Self-Righting Aeronautical Frame with Weighted Apex
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Solution Overview
Problem
Remote-controlled helicopter models require manual reorientation after landing, limiting their operation to specific areas and restricting hobbyists due to the complexity of piloting and structural instability.
Innovation Solution
A self-righting frame assembly with vertically and horizontally oriented frames, a weighted mass, and a protrusion to initiate self-righting, combined with counter-rotating rotors for stability and propulsion, allowing the vehicle to automatically return to an upright position.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a remote-controlled helicopter model is designed with counter-rotating rotors for stability and vertical take-off capability, then the vehicle can operate without runways and provide thrilling flight experience, but the vehicle becomes prone to tipping on one or the other side when landing and requires manual reorientation
Solution Approach 1:
The patent implements a self-righting mechanism that allows the helicopter to automatically return to its proper orientation after tipping or landing on its side. The mechanism includes a weighted frame structure with a center of gravity positioned below the rotor axis, creating a self-correcting stabilizing force that rights the vehicle without requiring manual intervention from the operator.
Solution Approach 2:
The patent employs a weighted frame structure where a counterweight is positioned to create a center of gravity below the rotor axis. This counterweight arrangement provides a restoring moment that automatically corrects tipped positions, preventing the vehicle from remaining in unstable orientations and eliminating the need for manual reorientation.
2Reliability
If a remote-controlled helicopter model is designed with complex piloting requirements and tail rotor for torque counteraction, then the vehicle can achieve stable flight, but the complexity limits the number of hobbyists who can enjoy this activity
Solution Approach 1:
The patent extracts and eliminates the tail rotor component from the helicopter design, using counter-rotating main rotors instead to counteract torque. This simplifies the overall structure by removing the tail rotor assembly, tail boom, and associated control linkages, thereby reducing piloting complexity while maintaining flight stability through the alternative rotor configuration.
Solution Approach 2:
The patent inverts the conventional helicopter rotor arrangement by using two counter-rotating main rotors positioned above the vehicle instead of a single main rotor with a tail rotor. This inverted configuration naturally counteracts torque through equal and opposite rotational forces, eliminating the need for tail rotor-based torque compensation and simplifying the control system.
3Productivity
If a remote-controlled helicopter model tips on one side during landing, then the vehicle must be righted for further operations, but this requires the operator to walk to the remote location of the vehicle and right it manually
Solution Approach 1:
The patent implements a self-righting mechanism that allows the helicopter to automatically return to its proper orientation after tipping or landing on its side. The mechanism includes a weighted frame structure with a center of gravity positioned below the rotor axis, creating a self-correcting stabilizing force that rights the vehicle without requiring manual intervention from the operator.
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 helicopter-like RC models without manual reorientation, expanding operational areas and simplifying piloting by ensuring the vehicle can autonomously return to an upright state after landing.
Implementation Method 1
a weighted mass carried by a lower section of the frame assembly for the purpose of positioning a center of gravity of the frame assembly proximate to a bottom of the frame assembly
Implementation Method 2
an apex formed at a top of the at least one generally vertically oriented frame member for providing an initial instability to begin a self-righting process when the frame assembly is off-kilter
Data Source
AI summary
An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting dome shaped vehicle body has an apex/protrusion preferably at a top of a central vertical axis. The apex/protrusion provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting body 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 supporting surface. The body provides self-righting functionality and protection of elements carried therein.