Fixed-Structure VTOL Aircraft Dual Flight Control Systems
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft designs face limitations in both fixed-wing and multi-rotor technologies, with fixed-wing aircraft requiring ground sliding or special launching and recovering devices for takeoff and landing, and multi-rotor aircraft having inefficient power consumption and limited flight speed and duration, while existing hybrid schemes are complex and heavy, posing risks due to asymmetric lift forces.
Innovation Solution
A fixed-structure vertical takeoff and landing aircraft utilizing two independent or integrated flight control systems, comprising multi-rotor and fixed-wing systems, with engines connected to the fuselage or wings, allowing for flexible switching between flight modes using a manual control module, GPS, and power source, enabling vertical takeoff and landing, and high-speed cruising without complex mechanical variable-shaft structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a mechanical variable-shaft structure is used to incline engines for flight mode switching, then the thrust direction can be rotated, but the structure becomes complex and accessories become heavy
Solution Approach 1:
The flight control system is segmented into two independent systems: a multi-rotor flight control system for vertical takeoff and landing, and a fixed-wing flight control system for high-speed cruising. Each system independently controls specific engines without requiring mechanical repositioning, thereby avoiding complex variable-shaft structures while maintaining flight mode adaptability
Solution Approach 2:
The patent replaces the mechanical variable-shaft engine inclining system with an electronic flight control system. The multi-rotor system uses electronic control to adjust rotor speeds for vertical flight, while the fixed-wing system uses electronic throttle control for forward flight, eliminating the need for mechanical engine repositioning mechanisms
2Adaptability or versatility
If engines are inclined for flight mode switching, then thrust direction can be controlled, but the positions of wings and engines are limited by the center of gravity
Solution Approach 1:
The aircraft is divided into functionally independent rotor and fixed-wing segments with separate control systems. The multi-rotor system manages vertical flight engines independently from the fixed-wing system, allowing engines to be positioned optimally for each function without being constrained by center of gravity requirements for mechanical inclining
3Adaptability or versatility
If multi-rotor and fixed-wing systems are integrated with mechanical connection, then flight mode switching is possible, but the structure becomes complex and heavy
Solution Approach 1:
The aircraft employs two independent flight control systems rather than a mechanically integrated system. The multi-rotor flight control system and fixed-wing flight control system operate independently with separate control channels, eliminating the need for heavy mechanical coupling structures while achieving dual flight mode capability
Solution Approach 2:
The patent substitutes mechanical integration between multi-rotor and fixed-wing systems with independent electronic control systems. Each system has its own control channels that can be independently activated, removing the need for complex mechanical connection structures and reducing overall aircraft weight
4Ease of operation
If ground sliding or special launching devices are used for fixed-wing aircraft, then takeoff and landing can be achieved, but the system becomes complex and requires additional infrastructure
Solution Approach 1:
The aircraft combines multi-rotor and fixed-wing capabilities into a single platform that can perform both vertical takeoff and landing like a multi-rotor, and high-speed cruising like a fixed-wing. This eliminates the need for ground sliding or special launching devices by making the aircraft itself multi-functional
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 aircraft achieves efficient and reliable flight by freely switching between multi-rotor and fixed-wing modes, reducing complexity and weight, enhancing flight efficiency, and lowering costs, while being suitable for both unmanned and manned aircraft, applicable in civil and military aviation.
Implementation Method 1
the engines are internal combustion engines or motors or jet engines or rocket engines
Implementation Method 2
The advancing speed of the multi-rotor aircraft is achieved mainly by a rotor disc through the component force generated by inclination of a swash plate
Data Source
AI summary
The present invention discloses a fixed-structure vertical takeoff and landing aircraft based on the two flight control systems. The aircraft comprises an aircraft structure and the flight control systems. The aircraft structure comprises a fuselage, fixed wings, a steering engine system and a plurality of engines installed on the peripheral side of the fuselage or the ends of the fixed wings. The flight control systems include the multi-rotor flight control system and the fixed-wing flight control system which are relatively independent or integrated in the same flight control system. Free switching between a multi-rotor vertical takeoff and landing mode and a fixed-rotor high-speed cruising mode is achieved by controlling opening and closing of output channels of the multi-rotor flight control system and the fixed-wing flight control system relative to the steering engine system and the engines through a computer.