Releasable Pylon UAV for Anti-Aircraft Interception
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Solution Overview
Problem
Current unmanned aerial vehicles (UAVs) lack an effective solution for intercepting and destroying hostile aircraft, particularly in scenarios where they need to transition from vertical takeoff and landing to high-speed forward flight to engage both rotorcraft and fixed-wing aircraft without significant weight or cost penalties.
Innovation Solution
The development of an anti-aircraft UAV system featuring a convertible drone-type aircraft with selectively releasable pylons and rotor systems, equipped with chemical rocket motors for high-speed dash capabilities and tethered propulsion systems to increase the impact radius and interfere with target aircraft systems such as tail rotors or air intakes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the UAV is equipped with propulsion systems permanently attached to the wing, then the structural strength and stability are improved, but the weight increases and the adaptability for different flight modes deteriorates
Solution Approach 1:
The propulsion systems are divided into separable components (pylons) that can be independently attached to or released from the wing, allowing the UAV to reconfigure its weight distribution and aerodynamic properties for different flight modes while maintaining structural integrity when needed
Solution Approach 2:
The pylon attachment system transitions from a static permanent connection to a dynamic releasable connection, enabling the UAV to adapt its configuration in real-time between vertical takeoff mode (pylons attached) and high-speed forward flight mode (pylons released)
Solution Approach 3:
The pylons are temporarily discarded (released) during high-speed forward flight to reduce weight and drag, then can be recovered (re-attached) when vertical lift capability is needed again, optimizing performance for each specific flight phase
2Speed
If the UAV uses chemical rocket motors for high-speed dash capabilities, then the speed is improved, but the weight and cost increase
Solution Approach 1:
Chemical rocket motors are pre-installed on the pylons, ready for immediate activation when high-speed dash capability is required, allowing the UAV to achieve rapid acceleration without carrying the full weight penalty of permanently integrated rocket systems
Solution Approach 2:
The rocket motors are activated only when needed for high-speed dashes, then the pylons with motors can be released to reduce weight for subsequent flight phases, allowing the UAV to access high-speed capability temporarily without permanent weight penalty
3Adaptability or versatility
If the pylons are releasably connected to the wing, then the adaptability and impact radius are improved, but the device complexity increases
Solution Approach 1:
The release mechanism is segmented into independent components distributed at opposite ends of the wing, allowing each pylon to be controlled independently and simplifying the overall system architecture compared to a centralized complex mechanism
Solution Approach 2:
The release mechanism is extracted as a separate functional system from the main airframe, allowing it to be independently designed, tested, and maintained without affecting the core structural integrity of the UAV
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
This solution enables the UAV to effectively engage and incapacitate hostile aircraft by transitioning between helicopter and airplane modes, using tethered propulsion systems to enhance the impact radius and targeting capabilities, thereby improving the system's ability to down or destroy target aircraft with minimal additional weight or cost.
Implementation Method 1
equipped with chemical rocket motors for high-speed dash capabilities
Data Source
AI summary
An anti-aircraft system is described and includes an unmanned aerial vehicle (UAV) comprising a body; a wing connected to the body; and propulsion systems associated with the wing, wherein the propulsion systems comprise pylons releasably connected to opposite ends of the wing such that the propulsion systems may be selectively released from the wing during flight of the UAV.