Integral Thruster Satellite Frame for CubeSat Maneuverability
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Small satellites, such as CubeSats, often lack desirable functionality and flexibility due to their simple configurations and limited propulsion systems, which restrict their maneuverability and operational capabilities.
Innovation Solution
Integrally forming thrusters within the satellite's frame, using additively manufactured components such as electrically-operated propellant and electrodes, and nozzle structures, allowing for controlled thrust and maneuverability while maintaining a compact and lightweight design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If CubeSat satellites use simple configurations to keep costs low, then production costs are reduced, but functionality and flexibility are limited
Solution Approach 1:
The patent combines the frame structure and propulsion system into a single integrated component. The frame itself contains combustion chambers and propellant reservoirs, eliminating the need for separate propulsion modules. This merging reduces the number of parts, simplifies assembly, and lowers production costs while maintaining full propulsion functionality for various maneuvers.
Solution Approach 2:
The integrated frame-propulsion system serves multiple functions: structural support, propellant storage, and thrust generation. The same frame that provides structural integrity also houses the propulsion system, allowing the satellite to perform various maneuvers (orbit insertion, de-orbiting, attitude control) without requiring separate specialized components for each function.
2Device complexity
If CubeSat satellites use simple configurations, then device complexity is reduced, but maneuverability and operational capabilities are restricted
Solution Approach 1:
By merging the frame and propulsion system into one integrated structure, the patent reduces device complexity while preserving maneuverability. The unified design eliminates multiple separate components and their associated mounting hardware, simplifying the overall configuration while maintaining the capability to perform various orbital maneuvers through the integrated propulsion system.
3Adaptability or versatility
If thrusters are added to small satellites, then operational capabilities are improved, but device complexity and manufacturing difficulty increase
Solution Approach 1:
The patent resolves the manufacturing difficulty by merging the thruster assembly with the frame structure. Instead of manufacturing separate thrusters and mounting them to the frame, the propulsion system is integrated directly into the frame during a single manufacturing process, significantly reducing assembly steps and manufacturing complexity while maintaining full operational capabilities.
4Adaptability or versatility
If traditional separate propulsion systems are used, then functionality is achieved, but the satellite size and mass increase
Solution Approach 1:
By combining the propulsion system with the frame structure, the patent eliminates the mass of separate mounting structures, fuel tanks, and engine housings. The integrated design uses the frame material itself as part of the propulsion system structure, reducing overall satellite mass while maintaining complete propulsion functionality for various operational requirements.
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
Enables precise and flexible satellite maneuvers, including orbit changes and de-orbiting, while keeping production costs low and ensuring safety through controlled propellant consumption and additive manufacturing processes.
Implementation Method 1
The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.