Satellite Thermal Control for Launcher-Adapter Stability
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Solution Overview
Problem
Artificial satellite antenna reflectors experience periodic mispointing due to thermal expansion and contraction of the launcher-adapter, leading to deformation of the mounting structure and reduced performance, and existing repointing mechanisms are costly and unreliable.
Innovation Solution
The satellite incorporates a heat-exchange system with a first heat-exchange section in thermal contact with the launcher-adapter and a second heat-exchange section connected to a radiator, allowing for controlled temperature regulation to minimize thermal expansion and contraction, and a method for filling the propellant tank using a radiator for cooling to prevent contamination and reduce filling time.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the antenna reflectors are fastened close to the launcher-adapter to maintain focal distance, then the focal distance is preserved, but thermal expansion and contraction of the launcher-adapter cause deformation and mispointing of the antenna reflectors
Solution Approach 1:
The patent introduces a thermal management system with heat exchange sections and radiators as an intermediary between the launcher-adapter and the mounting structure. This intermediary system actively regulates the temperature of the launcher-adapter, preventing excessive thermal expansion and contraction that would otherwise cause deformation and mispointing of the antenna reflectors, thus allowing the reflectors to be positioned close to the launcher-adapter while maintaining positioning accuracy
Solution Approach 2:
The patent changes the thermal parameters of the launcher-adapter by implementing active temperature regulation through the heat exchange system. By controlling the temperature of the launcher-adapter, the system prevents the material from undergoing significant thermal expansion and contraction, thereby maintaining the geometric parameters and positioning accuracy of the antenna reflectors even when positioned close to the launcher-adapter
2Manufacturing precision
If a mechanism for repointing antenna reflectors is implemented to correct mispointing, then antenna positioning accuracy is maintained, but the device complexity and cost increase significantly
Solution Approach 1:
The patent converts the harmful thermal effects into a beneficial situation by proactively managing the thermal environment. Instead of allowing thermal expansion and contraction to occur and then correcting the resulting mispointing with complex repointing mechanisms, the system uses heat exchange sections and radiators to prevent the thermal deformation from occurring in the first place, thereby eliminating the need for complex repointing mechanisms while maintaining antenna positioning accuracy
Solution Approach 2:
The patent replaces the mechanical repointing system with a thermal management system. Instead of using sensors, processing units, and actuators to mechanically adjust the antenna reflector orientation after mispointing occurs, the system uses thermal control components (heat exchange sections, fluid circulation, radiators) to prevent the mispointing from occurring, thereby eliminating the complex mechanical repointing mechanism
3Loss of time
If the propellant tank is filled quickly without cooling, then the filling time is reduced, but the temperature increase and pressure rise can cause contamination and safety issues
Solution Approach 1:
The patent applies preliminary cooling action to the propellant tank before and during the filling process. The thermal management system pre-cools the tank and maintains it at an appropriate temperature during filling, preventing the temperature increase and pressure rise that would otherwise occur during rapid filling. This preliminary action allows the tank to be filled quickly and safely without contamination or safety issues
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 maintains the focal distance of the antenna reflectors, reduces costs, and enhances the reliability of the satellite by minimizing mispointing and accelerating the propellant tank filling process while ensuring cleanliness and efficiency.
Implementation Method 1
a first heat-exchange section in thermal contact with at least one portion of the launcher-adapter in such a way as to allow for heat exchanges between the launcher-adapter and the first radiator
Implementation Method 2
a second heat-exchange section connected to a radiator
Data Source
AI summary
Disclosed is artificial satellite including: a mounting structure supporting equipment-bearing walls; a launcher-adapter rigidly connected to the mounting structure; a first radiator; and at least one first system for transporting heat by a fluid, including at least one duct having a first heat-exchange section and a second heat-exchange section, the second heat-exchange section being capable of being in thermal contact with the first radiator. The first heat-exchange section is in thermal contact with at least one portion of the launcher-adapter. Also disclosed is a method for filling a tank of propellant gas of the artificial satellite.