Self-Righting Drone Frame with Counter-Rotating Rotors
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Solution Overview
Problem
Remote-controlled model helicopters with single main rotors require a tail rotor for stability, limiting their operation to designated areas and necessitating user intervention to right the vehicle after non-upright landings, restricting hobbyist participation due to complexity and expertise requirements.
Innovation Solution
A self-righting frame assembly with vertically oriented frames, a weighted mass positioned near the bottom, and a protrusion at the top to initiate self-righting when inverted, combined with counter-rotating rotors for stability and remote control operation, allowing the vehicle to automatically return to an upright position.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a single main rotor helicopter design is used, then the vehicle can achieve vertical take-off and landing capability, but the vehicle becomes unstable and requires a tail rotor for counter-torque control
Solution Approach 1:
The patent removes the tail rotor component entirely from the helicopter design. By using a dual counter-rotating main rotor configuration instead of a single main rotor with tail rotor, the system eliminates the need for tail rotor counter-torque control, thereby simplifying the overall device structure while maintaining stability
Solution Approach 2:
The patent combines the functions of two main rotors that counter-rotate to simultaneously provide lift and counteract torque effects. This merging of functions eliminates the need for a separate tail rotor system, reducing device complexity while maintaining vertical take-off and landing capability
2Reliability
If the helicopter lands in a non-upright position, then the vehicle may be stable on the ground, but user intervention is required to right the vehicle for further operation
Solution Approach 1:
The patent incorporates a self-righting mechanism using a weighted mass positioned at the bottom of the frame and a protrusion at the top. When the vehicle lands in a non-upright position, gravity acting on the weighted mass automatically rights the vehicle to its upright orientation without requiring user intervention, thereby maintaining reliability while improving ease of operation
Solution Approach 2:
The patent uses a weighted mass positioned at the bottom of the frame structure to create a counterbalancing effect. This weighted mass acts as a counterweight that, combined with the top protrusion, ensures the vehicle automatically returns to its upright position after landing, eliminating the need for manual reorientation
3Stability of the object's composition
If a tail rotor is added for stability, then the helicopter can maintain directional control, but the vehicle requires a larger size and more complex control systems
Solution Approach 1:
The patent combines the stability function and torque counteraction into the dual main rotor system itself. The counter-rotating rotors provide both lift and directional stability without requiring a separate tail rotor, thereby maintaining stability while reducing device complexity
Solution Approach 2:
The patent removes the tail rotor component from the design, extracting the unnecessary element that added complexity. The dual counter-rotating main rotors alone provide sufficient stability and control, eliminating the need for additional stabilizing components
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 remote operation of model helicopters without user intervention for reorientation, simplifying handling and expanding operational areas by ensuring the vehicle can autonomously return to an upright state after non-upright landings, thus reducing the complexity and expertise needed for operation.
Implementation Method 1
A weighted mass is mounted within the frame assembly and positioned proximate to a bottom of the frame assembly along the central vertical axis for the purpose of positioning a center of gravity of the frame assembly proximate to a bottom of the frame assembly
Implementation Method 2
At a top of the vertical axis, include a protrusion extending above the vertical frames for providing an initial instability to begin a self-righting process when the frame assembly is inverted
Data Source
AI summary
An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.