Transformable Wing UAV for High-Speed Transit and Low-Speed Loitering
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Solution Overview
Problem
Current UAV systems employing parachutes are limited by low airspeed, making it difficult to quickly reach and loiter over target areas, especially in military missions, and often require significant power to overcome drag, resulting in shorter time-on-station and limited payload capacity.
Innovation Solution
A UAV system with a vertical fuselage that can transition between fixed-wing and paraglider configurations, allowing for rapid flight to and from operational areas at higher speeds, and then perform missions using powered paraglider flight, with optional wing jettisoning for disposable operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a UAV uses a parachute for descent and low-speed operation, then it can perform precision missions and has simple structure, but it is limited to low airspeed (20-50 mph) and cannot quickly reach target areas
Solution Approach 1:
The UAV employs a transformable wing structure that can dynamically change configuration between fixed-wing mode for high-speed transit and paraglider mode for low-speed mission operations. This dynamic reconfiguration allows the single vehicle to achieve both high speeds and precision control without requiring separate specialized vehicles.
Solution Approach 2:
The UAV is designed as a multi-functional platform that can perform both high-speed transit and low-speed precision missions using the same vehicle. The transformable wing system enables the UAV to switch between configuration modes, making it universally capable of different operational requirements without needing multiple specialized vehicles.
2Ease of operation
If a UAV uses a fixed-wing configuration for high-speed flight, then it can quickly reach target areas, but it cannot perform precision low-speed missions and has limited maneuverability
Solution Approach 1:
The transformable wing system allows the UAV to dynamically adjust its configuration based on mission phase. During high-speed transit, the fixed-wing configuration provides efficient cruise performance. Upon reaching the target area, the wing transforms into a paraglider configuration that enables slow, precise maneuvering for mission execution.
3Speed
If a powered parachute UAV uses high power to overcome drag, then it can achieve higher speeds, but it results in shorter time-on-station and limited payload capacity
Solution Approach 1:
The flight mission is segmented into distinct phases with different configuration modes. The fixed-wing configuration is used for the transit phase where high speed is needed, and the paraglider configuration is used for the mission phase where low speed and energy efficiency are critical. This segmentation allows each phase to operate in its optimal performance regime.
Solution Approach 2:
The UAV changes its aerodynamic parameters by transforming the wing configuration. This parameter change allows the vehicle to have low drag during high-speed transit and low drag during low-speed mission operations, eliminating the need for high power consumption that would otherwise be required to overcome parachute drag at higher speeds.
4Adaptability or versatility
If a UAV is designed as a disposable system with bomb payload, then it can be used for high-risk missions, but it cannot return to starting location and requires wing jettisoning
Solution Approach 1:
For disposable missions, the wings are extracted (jettisoned) from the UAV after the high-speed transit phase. This allows the main body to be simplified for single-use missions while retaining the transformable wing capability for reusable missions. The wing extraction eliminates the need for the UAV to have return 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
Enables faster and more efficient deployment to and from operational areas, increased payload capacity, and extended loiter times, while maintaining the ability to perform missions at higher speeds without the need for extensive power consumption.
Implementation Method 1
The fixed wing configuration allows the vehicle to fly to and from operational areas at much greater speeds than a typical paraglider
Implementation Method 2
The engine and propeller provide thrust
Implementation Method 3
a paraglider, which is limited in its forward speed due to the drag of the paraglider chute to around 20 miles per hour
Implementation Method 4
control lines from the guidance system are pulled or released to deform a portion of the parachute, causing the parachute to change direction
Data Source
AI summary
A remotely controlled or autonomously controlled UAV is disclosed. The UAV has both wings and a deployable parachute to enable both fixed wing flight and paraglider flight. The UAV can fly at a higher speed to a mission area as a fixed wing craft, and loiter over the area as a powered paraglider. In some embodiments, the wings are jettisoned over the mission area and the UAV configured as a powered paraglider completes its mission. In other embodiments the UAV flies to the mission area as a fixed wing craft, deploys the parachute to loiter as a powered paraglider and then jettisons the parachute to fly under a fixed wing back to a base. The former embodiment cannot fly back to a base, they may be used to carry and deploy bombs or grenades, while the latter may be used for surveillance, deliver supplies or the like.