Satellite Propulsion System With Rotating Thruster Modules
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Solution Overview
Problem
Current satellite propulsion systems for orbit control are complex, expensive, and have a high mass, limiting the payload capacity due to the need for multiple thrusters of different types at various locations on the satellite, which increases the cost and fuel consumption, especially for inclination control.
Innovation Solution
A propulsion system comprising two sets of propulsion assemblies fixed to the satellite, each with two propulsion modules that include a motorized connection for rotation around a tangential axis, an offset arm, and a thruster plate, allowing for efficient thrust orientation perpendicular to the orbit axis, with redundancy thrusters and additional motorized connections for enhanced control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple thrusters of different types are positioned at various locations on the satellite to meet all mission needs, then the satellite can perform orbit control and attitude control functions, but the cost and mass of the propulsion system increase significantly
Solution Approach 1:
The patent applies a single type of thruster (electric or chemical) that can perform multiple functions including orbit control, inclination control, and attitude control through strategic positioning and control algorithms. This eliminates the need for separate specialized thrusters for each function, reducing overall system mass while maintaining full operational capability.
Solution Approach 2:
The patent combines orbit control and attitude control functions into a unified propulsion system using the same thruster type. By merging these previously separate functions into a single system architecture, the patent reduces the total number of thrusters needed and simplifies the overall propulsion system while maintaining all required control capabilities.
2Productivity
If chemical thrusters are used for main propulsion and electric thrusters for inclination control, then the satellite can efficiently perform orbit transfer and station-keeping, but the system complexity and fuel requirements increase
Solution Approach 1:
The patent employs a single thruster type that can perform both high-power orbit transfer maneuvers and precise inclination control operations. This universal thruster approach eliminates the need for separate chemical and electric thruster systems, reducing system complexity while maintaining the ability to efficiently perform all propulsion functions.
Solution Approach 2:
The patent achieves different operational modes (high-power orbit transfer vs. precision inclination control) by varying thruster firing parameters such as pulse duration, frequency, and combination of thrusters, rather than using physically different thruster types. This parameter-based control approach simplifies the hardware architecture while maintaining operational versatility.
3Reliability
If redundancy thrusters are added for safety and reliability, then the mission reliability improves, but the mass and cost of the propulsion system increase
Solution Approach 1:
The patent integrates redundancy into the same thruster type and configuration used for primary operations, rather than adding separate backup systems. This approach allows the same thrusters to serve both primary and backup functions, reducing overall system mass while maintaining reliability through controlled redundancy strategies.
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 efficient inclination control with reduced fuel consumption and improved torque control around three axes, enhancing the satellite's ability to maintain its orbit while minimizing the bulk and complexity of the propulsion system.
Implementation Method 1
a thruster capable of delivering thrust oriented along an axis perpendicular to the axis V
Implementation Method 2
a motorized connection for rotation around an axis parallel to the axis V, an offset arm, and a plate supporting a thruster capable of delivering thrust oriented along an axis perpendicular to the axis V
Data Source
Figure 1
Figure 2
Figure 3a~3c
AI summary
The invention relates to a propulsion system for orbit control of a satellite in Earth orbit moving at a velocity along an axis V tangential to the orbit. It comprises two propulsion assemblies (50a; 50b), fixed to the satellite opposite each other with respect to the orbital plane, each propulsion assembly comprising two propulsion modules; each propulsion module comprising successively: - a motorized link (51a) for rotation about an axis (R1a) parallel to the axis V, - an offset arm (52a), and - a plate (53a) supporting a thruster (54a) capable of delivering thrust oriented along an axis perpendicular to the axis V, the two propulsion modules of each propulsion assembly being connected to the satellite on either side and substantially equidistant from a plane P perpendicular to the axis V passing through a center of mass CM of the satellite.