Rocket Nozzle Exit Teeth for Symmetric Flow and Lower Side Loads
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Solution Overview
Problem
Conventional rocket engines experience lateral forces due to asymmetric jet separation at the nozzle exit, leading to increased weight and reduced payload, as ambient air flows into the nozzle during startup or shutdown, causing asymmetric flow structures.
Innovation Solution
A launch platform with inwardly projecting teeth at the nozzle's trailing edge disrupts the flow to create symmetrical flow patterns, reducing side loads by incorporating an ablative material that dissolves with increasing temperature, minimizing weight and performance losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the rocket engine nozzle is designed to withstand lateral forces from asymmetric jet separation, then the structural strength is improved, but the weight of the nozzle and engine components increases
Solution Approach 1:
The teeth on the launch platform create preliminary flow disturbances that prevent asymmetric jet separation before it can occur. By disrupting the ambient air flow and combustion gas flow at the nozzle exit plane, the teeth eliminate the formation of large-scale asymmetric flow structures that would otherwise generate lateral forces requiring additional structural reinforcement.
Solution Approach 2:
The launch platform with teeth acts as an intermediary element between the ambient air and the combustion gases at the nozzle exit. This intermediary structure mediates the interaction between the two fluid streams, creating a more symmetric mixed flow pattern that reduces lateral forces on the nozzle while allowing the nozzle to maintain lighter construction.
2Weight of moving object
If the teeth are made of ablative material to minimize weight and performance losses, then the weight is reduced, but the reliability during normal operation may be affected
Solution Approach 1:
The ablative teeth perform their flow disruption function during the preliminary phase of rocket operation (startup and throttling) when asymmetric jet separation is most problematic. Once this preliminary flow conditioning is achieved, the teeth are consumed by ablation, eliminating the need for long-term structural reliability during normal high-temperature operation.
Solution Approach 2:
The teeth are designed as disposable ablative components that serve their purpose during critical transient phases and are then consumed. This approach allows using simple, lightweight ablative materials rather than requiring high-strength, high-temperature resistant materials that would be necessary for permanent components, significantly reducing weight while maintaining reliability for the duration needed.
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 toothed launch platform improves flow symmetry, reducing side loads on the nozzle and maintaining optimal performance without increasing the engine's weight, as the teeth dissolve during normal operation.
Implementation Method 1
The tooth group is made of an ablative material that dissolves in the combustion gases
Data Source
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AI summary
The present disclosure comprises a launch platform for a rocket engine and a nozzle (210) for a rocket engine, each having an inwardly projecting tooth group (110). The tooth group comprises a plurality of teeth arranged at an exit edge (212) of the nozzle (210) of the rocket engine and projecting into the outflowing combustion gases.