Rocket Engine Multi-Time Ignition Apparatus
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Solution Overview
Problem
Existing multi-time ignition starting apparatuses for rocket engines are heavy, complex in structure, and have low reliability, limiting their ability for repeated starts, which is a concern for reusable carrier rockets.
Innovation Solution
A multi-time ignition starting apparatus featuring a thrust chamber, generator, turbopump assembly, fuel tank, and oxidizer tank, with interconnected pipelines and valves, allowing for the reuse of gasified fuel and oxidizer, and igniter systems to enable multiple ignition starts with a simple and lightweight design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If two pump bodies are used to convey oxidizer and fuel to the gas generator for multiple repeated starts, then the rocket engine can achieve multiple repeated starts, but the weight of the whole apparatus increases and the structure becomes complicated with low reliability
Solution Approach 1:
The patent combines the functions of two separate pump bodies into a single turbopump assembly. The turbopump assembly includes a turbine driven by combustion gases and a pump section that pressurizes both fuel and oxidizer, eliminating the need for separate pump bodies while achieving multiple repeated starts through the gas generator's ability to refill propellant tanks
Solution Approach 2:
The gas generator serves multiple functions: it generates combustion gases to drive the turbine for pump operation, and simultaneously acts as a propellant storage and refill system. The gas generator can be refilled from the main propellant tanks, enabling multiple repeated starts without requiring separate starting systems for each propellant
2Duration of action of moving object
If two pump bodies are used to convey oxidizer and fuel to the gas generator for multiple repeated starts, then the rocket engine can achieve multiple repeated starts, but the weight of the whole apparatus increases
Solution Approach 1:
The patent combines the functions of two separate pump bodies into a single turbopump assembly. The turbopump assembly includes a turbine driven by combustion gases and a pump section that pressurizes both fuel and oxidizer, eliminating the need for separate pump bodies while achieving multiple repeated starts through the gas generator's ability to refill propellant tanks
Solution Approach 2:
The gas generator serves multiple functions: it generates combustion gases to drive the turbine for pump operation, and simultaneously acts as a propellant storage and refill system. The gas generator can be refilled from the main propellant tanks, enabling multiple repeated starts without requiring separate starting systems for each propellant
3Duration of action of moving object
If two pump bodies are used to convey oxidizer and fuel to the gas generator for multiple repeated starts, then the rocket engine can achieve multiple repeated starts, but the reliability of the apparatus decreases
Solution Approach 1:
The patent combines the functions of two separate pump bodies into a single turbopump assembly. The turbopump assembly includes a turbine driven by combustion gases and a pump section that pressurizes both fuel and oxidizer, eliminating the need for separate pump bodies while achieving multiple repeated starts through the gas generator's ability to refill propellant tanks
Solution Approach 2:
The gas generator serves multiple functions: it generates combustion gases to drive the turbine for pump operation, and simultaneously acts as a propellant storage and refill system. The gas generator can be refilled from the main propellant tanks, enabling multiple repeated starts without requiring separate starting systems for each propellant
4Duration of action of moving object
If gunpowder igniters are used for multiple ignition starts, then the rocket engine can be ignited multiple times, but multiple gunpowder starters must be provided leading to complicated structure
Solution Approach 1:
The gas generator serves multiple functions: it generates combustion gases to drive the turbine for pump operation, and simultaneously acts as a propellant storage and refill system. The gas generator can be refilled from the main propellant tanks, enabling multiple repeated starts without requiring separate starting systems for each propellant
Solution Approach 2:
The gas generator automatically refills itself from the main propellant tanks during engine operation. The refilling is achieved through pressure differential and valve control systems that transfer propellant from the main tanks to the gas generator, enabling the system to prepare for subsequent starts without external intervention
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 apparatus achieves reliable and repeated ignition starts with a reduced weight and complexity, ensuring continuous operation by recycling and replenishing fuel and oxidizer, and allowing for controlled pipeline operations.
Implementation Method 1
the fuel tank being also communicated with the first outlet of the thrust chamber through a first pipeline to fill a gasified fuel, after being heated and gasified by the thrust chamber, from the thrust chamber into the fuel tank
Implementation Method 2
the oxidizer outlet being communicated with an inlet of the oxidizer tank through a second pipeline, the second pipeline being provided with a heat exchanger to heat and gasify an oxidizer output from the oxidizer pump and fill the gasified oxidizer into the oxidizer tank
Implementation Method 3
a generator with a second inlet and a second outlet; a turbopump assembly communicated with the second outlet of the generator
Implementation Method 4
a thrust chamber with a first inlet and a first outlet; a generator with a second inlet and a second outlet
Data Source
Figure 1
AI summary
The present invention relates to the field of space propulsion technology, and in particular, to a multi-time ignition starting apparatus for a rocket engine and a rocket engine having the same. The multi-time ignition starting apparatus for a rocket engine comprises: a thrust chamber with a first inlet and a first outlet; a generator with a second inlet and a second outlet; a turbopump assembly communicated with the second outlet of the generator , having a fuel inlet, an oxidizer inlet, a fuel outlet and an oxidizer outlet, both the fuel outlet and the oxidizer outlet being concurrently communicated with both the first inlet and the second inlet; and a fuel tank and an oxidizer tank, both having outlets concurrently communicated with both the first inlet and the second inlet, the fuel tank being also communicated with the first outlet of the thrust chamber through a first pipeline to fill a gasified fuel from the thrust chamber into the fuel tank. The present invention provides a multi-time ignition starting apparatus for a rocket engine with a light weight, a simple structure and high reliability and a rocket engine having the same.