Pneumatic Drone Launch Tube With Triggered Pressure Release
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Solution Overview
Problem
Existing pneumatic launching devices for drones lack control over the launch pressure, leading to inconsistent drone ejection speed and height, necessitating safety margins to avoid vehicle antennas, and thus are inefficient in rapid deployment.
Innovation Solution
A pneumatic launching device with a pressurization chamber and temporary closure means, utilizing a chemical reaction to generate pressurized gas, which instantly opens at a predetermined trigger pressure to control the launch pressure and ensure reliable ejection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If gas pressure is released progressively or partially as in prior art devices, then the drone can be deployed, but the launch pressure cannot be controlled precisely, resulting in inconsistent ejection speed and height
Solution Approach 1:
The closure means transitions from a static closed state to a dynamic open state instantaneously, allowing the pressurization chamber to rapidly discharge controlled amounts of gas. This dynamic transition enables precise control over launch pressure by regulating the timing and completeness of the opening action, resolving the contradiction between pressure control precision and mechanism complexity.
Solution Approach 2:
The invention changes the parameter of gas discharge from progressive/partial release to instantaneous complete release. By controlling the closure means to open fully and instantly at a predetermined moment, the system achieves precise launch pressure control through parameter change rather than through complex progressive release mechanisms.
2Reliability
If safety margins are added to prevent drone contact with vehicle antennas, then drone safety is improved, but deployment time increases and operational efficiency decreases
Solution Approach 1:
The system incorporates feedback through predetermined trigger pressure values that automatically control the opening of the closure means. This feedback mechanism ensures consistent, reproducible launch pressure and drone ejection parameters, eliminating the need for conservative safety margins while maintaining high reliability. The feedback loop enables precise control that achieves both safety and speed.
Solution Approach 2:
The trigger pressure value is predetermined and set in advance based on precise calculations and testing. This preliminary action establishes the optimal launch parameters before deployment, ensuring that each launch achieves the exact required ejection speed and height without needing additional safety margins, thereby improving both reliability and productivity.
3Manufacturing precision
If conventional pneumatic launching devices are used, then drone deployment is possible, but the ejection speed and height are inconsistent due to lack of pressure control
Solution Approach 1:
The system performs self-service through automatic control of the closure means opening based on predetermined trigger pressure values. The pressurization chamber automatically discharges the precise amount of gas needed by instantaneously opening the closure means when the trigger pressure is reached, eliminating the need for manual pressure regulation and ensuring consistent ejection parameters while simplifying operation.
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 precise control over drone ejection speed and height, allowing reliable and reproducible deployment without safety margins, enhancing operational efficiency.
Implementation Method 1
a chemical reaction to generate pressurized gas
Implementation Method 2
the release of the pressure contained in the chamber generates energy, which in turn propels the drone
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
The invention relates to a device (1) for pneumatic launching of a drone (2), comprising a launch tube (3), a pressurization chamber (6) situated at the rear of the tube (3) and provided with a passage opening (63) leading into the tube (3), and means (7) for temporarily closing the passage opening (63). According to the invention, the temporary closing means (7) are arranged to change from a closed configuration to an open configuration instantaneously under the action of the gas pressure inside the chamber (6), after the latter has reached a trigger pressure, and the cross section of the passage opening (63) is sufficiently large that, instantaneously with the change to the open configuration, the gas pressure prevailing in the chamber (6) and the space located behind the drone (2), then in communication with each other, is the desired launching pressure for the drone (2).