Rocket Engine Thermal Conditioning During Concurrent Propellant Filling
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Solution Overview
Problem
Existing cryogenic fuel filling systems require a significant time to develop static head pressure for thermal conditioning of rocket engines, delaying launch readiness, and some launch vehicles lack the necessary height to generate this pressure.
Innovation Solution
Implementing a flow director to divert a portion of the cryogenic propellant flow into the rocket engine's chill line concurrently with tank filling, eliminating the need for static head pressure development and reducing the reliance on recirculation pumps.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cryogenic propellant is provided to chill line for thermal conditioning of rocket engine, then rocket engine is thermally conditioned, but launch readiness is delayed due to time required to fill tank to requisite height
Solution Approach 1:
The flow director enables preliminary thermal conditioning action by directing propellant flow to the chill line before the tank reaches requisite fill height. This allows the rocket engine to be thermally conditioned in advance during the tank filling process, eliminating the sequential delay between filling and conditioning.
Solution Approach 2:
The flow director maintains continuous useful action by simultaneously performing tank filling and engine thermal conditioning operations. Propellant flows continuously to both the tank and the chill line, ensuring that thermal conditioning occurs continuously throughout the filling process rather than being interrupted or delayed.
2Productivity
If static head pressure is used to drive flow of cryogenic propellant to chill line, then propellant flows through engine, but significant tank height is required which increases vehicle size
Solution Approach 1:
The flow director acts as an intermediary device that redirects propellant flow to the chill line. It mediates between the propellant source and the chill line inlet, enabling flow to be directed to the engine without requiring the propellant to accumulate to a height that generates sufficient static head pressure.
Solution Approach 2:
The flow director replaces the mechanical system relying on gravitational static head pressure with a flow redirection mechanism. Instead of using the weight of accumulated propellant to drive flow, the flow director actively directs propellant to the chill line, substituting a mechanical flow control approach for a passive gravitational approach.
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 rapid thermal conditioning of rocket engines, reducing launch readiness time and allowing for more compact vehicle designs by eliminating the need for additional equipment, thus achieving quicker launch and re-launch capabilities.
Implementation Method 1
the cryogenic rocket propellant is provided to a chill line of a rocket engine to thermally condition the rocket engine
Implementation Method 2
the cryogenic rocket propellant is provided to a chill line of a rocket engine to thermally condition the rocket engine
Implementation Method 3
a flow director to direct at least a portion of a flow of the rocket propellant to the chill line
Data Source
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AI summary
Concurrent rocket engine pre-conditioning and tank filling is disclosed. An apparatus includes an inlet valve (212) to supply a rocket propellant tank (202) that is associated with a rocket engine (210) with rocket propellant, a flow director (503) to direct at least a portion of a flow of the rocket propellant from the inlet valve (212) to a chill line (218) of the rocket engine to thermally condition the rocket engine as the rocket propellant tank is being filled with the rocket propellant, and a bypass branch (508) that extends from an exit of an engine bleed line (217) to a bypass valve (512) of the rocket propellant tank.