselage (10), fixed-wings (11) and a thruster (12) both configured on the fuselage. A storage room (13) is configured inside the fuselage (10), a plurality of openings and their corresponding doors (14) are configured on the fuselage (10), and the openings are connected to the storage room (13). A driving mechanism (30), and a deployable supporting mechanism driven by the driving mechanism (30) are arranged inside the storage room (13), and the outer ends of the deployable supporting mechanism are provided with vertical lifters (40). The fixed-wing aircraft can be in an open state and a closed state, in the open state, the doors (14) open and the vertical lifters (40) spread out outside the storage room (13) through the doors (14), by the act of the deployable supporting mechanism; in the closed state, the vertical lifters (40) are located within the storage room (13) by act of the deployable supporting mechanism while the doors (14) closed. The aircraft may operate in high-speed cruise mode or vertical take-off and landing mode, and can reach a working condition of highest energy efficiency in both modes.