Deployable UAV Wings for Compact Launch and Extended Flight
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current compact configurations of unmanned aerial vehicles (UAVs) are limited in flight range, endurance, and payload capacity, and require external aerodynamic treatments for launch and transition to flight.
Innovation Solution
The UAV features deployable components including telescoping wings, deployable stabilizers, and a propulsion mechanism that automatically deploy upon launch conditions, maintaining roll control and aerodynamic efficiency through a gearbox and fairing system.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If compact configuration is used, then portability and launch ease are improved, but flight range and endurance deteriorate
Solution Approach 1:
The wing is divided into multiple sections (root section and one or more tip sections) that can be independently positioned. The tip sections can be stowed within or alongside the root section during compact configuration, and deployed outward to increase wingspan for extended flight endurance. This segmentation allows the vehicle to transition between compact and extended configurations.
Solution Approach 2:
The wing tip sections are designed to be stowed within the interior of the root section or nested alongside it during compact configuration. This nesting arrangement minimizes the overall vehicle volume while preserving the capability to deploy the full wingspan when needed for extended flight operations.
2Volume of moving object
If compact configuration is used, then portability is improved, but payload capacity deteriorates
Solution Approach 1:
The modular payload can be positioned within the fuselage and configured in different arrangements. When the wing tip sections are stowed, the payload can be positioned to optimize space utilization. When wing tip sections are deployed, the payload configuration can be adjusted to balance the extended wingspan, effectively utilizing the increased structural capacity.
3Duration of action of moving object
If deployable components are added, then flight performance is improved, but device complexity increases
Solution Approach 1:
The wing tip sections are designed to be movable between stowed and deployed positions. This dynamic configuration allows the vehicle to adapt its wingspan based on flight requirements. The movability is achieved through mechanisms that allow the tip sections to be positioned within or alongside the root section, and then deployed outward when needed.
Solution Approach 2:
The wing tip sections are designed to automatically deploy or stow based on flight conditions. The aerodynamic forces and structural mechanisms work together to enable automatic transition between configurations, reducing the need for complex active control systems and minimizing mechanical complexity while maintaining flight performance.
4Length of moving object
If telescoping wing system is used, then wingspan adjustment is improved, but manufacturing complexity increases
Solution Approach 1:
The wing is segmented into a root section and one or more tip sections that can be independently manufactured. Each section can be fabricated separately using standard manufacturing processes, and then assembled through connection mechanisms that allow telescoping or nested positioning. This segmentation simplifies the manufacturing of each individual component while enabling complex overall functionality.
Solution Approach 2:
The wing tip sections are designed to nest within or alongside the root section in the stowed configuration. This nested arrangement uses straightforward geometric relationships and connection points that can be manufactured using conventional techniques, avoiding the need for complex telescoping mechanisms while achieving the same space-saving effect.
Data Source
AI summary
An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.