UAV Launch Tube Clasp Coupling for Rapid Gas Propulsion
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Solution Overview
Problem
Existing methods for launching unmanned aerial vehicles (UAVs) are time-consuming and cumbersome, often requiring manual assembly and launch, and may involve complex uplink guidance systems.
Innovation Solution
A launch tube apparatus featuring a sabot with an expandable skirt and clasp mechanism, utilizing a gas generator to generate high-pressure gas to detachably secure and propel the UAV within the tube, allowing for rapid and efficient launch.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If manual assembly and launch methods are used, then the launch process can be controlled and safe, but the launch time and operational complexity increase significantly
Solution Approach 1:
The UAV is pre-assembled and pre-positioned within the launch tube in an unassembled state, with all components (gas generator, sabot, clasp mechanism) pre-configured. The system requires only insertion of the UAV into the tube and activation of the gas generator, eliminating time-consuming on-site assembly operations while maintaining safety through controlled automated launch.
Solution Approach 2:
The manual mechanical launch process is replaced with an automated gas-powered system. The gas generator produces pressurized gas that automatically propels the UAV through the launch tube via the sabot mechanism, eliminating the need for manual pushing or complex mechanical launch devices, thereby reducing assembly time while maintaining controlled launch.
2Measurement precision
If complex uplink guidance systems are used, then the UAV can be precisely guided and controlled, but the system complexity and operational burden increase
Solution Approach 1:
The patent extracts and eliminates the complex human-in-the-loop uplink guidance system from the launch process. Instead of using complex real-time control systems, the UAV is launched using a simple gas-powered mechanism, and guidance is achieved through preloaded intercept/strike points and onboard inertial navigation, significantly reducing system complexity while maintaining flight precision.
Solution Approach 2:
The UAV employs onboard flight path guidance generators and inertial sensors to navigate autonomously without requiring complex external uplink control. The system uses preprogrammed intercept points and onboard processing to guide the UAV, allowing the vehicle to serve itself rather than requiring complex external guidance systems.
3Reliability
If a secure detachable coupling mechanism is used, then the UAV can be reliably launched, but the device complexity increases
Solution Approach 1:
The coupling mechanism is segmented into simple, discrete components: a clasp element with engagement surfaces that interact with corresponding surfaces on the UAV and sabot. This modular segmentation allows for reliable coupling through multiple engagement points while keeping each individual component simple and easy to manufacture, avoiding complex integrated mechanisms.
Solution Approach 2:
The clasp mechanism utilizes curved or rounded engagement surfaces that allow for smooth insertion and secure locking. The spherical or curved geometry of the engagement surfaces provides inherent alignment and secure coupling through simple geometric interlocking, eliminating the need for complex multi-component coupling mechanisms while ensuring reliable UAV-sabot attachment.
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 quick and reliable launch of UAVs with minimal human intervention, ensuring secure coupling and controlled gas release, enhancing launch efficiency and reducing assembly time.
Implementation Method 1
generation of gas by the gas generator pushes the expandable skirt off of the gas generator by breaking the detachable binding of the adhesive
Implementation Method 2
The expandable skirt may be axially restrained within the tube using an adhesive, and the adhesive may detachably bind the expandable skirt about a shell within the tube
Implementation Method 3
The expandable skirt may be axially restrained within the tube using an adhesive, and the adhesive may detachably bind the expandable skirt about a shell within the tube
Implementation Method 4
a sabot with an expandable skirt and clasp mechanism, utilizing a gas generator to generate high-pressure gas to detachably secure and propel the UAV within the tube
Implementation Method 5
the clasp is rotationally constrained by the inner circumferential wall and the first clasp tab
Implementation Method 6
the inner circumferential wall prevents the clasp from slipping off of the second clasp tab while the UAV is in the tube
Data Source
AI summary
An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.