Solid Booster Igniter Ejection for Controlled Combustion Extinction
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Solution Overview
Problem
Solid propellants for launchers face challenges in controlling combustion duration and extinction, leading to asymmetrical thrust and complex manufacturing due to the self-sustaining nature of combustion and the difficulty in creating evacuation channels for Thrust Stop Devices.
Innovation Solution
A solid propellant design featuring an igniter ejection system with a pyrotechnic cutting system and chimney to open the combustion channel externally, allowing controlled gas leakage and extinction without requiring an evacuation channel, ensuring controlled combustion cessation and reduced residual thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If an evacuation channel is created in the propellant to stop combustion using a Thrust Stop Device, then combustion extinction can be controlled, but the manufacture of the propellant becomes complex
Solution Approach 1:
The invention extracts the combustion channel closure function from the propellant body itself and relocates it to a separate igniter component. The igniter acts as a movable closure for the combustion channel, which can be ejected when combustion needs to be stopped. This separates the combustion control function from the propellant manufacturing process, eliminating the need to create evacuation channels in the propellant while maintaining reliable combustion extinction control.
2Power
If solid propellants are used for boosters, then high thrust is generated for small volume with ignition reliability, but combustion duration cannot be controlled due to self-sustaining combustion
Solution Approach 1:
The invention makes the combustion channel closure dynamic by using an ejectable igniter. During normal operation, the igniter remains in place closing the combustion channel and allowing self-sustaining combustion for high thrust. When combustion duration needs to be controlled, the igniter can be ejected to open the channel and allow gas leakage, thereby stopping combustion. This dynamic approach maintains the benefits of solid propellants while adding combustion duration control capability.
3Power
If multiple booster propellants are used for the same stage, then thrust is increased, but they do not necessarily extinguish at the same time resulting in asymmetrical thrust
Solution Approach 1:
The invention enables controlled extinction of multiple booster propellants through a common control system that can monitor and coordinate the ignition state of each propellant. By using the ejectable igniter mechanism, the control system can ensure that all boosters are extinguished simultaneously or in a coordinated sequence, maintaining thrust symmetry even when multiple propellants are used. This feedback-controlled approach eliminates the random extinction timing that causes asymmetrical thrust.
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 precise control over combustion extinction, eliminates asymmetrical thrust, simplifies propellant manufacturing, and reduces the risk of collision during separation by generating a recoil force, ensuring safe and symmetrical shutdown of multiple propellants.
Implementation Method 1
a pyrotechnic cutting system configured to allow the combustion channel to be opened... a leak of gases internal to the propellant is generated through the combustion channel, which results in a reduction of the internal pressure in order to stop combustion
Implementation Method 2
The igniter is a gas generator that increases the pressure in the propellant until it initiates combustion of the propellant. Combustion generates gases, which maintain the pressure that allows further combustion.
Implementation Method 3
the chimney of the propellant being oriented so as to generate a thrust in the opposite direction to that generated by the rear nozzle during the ejection of the gases, these being oriented in a direction making it possible to obtain a recoil force relative to the rest of the launcher
Data Source
Figure 1A~2
Figure 3A~3C
AI summary
Solid booster (14) for a launcher, the booster being suitable for being separated from the rest of the launcher and comprising a wall (18) defining a combustion chamber (19) comprising an end, termed a front end (19a), and an opposite end, termed a rear end (19b), propellant (24) arranged in the combustion chamber, a combustion channel (26) passing through the combustion chamber from the front end toward the rear end, a nozzle (22) arranged at the rear end of the combustion chamber, an ignition (28) closing off the combustion channel at the front end of the combustion chamber, a skirt (20) covering the ignition at the front end of the combustion chamber, the skirt allowing the mechanical link with the rest of the launcher, and an ignition ejection system (34, 36, 38).