Micro-thruster Array for Satellite Dispersion and De-orbiting
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Solution Overview
Problem
Small artificial satellites face limitations in mission duration and dispersion time due to orbital decay and limited space for propulsion systems, which restricts their operational life and requires extensive time for dispersion after launch.
Innovation Solution
A propulsion system with multiple engines and a control unit that allows configuration for orbit correction, dispersion, and de-orbiting, enabling extended mission life and efficient satellite distribution in constellations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If traditional propulsion systems are used in small satellites, then the satellite can perform basic orbit maintenance, but the propulsion system occupies a significant proportion of the available volume leaving little space for instrumentation
Solution Approach 1:
The propulsion system is divided into multiple independent micro-thrusters instead of using a single large engine. Each micro-thruster is small and can be independently controlled, allowing the propulsion function to be distributed across multiple compact units that occupy minimal space while maintaining reliable orbit correction capability through coordinated operation
Solution Approach 2:
The micro-thruster array is designed to perform multiple functions: orbit correction, satellite dispersion in constellations, and controlled de-orbiting. This multi-functional design eliminates the need for separate propulsion systems for different operations, maximizing the use of limited satellite volume while ensuring comprehensive propulsion capability throughout the satellite's operational life
2Adaptability or versatility
If satellites are launched in constellations, then missions can be undertaken that are impossible with a single satellite, but the satellites take up to two weeks to disperse after launch
Solution Approach 1:
The micro-thrusters are pre-configured and pre-tested during satellite assembly, with dispersion trajectories pre-calculated. Upon deployment, the thrusters immediately execute pre-programmed dispersion maneuvers, reducing the time required to achieve proper constellation geometry from weeks to days or hours, while maintaining the full mission capability of the constellation
3Reliability
If satellites remain in orbit after their natural life ends, then they continue to occupy orbital space, but they become useless orbital hazards
Solution Approach 1:
The same micro-thruster propulsion system that enables orbit correction and dispersion is used in reverse to perform controlled de-orbiting at the end of the satellite's operational life. By firing the thrusters in the opposite direction of orbital motion, the satellite reduces its orbital velocity and re-enters the atmosphere in a controlled manner, converting the propulsion system from an orbit-maintaining device into an orbit-aborting device, thereby eliminating orbital debris hazards
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
The system significantly extends satellite operational life, reduces dispersion time, and allows for controlled re-entry, preventing useless satellites from becoming orbital hazards.
Implementation Method 1
a plurality of engines fixable to a frame of a satellite; a control unit connected functionally to the engines for sending at least one activation signal for activating at least one engine
Data Source
AI summary
A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.