Tiltrotor Propulsion Units for VTOL Flight Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current vertical takeoff and landing (VTOL) and vertical/short takeoff and landing (V/STOL) aircraft designs face challenges in efficiently providing propulsion and control for vectored thrust flight and aerodynamic flight, particularly in generating controlling moments about three orthogonal axes while maintaining simplicity and cost-effectiveness.
Innovation Solution
A system comprising at least three propulsion units, where two are tiltable and one is non-tiltable, allowing for independent control of thrust vectors and tilting to provide vertical and longitudinal thrust, and generate control moments for pitch, roll, and yaw during vectored thrust and aerodynamic flight, with the tiltable units capable of tilting between vertical and longitudinal thrust directions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If separate powerplants are used for vertical and horizontal thrust, then propulsion efficiency is improved, but device complexity increases
Solution Approach 1:
The patent employs propulsion units that can perform multiple functions - generating both vertical thrust for takeoff/landing and horizontal thrust for forward flight. The tiltable propulsion units can redirect their thrust vectors to provide different flight modes, eliminating the need for separate powerplants for vertical and horizontal propulsion while maintaining propulsion efficiency
Solution Approach 2:
The propulsion units are designed with tilting mechanisms that allow dynamic adjustment of thrust vector direction. This dynamic capability enables the same propulsion units to adapt between vertical and horizontal thrust generation, resolving the contradiction by providing multi-functionality without requiring separate static powerplant systems
2Adaptability or versatility
If tiltable propulsion units are used for vectored thrust flight, then flight control capability is improved, but device complexity increases
Solution Approach 1:
The tiltable propulsion units serve multiple purposes: they provide vertical thrust for hover, horizontal thrust for forward flight, and generate control moments for pitch, roll, and yaw. This multi-functionality improves flight control capability while avoiding the need for separate control systems, thereby managing device complexity
Solution Approach 2:
The patent merges the functions of propulsion and flight control into a single integrated system. The tiltable propulsion units simultaneously provide thrust and generate control moments, combining what would traditionally require separate propulsion and control systems into one unified mechanism, thus improving control capability without proportionally increasing complexity
3Stability of the object's composition
If three or more propulsion units are used for generating control moments, then flight stability is improved, but device complexity increases
Solution Approach 1:
The patent positions propulsion units at specific locations on the airframe (including lateral separation and forward/aft positioning) to create inherent stability characteristics. The third propulsion unit is positioned to provide pitch balance, while the lateral arrangement of units generates rolling and yawing moments. This strategic local positioning achieves flight stability without requiring additional complex control mechanisms
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
Enables efficient and controlled flight operations in both vectored thrust and aerodynamic modes with reduced complexity and cost, providing pitch balance and allowing for autonomous point vertical landing, hover, and aerodynamic flight capabilities.
Implementation Method 1
at least three propulsion units... providing a thrust for enabling vectored thrust flight and aerodynamic flight
Data Source
Figure 1~2
Figure 3(a)~3(c)
Figure 4~6
AI summary
According to one aspect of the invention there is provided a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, in which at least three propulsion units provide vertical thrust for vectored thrust flight, and in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle. The control moments are generated by selectively varying the thrust generated by each of the propulsion units independently of one another, and: by selectively vectoring the thrust of one propulsion unit with respect to each of two independent tilt axes independently of one another, or by selectively vectoring the thrust of each of two propulsion units with respect to a respective tilt axis, independently of one another.