UAV Catapult Launcher with Multi-Rail Elastic Tensioning
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Solution Overview
Problem
Current UAV launch systems face challenges in rapidly and efficiently launching multiple UAVs, especially in remote areas, due to inefficiencies and misalignment issues in multi-rail systems, and require a compact, portable design with minimal consumables.
Innovation Solution
A catapult UAV launcher system utilizing multiple rail systems with independently tensioned elastic units, where the overall force is evenly partitioned across each rail to ensure uniform acceleration and alignment, using a winch and pulley mechanism to elongate elastic units and rapidly launch UAVs with minimal components and consumables.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single rail system is used for UAV launch, then the structure is simpler, but the force application creates misalignment and hysteresis issues
Solution Approach 1:
The launcher is divided into multiple independent rail systems (at least two rails) that work in parallel. Each rail system independently supports and guides the shuttle assembly, distributing the launch forces across multiple pathways. This segmentation eliminates the misalignment and hysteresis problems associated with single-rail systems by providing redundant, synchronized force application points.
2Reliability
If multiple rail systems are used to eliminate misalignment, then launch alignment improves, but the device complexity increases
Solution Approach 1:
Multiple rail systems are merged into a unified launcher structure that shares common components including the shuttle assembly, control systems, and support framework. The rails are integrated through a common base structure and coordinated control mechanism, allowing force distribution across multiple rails while maintaining a cohesive, manageable system architecture rather than treating each rail as a completely separate unit.
3Force
If larger components are used in single rail systems to provide sufficient force, then the launch force is adequate, but the portability and compactness are reduced
Solution Approach 1:
The total launch force requirement is segmented across multiple rail systems, allowing each individual rail to use smaller, lighter components while collectively providing the necessary total force. This distribution enables the use of lighter elastic units and structural elements in each rail compared to a single-rail system that would require one large, heavy component to provide equivalent force.
Solution Approach 2:
The launcher employs elastic units (such as elastic cords or springs) that provide the necessary force through material elasticity rather than heavy mechanical systems. The use of high-strength, low-weight elastic materials allows adequate force generation with minimal weight, enhancing portability while maintaining launch capability.
4Force
If compressed air canisters or other consumables are used to provide motive force, then the launch force is reliable, but the portability and operational independence are reduced
Solution Approach 1:
The launcher uses elastic units that store and release mechanical energy through their inherent elastic properties, eliminating the need for external consumables like compressed air canisters. The system is self-contained, using reusable elastic components that can be reset and fired repeatedly without requiring replenishment of consumable materials, thereby enhancing operational independence and portability.
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 rapid, safe, and effective launch of multiple UAVs with improved portability and operational independence by mitigating hysteresis and misalignment, while reducing the need for large components and consumables.
Implementation Method 1
utilizing a plurality of elastic units such as bungees for motive force. The catapult system partitions an overall force generated by elongation of the elastic units
Implementation Method 2
The catapult system partitions an overall force generated by elongation of the elastic units using a winch into substantially equivalent forces applied within each rail system
Data Source
AI summary
The disclosure provides a rapid UAV launcher comprising an upper shuttle assembly and typically a plurality of rail systems. Each rail system comprises a lower shuttle assembly extending into a rail channel and translating over a rail surface. The rail channels of each rail system e generally parallel. The lower shuttle assembly of each rail system is coupled to a winch strap at a first end and an intermediary rope toward the intended direction of launch. The intermediary rope extends through the rail channel, through a brake disposed in the rail channel, around a pulley, and couples to a forward bungee connector coupled to an elastic unit. During a launch sequence, a rear mounted winch reels the winch strap to pull the lower shuttle assembly toward the winch, elongating the elastic unit, and providing individual tension forces to the lower shuttle assembly of each rail system.