Variable-Torque UAV Propellers for Motor-Out Flight Control
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Solution Overview
Problem
Current unmanned aerial vehicles (UAVs) face design tradeoffs between agility and energy efficiency, and lack control in degraded operational states such as motor out situations, limiting their ability to maintain stability and maneuverability.
Innovation Solution
The implementation of a hexagonal ring wing design with six propulsion mechanisms that can adjust force-torque ratios by deploying, extending, rotating, or expanding propeller blades to maintain control and safety, even in degraded states, allowing the UAV to transition between vertical takeoff and landing (VTOL) and horizontal flight orientations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional fixed-propeller UAV design is used, then manufacturing simplicity is maintained, but controllability in degraded operational states deteriorates
Solution Approach 1:
The propeller is divided into multiple independent adjustable blades rather than a fixed monolithic structure. Each blade can be independently controlled to change its pitch angle or retract, allowing the system to maintain controllability even when some blades or propulsion mechanisms fail, thus improving reliability in degraded states.
Solution Approach 2:
The propeller transitions from a static fixed-pitch design to a dynamic variable-pitch design where blade angles can be adjusted in real-time. This dynamic capability allows the UAV to adapt propeller characteristics during flight to maintain control authority under varying operational conditions, including degraded states.
2Ease of operation
If variable force-torque ratio control is implemented, then maneuverability is improved, but energy efficiency deteriorates
Solution Approach 1:
The system changes the pitch angle parameter of propeller blades to vary the force-torque ratio. By adjusting this single parameter, the UAV can optimize between maneuverability (higher pitch for more torque) and energy efficiency (lower pitch for less drag), allowing dynamic trade-offs based on flight conditions without continuously expending maximum energy.
Solution Approach 2:
The variable pitch mechanism allows periodic adjustment of propeller characteristics during flight phases. During cruise, blades are set to efficient low-pitch angles for energy savings, while during maneuvering, pitch is increased temporarily to provide additional torque, then returned to efficient settings, creating a periodic pattern of high-and-low energy consumption states.
3Adaptability or versatility
If propeller blades are made adjustable for force-torque control, then adaptability is improved, but device complexity worsens
Solution Approach 1:
The adjustable propeller blades serve multiple functions: they provide thrust generation, force-torque ratio control, and failure compensation. This multi-functionality allows a single mechanical adjustment mechanism to handle diverse operational requirements including normal flight, maneuvering, and degraded-state control, reducing the need for separate specialized systems.
Solution Approach 2:
The propeller adjustment system is controlled autonomously based on sensor feedback about vehicle state and environmental conditions. The control system automatically adjusts blade pitches to maintain optimal performance without requiring manual intervention, allowing the system to adapt to changing conditions while keeping the control interface simple.
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 the UAV's controllability and safety by modifying force-torque ratios to compensate for propulsion failures, enabling safe landing and maintaining control in various operational states, while improving energy efficiency and maneuverability.
Implementation Method 1
the additional torque generated due to increased aerodynamic drag may be initiated, controlled, and/or modified to facilitate, improve, or increase controllability of an aerial vehicle
Data Source
AI summary
Systems and methods to improve controllability of an aerial vehicle responsive to degraded operational conditions are described. For example, one or more propeller blades of an aerial vehicle may be modifiable between two or more configurations. The configurations may include a low torque configuration suitable for normal operational conditions, and a high torque configuration suitable for degraded operational conditions. Various aspects or portions of a propeller blade may be modified to increase torque generated by the propeller blade due to drag or air resistance. The additional generated torque may then be used as a source of additional torque to improve controllability of the aerial vehicle responsive to degraded operational conditions.