Coaxial Reversible UAV Propellers for Rotor Failure Stability
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Solution Overview
Problem
Quadcopters face instability and surplus thrust issues due to rotor failure or malfunction, which current solutions, such as emergency parachutes, are unreliable and costly.
Innovation Solution
The implementation of a quadcopter design with co-axial reversible rotors and an autopilot control system that reverses propeller direction and adjusts speed to maintain yaw, roll, and pitch stability by redistributing thrust and torque across functional propellers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If emergency parachute is configured with quadcopter to assist emergency landing, then safety is improved, but device complexity and cost increase
Solution Approach 1:
The patent converts the harmful effect of rotor failure (surplus thrust and instability) into a beneficial control situation by using the autopilot system to detect failure and reverse propeller directions. This active conversion of failure conditions into controllable states eliminates the need for passive safety devices like emergency parachutes, thereby improving reliability while reducing device complexity and cost
2Reliability
If rotor failure occurs in quadcopter, then operational capability is reduced, but flight stability is compromised due to surplus thrust from other rotors
Solution Approach 1:
The patent applies inversion by reversing the rotation direction of functional propellers when failure is detected. Instead of attempting to maintain original thrust directions, the system inverts propeller directions to counteract surplus thrust from failed rotors, thereby restoring flight stability while adapting to reduced operational capability
3Ease of operation
If all four rotors are used for control and maneuverability, then maneuverability is maintained, but inherent instability remains and all rotors are required for control
Solution Approach 1:
The patent implements feedback through the autopilot control system that continuously monitors rotor status and automatically adjusts propeller directions and speeds in response to detected failures. This closed-loop feedback mechanism maintains flight stability and maneuverability by dynamically adapting control strategies based on real-time system state, eliminating the need for all four rotors to maintain control
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 solution effectively stabilizes the quadcopter in case of rotor failure, balancing thrust and torque, ensuring safe flight by reversing propeller direction and adjusting speed to counteract surplus thrust and torque imbalances.
Implementation Method 1
Quadcopters are lifted and propelled by four rotors. Quadcopters are inherently unstable and rely on all four rotors for their control and maneuverability.
Implementation Method 2
each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing any failure
Data Source
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AI summary
The present disclosure pertains to a multi-rotor unmanned aerial vehicle (UAV). Aspects of the present disclosure provide a UAV that includes at least four arms, each configured with a co-axial pair of contra rotating propellers, wherein each propeller has capability of rotating reversibly with associated reversal of direction of thrust, and an autopilot control system that controls rotational direction and speed of the at least four co-axial pairs of propellers to maintain yaw stability, roll stability and pitch stability of the UAV, wherein in an event of failure of any one co-axial pair out of the at least four co-axial pairs of propellers, the autopilot control system reverses direction of rotation and thereby direction of thrust of at least one propeller of any functional pair.