Satellite Thruster with Motorized Orientation for Orbit Control
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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, which increases the cost and mass of propellants and fuel.
Innovation Solution
A propulsion system with a thruster capable of delivering force along an axis perpendicular to the orbit and a motorized mechanism that allows rotation and orientation to control orbital parameters, including inclination, eccentricity, and drift, using a combination of motorized connections and offset arms to decouple torque axes and optimize force application.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple thrusters of different types are positioned at various locations on the satellite, then all mission requirements from transport to orbital maintenance can be met, but the cost and mass of the propulsion system increase significantly
Solution Approach 1:
The patent implements a single thruster type that can perform multiple functions by repositioning and reorienting itself through a motorized mechanism. The thruster can control all six orbital parameters (inclination, eccentricity, drift, etc.) and generate torques for angular momentum control, replacing the need for multiple specialized thrusters positioned at different locations on the satellite.
Solution Approach 2:
The thruster is mounted on a motorized mechanism that enables dynamic repositioning and reorientation during satellite operations. This dynamic capability allows one static thruster to function as multiple thrusters would, adapting its position and orientation to meet different mission requirements without adding mass through redundant hardware.
2Adaptability or versatility
If multiple thrusters of different types are positioned at various locations on the satellite, then all mission requirements from transport to orbital maintenance can be met, but the cost of propellants and fuel increases
Solution Approach 1:
A single thruster performs all propulsion functions that previously required multiple thrusters, including orbital transfer, inclination control, eccentricity control, and drift correction. This consolidation reduces the total propellant mass required since there is only one propulsion system to maintain and operate throughout the satellite's lifetime.
3Adaptability or versatility
If multiple thrusters of different types are positioned at various locations on the satellite, then all mission requirements from transport to orbital maintenance can be met, but the satellite's payload capacity is limited
Solution Approach 1:
By replacing multiple thrusters with a single multi-functional thruster on a motorized mechanism, the propulsion system mass is significantly reduced. This mass reduction directly increases the satellite's payload capacity, allowing more mass to be allocated to mission instruments and telecommunications equipment.
4Quantity of substance
If a single thruster with motorized mechanism is used to control all orbital parameters, then propellant and mass requirements are reduced, but the device complexity increases
Solution Approach 1:
The motorized mechanism provides dynamic repositioning and reorientation capabilities that enable a single thruster to control all six orbital parameters. While this adds mechanical complexity compared to fixed thrusters, it eliminates the need for multiple thruster systems, valves, and propellant management infrastructure, resulting in net simplification of the overall propulsion system.
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 solution enables efficient control of six orbital parameters with reduced propellant and mass requirements, simplifying the satellite architecture and reducing the need for redundant thrusters, thereby enhancing payload capacity and reducing fuel consumption.
Implementation Method 1
a thruster capable of delivering a force along an axis F having a component perpendicular to the orbit
Implementation Method 2
an amplitude and direction of torque in a plane perpendicular to the F axis, for angular momentum control
Data Source
Figure 1
Figure 2
Figure 3a~3c
AI summary
Propulsion system for orbit control of an Earth-orbiting satellite having an angular momentum accumulation capacity, characterized in that the propulsion system (50) comprises a thruster (51) capable of delivering a force along an axis F having a component perpendicular to the orbit, and a motorized mechanism (52) connected on one side to the thruster (51) and on the other side to a structure (20) of the satellite (10), said motorized mechanism (52) being capable of moving the thruster (51) along an axis V parallel to the velocity of the satellite (10), and capable of orienting the thruster (51) so as to allow control of: a component of the force along the axis V, for orbit control, an amplitude and direction of torque in a plane perpendicular to the axis F, for angular momentum control.