Offset Actuator Landing Gear for Heavy-Lift UAVs
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Solution Overview
Problem
Current landing gear systems for small UAVs are prone to structural failure during heavy-lift operations due to high weight and impact forces, leading to damage and loss of the UAV and its cargo.
Innovation Solution
A modular landing gear system with a rigid main body, pivotally connected landing units, and offset electromechanical actuators that transition between extended and retracted orientations, designed to absorb impact forces and prevent actuator failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional retractable landing gear with in-line servos is used, then the gear can retract during flight, but the servos are positioned directly in the impact force path causing structural failure during heavy-lift operations
Solution Approach 1:
The patent repositions the actuators from an in-line configuration (directly in the force path) to an offset configuration (adjacent to but not in the direct path of impact forces). This dimensional change in actuator placement allows the landing gear to maintain retraction capability while removing the actuators from the high-stress impact zone, thereby preventing structural failure during heavy-lift operations
Solution Approach 2:
The patent introduces a mechanical linkage system that acts as an intermediary between the offset actuators and the landing gear skids. This linkage mechanism transmits the actuation force from the offset position to the skids while isolating the actuators from direct impact forces, enabling both retraction function and actuator protection
2Quantity of substance
If heavy-lift operations are performed, then payload capacity increases, but impact forces during landing increase causing servo failure
Solution Approach 1:
By relocating actuators to an offset position adjacent to the landing gear skids rather than directly in line with them, the patent creates a geometric separation that removes the actuators from the direct impact force path. This allows heavy-lift operations to proceed with increased payload capacity while the actuators remain protected from the full magnitude of landing impact forces
Solution Approach 2:
The patent converts the potentially harmful direct impact forces on in-line actuators into a beneficial offset force configuration. The mechanical linkage system channels the impact forces around the actuators rather than through them, transforming what would be a failure condition into a protected operational state that enables heavy-lift capability
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
The system provides a stable platform for landing and secure retraction during flight, preventing actuator damage and ensuring safe operation and cargo transport by distributing impact forces away from the actuators.
Implementation Method 1
The actuators can include linear motors that are offset from the landing unit connection assemblies
Implementation Method 2
The landing units are pivotally connected to the main body so as to transition between an extended orientation for use during setup and landing, and a retracted orientation
Data Source
AI summary
A landing system for a heavy-lift unmanned aerial vehicle includes an elongated main body that is constructed from a rigid material. The main body includes a central aperture and plurality of connectors for engaging complementary connectors located on the bottom of an unmanned aerial vehicle. A pair of landing units that are positioned along two sides of the main body via connection assemblies which transition the landing units between an extended and retracted orientation. A pair of electromechanical actuators are positioned along the main body at locations adjacent to the landing units. The actuators can include linear motors that are offset from the landing unit connection assemblies. The actuators are coupled to the control and power units of an attached unmanned aerial vehicle.