Vapor Jetting Device Segmented Casing for Spacecraft
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Solution Overview
Problem
Existing vapor jetting devices face challenges such as increased weight due to the need for a foamed metal member in the tank, high thermal energy requirements for propellant gasification, sloshing phenomena during spacecraft posture control, and complex piping connections that are labor-intensive and prone to leaks.
Innovation Solution
A vapor jetting device with a box-shaped casing containing a propellant holding unit, a gas storing unit separated by a partition wall with a communication hole, and a machine housing unit, which reduces the need for extensive piping and allows for improved gas-liquid separation by using a heat spreader to evaporate propellant before it enters the gas storing unit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a foamed metal member is provided inside the tank to hold propellant, then the propellant can be held in air bubbles, but the weight of the tank increases and the entire tank needs to be heated for gasification
Solution Approach 1:
The invention extracts the propellant holding function from the entire tank structure and concentrates it in a specific propellant holding chamber. The tank is divided into multiple chambers, with only the propellant holding chamber containing the propellant in air bubbles configuration, while other chambers serve different functions. This extraction reduces the overall weight compared to filling the entire tank with foamed metal structure.
Solution Approach 2:
The tank is segmented into multiple functional chambers including a propellant holding chamber, a gas holding chamber, and other specialized chambers. This segmentation allows different parts of the tank to have different functions and weight characteristics, reducing the overall weight while maintaining propellant holding capability in the specific chamber where it is needed.
2Device complexity
If the entire tank is heated to gasify the propellant, then the propellant can be evaporated, but enormous thermal energy is required
Solution Approach 1:
Heating is applied locally to the propellant holding chamber rather than heating the entire tank. The propellant holding chamber is specifically designed to receive thermal energy for gasification, while other chambers remain at different temperatures. This local heating approach dramatically reduces the thermal energy required compared to heating the entire tank structure.
Solution Approach 2:
The tank is divided into thermally zones with different temperature characteristics. The propellant holding chamber is the primary zone for heating and gasification, while other chambers serve different thermal functions. This thermal segmentation reduces the total mass that needs to be heated, lowering energy consumption.
3Volume of stationary object
If the propellant storage space and gas reserving space are placed close to each other, then the apparatus size is reduced, but the propellant moves into the gas reserving space during posture control causing sloshing
Solution Approach 1:
The tank is segmented into distinct propellant holding chamber and gas holding chamber separated by partition walls with communication holes. This segmentation maintains close proximity of storage spaces for compactness while preventing direct mixing of propellant and gas during spacecraft posture control, eliminating sloshing issues.
Solution Approach 2:
Partition walls with communication holes act as intermediaries between the propellant holding chamber and gas holding chamber. These partition walls allow controlled interaction between liquid propellant and gas phases while maintaining physical separation that prevents sloshing during spacecraft maneuvers.
4Quantity of substance
If the tank is made spherical to optimize propellant storage, then the storage efficiency is improved, but wasted space occurs when connected to a spacecraft and the size increases
Solution Approach 1:
The tank is divided into multiple functional chambers including propellant holding chamber, gas holding chamber, and machine housing unit. This segmentation allows the overall tank structure to adopt a more compact, spacecraft-friendly geometry while maintaining efficient propellant storage within the propellant holding chamber. The modular chamber design enables better integration with spacecraft constraints.
Solution Approach 2:
The tank structure serves multiple functions through its segmented design: propellant storage, gas storage, machine housing, and thermal management. This multi-functionality reduces the overall volume required compared to a simple spherical storage tank, as the same structure performs multiple roles essential for spacecraft operation.
5Adaptability or versatility
If the tank and thruster are connected by piping to enable flexible design, then design flexibility is improved, but connection work and leakage inspection require time, labor, and specialized knowledge
Solution Approach 1:
The gas holding chamber and thruster are directly integrated with minimal or no intermediate piping. The communication holes in the partition walls provide direct flow paths from the propellant holding chamber through the gas holding chamber to the thruster. This merging eliminates numerous piping connections, reducing assembly time and leakage inspection requirements while maintaining design flexibility through the modular chamber structure.
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 design reduces the size and weight of the device, minimizes sloshing, and simplifies the connection process, enhancing gas-liquid separation and reducing labor and time required for assembly and inspection.
Implementation Method 1
a heater that is placed in the casing and heats at least the gas storing unit
Implementation Method 2
a vapor jetting device that evaporates a propellant in the form of liquid and jets gas by means of a steam pressure
Implementation Method 3
using a heat spreader to evaporate propellant before it enters the gas storing unit
Implementation Method 4
forms a space that is divided from the propellant holding unit by a partition wall including a communication hole
Data Source
AI summary
Provided is a vapor jetting device including: a box-shaped casing; a propellant holding unit that is placed in the casing and forms a space for holding a propellant; a gas storing unit that is placed in the casing, forms a space that is divided from the propellant holding unit by a partition wall including a communication hole, and stores gas; a machine housing unit that is placed in the casing, forms a space that is divided from the propellant holding unit and the gas storing unit by partition walls, and houses machines; a nozzle that is connected to the casing and ejects the gas to an outside; a gas flow path that is formed in the casing and supplies the gas stored in the gas storing unit to the nozzle; and a heater that is placed in the casing and heats at least the gas storing unit.