Satellite Electrical Propulsion Redundancy via Fixed Thruster
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Solution Overview
Problem
Existing satellite systems with electrical propulsion face challenges in robustness and complexity during orbit and attitude control maneuvers, particularly in geostationary orbits, due to the lack of redundancy and efficiency in thruster configurations, which can lead to mission failures and increased costs.
Innovation Solution
A satellite design incorporating a combination of orientable and fixed electrical thrusters, along with a redundant power network, allowing for efficient orbit transfer and attitude control with reduced thruster count, enhanced redundancy, and simplified failure management, utilizing a thruster of fixed orientation aligned with the satellite's center of mass for eccentricity control and redundancy in case of failures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites use electrical propulsion means with orientable thrusters for orbit and attitude control, then better performance is achieved compared to chemical propulsion, but the system lacks robustness and redundancy, leading to mission failures
Solution Approach 1:
The satellite's propulsion system is segmented into multiple independent thrusters (at least three electrical thrusters) with distinct functions: one thruster for transfer maneuvers and at least two thrusters for station keeping. This segmentation provides functional redundancy and simplifies failure management, as the loss of one thruster does not compromise the entire mission.
Solution Approach 2:
The satellite is equipped with redundant thrusters and power units before any failure can occur. The system includes at least three electrical thrusters and corresponding power units, ensuring that if one thruster or power unit fails, the remaining components can immediately take over without interrupting mission operations.
2Ease of operation
If satellites employ multiple orbit control maneuvers with thrusters activated, then orbit and attitude control is achieved, but the system complexity increases and robustness decreases
Solution Approach 1:
The electrical thrusters are designed to perform multiple functions: transfer maneuvers from injection orbit to geostationary orbit, north/south inclination control, and east/west longitude control. This multi-functionality reduces the need for specialized thruster configurations for each maneuver type, simplifying the overall system while maintaining full operational capability.
3Measurement precision
If satellites use electrical thrusters with orientable thrust direction, then control precision is improved, but the device complexity and mass increase
Solution Approach 1:
Instead of using complex orientable thrusters for all control functions, the invention uses fixed-oriented thrusters strategically positioned and activated in specific sequences. The thrusters are oriented to provide optimal control authority for each maneuver type through proper selection of which thrusters to activate, rather than relying on continuous orientation adjustment mechanisms.
4Productivity
If satellites transfer from injection orbit to mission orbit, then the mission objective is achieved, but exposure to radiation increases during the transfer phase
Solution Approach 1:
The transfer from injection orbit to geostationary orbit is executed as efficiently as possible using electrical propulsion, minimizing the time spent in radiation-prone regions. The satellite performs the necessary orbital maneuvers quickly and transitions to the protected geostationary orbit, reducing overall radiation exposure while maintaining transfer efficiency.
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 enables more efficient and robust satellite operations with reduced mass and cost, minimizing exposure to radiation during transfer and maintaining high mission reliability even in the event of thruster or power unit failures, while allowing for diverse and efficient orbit and attitude control maneuvers.
Implementation Method 1
Recently electrical propulsion has been used instead of chemical propulsion to carry out the transfer and station keeping of satellites
Implementation Method 2
eccentricity can be controlled during E/W maneuvers or N/S maneuvers
Data Source
AI summary
A satellite, intended to be placed in a station in orbit about a celestial body, including a first electrical thruster of orientatable thrust direction, a second electrical thruster of orientatable thrust direction, and an electrical thruster of fixed orientation that is fixed with respect to the satellite and of line of thrust passing through the center of gravity of the satellite. The satellite includes two electrical-thruster power units and an electrically interconnecting network connecting a first power unit to the first thruster of orientatable thrust direction and to the thruster of fixed orientation, and connecting a second power unit to the second thruster of orientatable thrust direction and to the thruster of fixed orientation. Each of the power units is configured to power either the associated thruster of orientatable thrust direction or the thruster of fixed orientation.