Solar Thermal Thruster Cooling Channels for Multi-Propellant Heat Control
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Solution Overview
Problem
Current solar thermal rocket propulsion systems face inefficiencies due to heat loss and thermal stress, particularly in smaller chambers, and lack flexibility in operating with various propellant types and conditions, which affects their thermal efficiency and operational reliability.
Innovation Solution
The development of a solar thermal thruster with adjustable regenerative channels, a multi-surface light trapping solar absorber, and an adjustable cooling system allows for the use of multiple propellant types in both liquid and gaseous states, optimizing thermal energy conversion and reducing thermal stress through dynamic heat management and propellant flow control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If solar thermal rockets use smaller chambers, then the device size is reduced, but heat loss increases and thermal efficiency decreases
Solution Approach 1:
The chamber is divided into multiple zones with different thermal management strategies. Regenerative cooling channels are segmented and distributed throughout the chamber structure, allowing localized heat extraction where most needed while maintaining compact overall dimensions. This segmentation enables efficient heat management in small chambers by creating multiple heat transfer pathways.
Solution Approach 2:
The regenerative cooling channels are nested within the chamber walls and structural components. The cooling passages are integrated into the chamber structure itself, with channels embedded in the wall thickness and nested within support ribs. This nesting approach maximizes heat transfer surface area within the limited volume of a small chamber, reducing heat loss without increasing external dimensions.
2Reliability
If solar thermal rockets are designed for specific propellants, then the system is optimized for those propellants, but flexibility to use different propellant types is reduced
Solution Approach 1:
The regenerative cooling system is designed with adjustable parameters that can be tuned for different propellant types. The cooling channel geometry, flow rate, and heat transfer coefficients can be modified to accommodate various propellants' thermal properties. This universal design allows the same chamber structure to reliably operate with different propellants by adjusting operational parameters rather than redesigning the entire system.
Solution Approach 2:
The cooling system incorporates dynamic adjustment capabilities where flow rates, channel configurations, or active cooling elements can be modified during operation based on the propellant being used. This dynamic adaptability allows the system to optimize its thermal management characteristics for each specific propellant type while maintaining a single unified chamber structure.
3Ease of manufacture
If regenerative cooling channels have fixed geometry, then manufacturing is simplified, but ability to adjust for different propellant conditions is limited
Solution Approach 1:
The cooling channels incorporate adjustable elements such as movable walls, expandable sections, or reconfigurable flow paths that can be modified after manufacturing. These dynamic features allow the fixed-manufactured base structure to be adapted to different propellant conditions through operational adjustments, combining manufacturing simplicity with operational flexibility.
Solution Approach 2:
The system allows changes in operational parameters such as flow rate, pressure, or temperature profiles through the cooling channels to adapt to different propellants. By varying these parameters rather than changing the physical channel geometry, the system maintains manufacturing simplicity while achieving adaptability to different propellant conditions through controlled parameter adjustments.
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 enhances the thermal efficiency and operational flexibility of solar thermal rockets, enabling them to operate effectively with different propellants and reducing thermal stress, thereby improving their performance and durability.
Implementation Method 1
a solar absorbing structure comprising an assembly of partially reflecting, partially transmitting, and partially absorbing surfaces, thereby converting solar energy into thermal energy within the surfaces
Implementation Method 2
one or more regenerative channels configured to direct flow of and simultaneously change thermal energy of the one or more propellants
Implementation Method 3
one or more peripheral cooling channels
Implementation Method 4
one or more peripheral cooling channels, and the thruster adapts for different propellant types by using at least one valve to adjust a deployed length of at least one cooling channel
Data Source
AI summary
Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.