Tail Sitter Aircraft Refueling System with Movable Fuel Tanks
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Solution Overview
Problem
Conventional VTOL aircraft lack efficient refueling capabilities, both in-flight and on the ground, which is a tactical need for missions requiring long range and endurance, and existing configurations often compromise on complexity, weight, and efficiency.
Innovation Solution
A tail sitter aircraft with proprotors and a refueling system that includes fuel tanks and a hose and drogue system, powered by an auxiliary power unit, allowing for both aerial and ground refueling, and featuring foldable wings and rotor blades for reduced size and increased operational flexibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If tilt-wing or tilt-rotor features are added to achieve VTOL capability with long range and endurance, then the aircraft can perform both vertical and horizontal flight, but the device complexity and empty weight increase significantly
Solution Approach 1:
The aircraft is divided into functionally independent segments: fixed horizontal wings for forward flight and separate vertical proprotors for VTOL operations. This segmentation allows each component to be optimized for its specific function without the complexity of integrated tilt mechanisms, resolving the contradiction between VTOL capability and device complexity
Solution Approach 2:
The proprotors serve multiple functions: they provide vertical lift during VTOL operations and can be positioned to contribute to forward thrust during horizontal flight. This multi-functionality achieves versatility without requiring separate specialized systems for each flight mode, reducing overall device complexity
2Adaptability or versatility
If tilt-wing or tilt-rotor features are added to achieve VTOL capability with long range and endurance, then the aircraft can perform both vertical and horizontal flight, but the empty weight increases
Solution Approach 1:
By separating the VTOL function into independent proprotor units rather than integrating tilt mechanisms into the entire wing structure, the weight penalty is localized to specific components rather than the entire aircraft structure, reducing overall empty weight increase
Solution Approach 2:
The VTOL capability is extracted as a separate functional system (proprotors) rather than being integrated into the main wing structure. This extraction allows the fixed wings to remain lightweight and optimized for forward flight while adding only the necessary weight for vertical operations, minimizing the empty weight penalty
3Speed
If conventional fixed wing aircraft are used for long range missions, then efficient forward flight is achieved, but VTOL capability is lost
Solution Approach 1:
The aircraft combines fixed horizontal wings optimized for efficient forward flight with separate vertical proprotors for VTOL operations. This segmentation allows each system to be optimized for its primary function while working together to provide both forward flight efficiency and VTOL capability
Solution Approach 2:
The invention merges two distinct flight capability systems (fixed-wing forward flight and rotorcraft VTOL) into a single integrated aircraft platform. The fixed wings provide efficient forward flight while the proprotors provide VTOL capability, achieving a combination that neither system could provide alone
4Duration of action of moving object
If refueling system is added to enable aerial and ground refueling, then mission duration is extended, but device complexity increases
Solution Approach 1:
The refueling system is designed with multi-functionality to handle both aerial refueling (via hose and drogue) and ground refueling operations through a single integrated apparatus. This universal design extends mission duration without proportionally increasing complexity, as one system performs multiple refueling functions
Solution Approach 2:
The refueling system incorporates dynamic components including deployable hoses, movable fuel tanks, and adjustable positioning mechanisms that allow the system to adapt between aerial and ground refueling modes. This dynamic flexibility enables extended mission duration while managing complexity through adaptive rather than static design
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 tactical refueling options for VTOL aircraft, enhancing mission duration and flexibility with reduced complexity and weight, and allowing operations from small decks and varied environments.
Implementation Method 1
an auxiliary power unit configured to power a fuel transfer between the at least one fuel tank and the refueling apparatus
Implementation Method 2
a hose and drogue system fluidly communicative with the at least one fuel tank
Data Source
AI summary
An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations.