Hydropneumatic Rocket Launch Device Safety Valve
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Solution Overview
Problem
Existing holding and starting devices for hydro-pneumatically driven model rockets are either mechanically unstable and unsafe or overly complex and expensive, lacking a reliable mechanism for pressure reduction in case of an unsuccessful start.
Innovation Solution
A holding and starting device composed of a monobloc flange and hollow cylinder with pivotable latches and a pretensioned release ring, featuring a safety valve for pressure relief and remote actuation, ensuring secure holding and controlled release of the rocket.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing holding and starting devices are used, then mechanical stability and safety are improved, but device complexity and cost increase
Solution Approach 1:
The device is divided into distinct functional modules: a holding device with clamping arms for securing the rocket, a separate pretensioned release ring mechanism for controlled release, and a safety valve system for pressure relief. This segmentation allows each component to be optimized independently while maintaining overall simplicity and reliability.
Solution Approach 2:
The release ring is pretensioned in a first rotational direction before use, storing mechanical energy that automatically engages the latches with the locking ring when the rocket is mounted. This preliminary action ensures reliable locking without requiring additional actuators or complex control mechanisms.
2Reliability
If a reliable pressure reduction mechanism is added, then safety is improved, but device complexity increases
Solution Approach 1:
The safety valve is designed to automatically activate when excessive pressure builds up in the system, relieving pressure without requiring external control or additional complexity. The valve serves itself by responding directly to the pressure condition it is designed to protect against.
Solution Approach 2:
The safety valve acts as an intermediary between the pressurized system and the environment, providing a controlled pressure relief path that protects the entire system without requiring complex control logic or multiple safety components.
3Ease of manufacture
If manual pump pressurization is used, then cost is reduced, but productivity and energy efficiency worsen
Solution Approach 1:
The device utilizes hydro-pneumatic principles where compressed air pressurizes water in the rocket body, and the resulting hydro-pneumatic force propels the rocket. This approach is more efficient than purely manual pumping while keeping the pressurization mechanism simple and cost-effective.
Solution Approach 2:
The system changes the physical state and pressure parameters of the propellant (water and compressed air) to achieve efficient propulsion. By optimizing the pressure and composition parameters, the system achieves high productivity with simple, low-cost components.
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 device provides a safe, simple, and cost-effective solution for hydro-pneumatically driven model rockets, ensuring secure pressure generation and riskless pressure reduction in case of an unsuccessful start, allowing for repeated attempts without mechanical instability or high costs.
Implementation Method 1
latches (2) pivotable about a shaft (10), located on the flange (7) and laterally encompassing the hollow cylinder portion (8), and having a latch engagement means (2g) for a locking ring (14) of the aircraft
Implementation Method 2
a release ring (3; 11) rotatably mounted on the base body (1) relative to the longitudinal axis of the hollow cylinder portion (8) and having recesses or setoffs (12) for receiving stop ends (2c) of the respective latch (2), so that a release of the locking ring (14) of the aircraft can take place
Implementation Method 3
a body partially filled with water is driven by means of the previously compressed air located above it. When the nozzle is released, the water exits by means of the compressed air from the rocket body at high velocity and accelerates the rocket body by a reaction effect
Implementation Method 4
a flange (7) that can be connected to it, the flange furthermore merging into a hollow cylinder portion (8) receiving at least one sealing ring (9) arranged at the outer circumference side
Data Source
AI summary
A holding and starting device for hydro-pneumatically driven aircrafts composed of a base body carrying a flange that can be connected to it, the flange furthermore merging into a hollow cylinder portion receiving at least one sealing ring, latches pivotable about a shaft, and having a latch engagement means for a locking ring of the aircraft, and a release ring rotatably mounted on the base body, so that a release of the locking ring of the aircraft can take place. The latches have an actuating surface, which surface causes a pivoting movement of the latches when a nozzle-like neck portion of the aircraft is put on. With or at a rotation of the release ring against pretension, stop ends of the latches move into a respective associated setoff or a respective associated recess, so that the latches release the locking ring for starting.