Dual-module Satellite Propulsion System for Orbit Control
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Solution Overview
Problem
Current satellite propulsion systems for orbit and attitude control are complex, costly, and heavy, limiting the payload capacity due to the need for multiple thrusters and fuels, which complicates the control of orbital parameters like inclination, eccentricity, and drift.
Innovation Solution
A propulsion system comprising two modules with motorized rotation links, offset arms, and plates supporting thrusters oriented to generate thrust efficiently along specific axes, allowing for simultaneous activation of thrusters to control inclination and eccentricity with reduced fuel consumption and increased payload capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple thrusters and fuels are used to control orbit and attitude, then control capability is improved, but system weight and cost increase
Solution Approach 1:
The patent combines multiple thrusters (first and second thrusters) and multiple fuels (first and second fuels) into a single integrated propulsion system mounted on one face of the satellite. This merging approach maintains the control capability for both orbit and attitude while reducing the overall system weight compared to having separate thruster assemblies distributed throughout the satellite structure.
Solution Approach 2:
The propulsion system is designed to perform multiple functions simultaneously: the first and second thrusters can control both the satellite's orbit and its attitude orientation. The system can switch between using the first fuel and the second fuel depending on the specific control requirement, making the propulsion system universal for both orbit control and attitude control operations.
2Adaptability or versatility
If multiple thrusters and fuels are used to control orbit and attitude, then control capability is improved, but device complexity increases
Solution Approach 1:
The patent merges the first and second thrusters along with their respective fuel storage and delivery systems into a single integrated propulsion assembly. This consolidation reduces the number of separate components and interconnections required, thereby simplifying the overall system architecture while maintaining the ability to perform both orbit and attitude control functions.
Solution Approach 2:
The propulsion system is segmented into distinct functional modules: a first thruster for primary orbit control, a second thruster for attitude control, first fuel storage for chemical propulsion, and second fuel storage for electrical propulsion. This segmentation allows for easier manufacturing, testing, and maintenance while reducing the complexity of integrating all components into a cohesive system.
3Power
If chemical thrusters are used for orbit transfer, then thrust power is improved, but fuel consumption increases
Solution Approach 1:
The patent employs parameter changes by switching between two different fuel types with different propulsion mechanisms. The first fuel (chemical) is used when high thrust power is needed for orbit transfer, while the second fuel (electrical/plasma) is used when lower thrust is sufficient for station-keeping and attitude control. This dynamic adjustment of propulsion parameters optimizes the balance between thrust power and fuel consumption based on the specific mission phase 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
This configuration enhances the efficiency of inclination control and reduces fuel consumption, while simplifying the propulsion system architecture, allowing for more effective orbit and attitude control with improved payload capacity.
Implementation Method 1
The thrust is generated when the charged xenon ions are accelerated from the thruster by an electromagnetic field
Implementation Method 2
xenon atoms are ionized by collision with electrons, creating xenon ions
Implementation Method 3
a motorized rotation link about an axis parallel to the axis V
Implementation Method 4
a plate supporting two thrusters, suitable for delivering a thrust on an axis
Data Source
AI summary
A propulsion system for the orbit control of a satellite in Earth orbit driven at a rate of displacement along an axis V tangential to the orbit comprises two propulsion modules, fixed to the satellite, and facing one another relative to the plane of the orbit, each of the propulsion modules comprising, in succession: a motorized rotation link about an axis parallel to the axis V; an offset arm; and a plate supporting two thrusters, suitable for delivering a thrust on an axis, arranged on the plate on either side of a plane P at right angles to the axis V passing through a center of mass of the satellite; each of the two thrusters being oriented in such a way that the thrust axes of the two thrusters are parallel to one another and at right angles to the axis V.