Aerodynamic Payload Ejection via Airflow Extraction
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Solution Overview
Problem
Current side-ways eject arrangements for aerial vehicles are inefficient in launching payloads, often resulting in jammed payloads and poor spread of countermeasures due to inadequate launch efficiency and slow ejection.
Innovation Solution
A payload launch arrangement featuring a push-out chamber coupled to an aerodynamic surface with an air intake and internal air transfer arrangement, utilizing an openable closure member to direct airflow for additional push-out force, enabling efficient sideway ejection via a guideway inclined at an acute angle, which enhances the payload's rotational motion and distance from the vehicle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If current side-ways eject arrangements are used, then the structure is simple, but the payload may get jammed in the launch opening and launch efficiency is poor
Solution Approach 1:
The patent introduces a pneumatic ejection system using compressed air stored in a reservoir. The air is directed through a nozzle to create a high-velocity jet that propels the payload out of the launch compartment. This pneumatic mechanism eliminates mechanical contact that could cause jamming, while providing rapid and reliable ejection. The system includes an air reservoir, valve, and nozzle arrangement that works together to generate the necessary thrust for efficient payload deployment.
Solution Approach 2:
The patent extracts the ejection function from traditional mechanical pushers or springs and implements it through a separate pneumatic subsystem. By taking out the ejection mechanism as an independent pneumatic system rather than integrating it mechanically with the payload interface, the design eliminates potential jamming points while maintaining simple overall structure. The air jet acts as a non-contact extraction force that propels the payload without mechanical interference.
2Quantity of substance
If side-ways eject arrangements are used, then the device complexity is low, but the bloom rate is poor and countermeasure spread is insufficient
Solution Approach 1:
The patent employs dynamic ejection by releasing multiple payloads at different times or angles using the pneumatic system. The rapid response capability of the pneumatic actuation allows for dynamic control of payload deployment sequences, enabling improved bloom rate where multiple countermeasures spread out in space and time. The system can adjust ejection timing and patterns to optimize countermeasure distribution without requiring complex mechanical positioning mechanisms.
3Speed
If traditional ejection mechanisms are used, then the structure is simple, but the ejection speed is slow and launch efficiency is poor
Solution Approach 1:
The patent changes the fundamental parameter of ejection force generation from mechanical (gradual force buildup) to pneumatic (rapid pressure-driven force). By utilizing compressed air at high pressure that expands rapidly through a nozzle, the system achieves very high ejection speeds. The key parameter change is transitioning from solid-mechanical force transmission to gas-dynamic force generation, which inherently provides faster response and higher acceleration of the payload.
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
The solution ensures rapid and efficient sideway ejection of payloads without jamming, improving the bloom rate and enabling effective countermeasure deployment, even during high-angle and slow-flying conditions.
Implementation Method 1
an airflow, which during use of the arrangement flows over an aerodynamic surface of the arrangement
Implementation Method 2
lead a separated flow of air divided from the airflow into the push-out chamber and/or the launch compartment
Data Source
AI summary
The present invention concerns a method for launching a payload (3) by means of an arrangement (1), which is configured for storing and launching a payload (3). A launch compartment (5) of the arrangement (1) is configured to eject the payload (3) from the launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1). An air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17).