On-Orbit CubeSat Launch Using Solid CO2 Phase Transition
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Solution Overview
Problem
Current on-orbit launch methods face challenges of high fuel consumption, high costs, and harmful emissions, making them inefficient and environmentally unfriendly for multiple space missions.
Innovation Solution
A low-consumption on-orbit continuous launch system utilizing a satellite platform with a launch apparatus that employs solid carbon dioxide as a working medium, which undergoes a phase change to produce high-pressure gaseous carbon dioxide for ejecting CubeSats into transfer orbits, enabling efficient and harmless on-orbit serving missions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional propulsion systems are used for orbital transfer, then missions can be completed, but fuel consumption is high and cost is high
Solution Approach 1:
The patent utilizes the phase transition of solid carbon dioxide to gas to generate high-pressure working medium for launching CubeSats. This phase change process provides the necessary propulsion force without requiring traditional chemical propellants, thereby significantly reducing fuel consumption while maintaining mission completion capability.
Solution Approach 2:
The patent changes the physical state parameters of carbon dioxide from solid to gas through heating, creating a high-pressure gaseous working medium. This parameter change enables the generation of sufficient thrust for orbital transfer without the need for large amounts of traditional fuel, thus improving energy efficiency while preserving mission reliability.
2Object-affected harmful factors
If traditional launch methods are used, then satellites can be deployed, but harmful emissions are generated
Solution Approach 1:
The patent converts solid carbon dioxide, which can be considered a waste product or harmless substance, into a useful high-pressure gaseous working medium through phase transition. This conversion enables launch capability while producing no harmful emissions, as carbon dioxide is environmentally benign compared to traditional chemical propellants.
Solution Approach 2:
The patent employs pneumatic principles by using compressed gas (gaseous carbon dioxide) as the working medium to provide propulsion force. This pneumatic approach replaces chemical combustion processes, eliminating harmful emissions while maintaining effective launch capability for deploying multiple CubeSats.
3Productivity
If single rocket single satellite mode is used, then mission can be completed, but cost is high and efficiency is low
Solution Approach 1:
The patent merges multiple CubeSat launch capabilities into a single integrated launch system carried by one satellite platform. The unified launch apparatus can sequentially or simultaneously deploy multiple CubeSats, significantly improving mission efficiency and reducing costs compared to multiple separate launches, while the overall system structure remains manageable through modular design.
Solution Approach 2:
The launch apparatus designed in the patent serves multiple functions: it can store multiple CubeSats, provide sequential launching capability, and adapt to different mission requirements. This multi-functional design enables a single system to replace multiple specialized systems, improving productivity while keeping device complexity at acceptable levels through versatile functionality.
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 significantly reduces fuel consumption and emissions, providing a safe, reliable, and cost-effective method for on-orbit launches, promoting energy conservation and emission reduction while enabling continuous and accurate deployment of CubeSats for various space missions.
Implementation Method 1
a solid working medium in the launch apparatus is activated by heating to undergo a phase change; the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium
Implementation Method 2
the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium
Data Source
AI summary
A harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.