Service Satellite Thruster Control for Host Satellite Station Keeping
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The high cost and limited operational life of satellites in orbit due to fuel depletion and gravitational/solar forces necessitate a technology for extending satellite life and maintaining orbital position.
Innovation Solution
A service satellite with a gripping mechanism and thruster system that forms an interconnected unit with a host satellite, using thrusters positioned to avoid passing through the combined center of mass, enabling station keeping and maneuvering to maintain a geostationary orbit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If a satellite carries more on-board propellant to extend operational life, then the duration of action increases, but the weight of the moving object increases, requiring more expensive launch vehicles
Solution Approach 1:
The propulsion function is segmented between two independent satellites: the host satellite carries the majority of propellant for long-term operation, while the service satellite provides auxiliary propulsion capabilities. This division allows the host satellite to be launched with reduced propellant mass while maintaining extended operational life through the service satellite's support.
Solution Approach 2:
The service satellite acts as an intermediary that provides propulsion services to the host satellite. By transferring propellant or providing thrust assistance from the service satellite, the host satellite can extend its operational life without carrying additional propellant mass during its primary launch.
2Manufacturing precision
If the satellite launch vehicle injects the satellite into an incorrect orbit requiring correction, then the position accuracy deteriorates, but the satellite must expend on-board fuel for orbit transition, reducing operational life
Solution Approach 1:
The service satellite serves as an intermediary propulsion system that can correct orbital deviations without consuming the host satellite's station-keeping fuel. The service satellite's thrusters provide the necessary delta-v for orbit correction, preserving the host satellite's propellant for its intended operational lifetime.
Solution Approach 2:
Instead of relying on the host satellite's limited propellant for both correction and station-keeping, the system applies partial propulsion action from the service satellite specifically for correction maneuvers. This separates the correction function from the station-keeping function, ensuring operational life is not compromised by injection errors.
3Adaptability or versatility
If the satellite uses its propulsion system for both initial orbit correction and station keeping, then the versatility is improved, but the duration of action decreases due to fuel depletion
Solution Approach 1:
The propulsion functions are segmented between two satellites: the service satellite handles initial orbit correction and positioning maneuvers, while the host satellite's propulsion system is dedicated to station-keeping operations. This functional segmentation allows both correction and station-keeping capabilities without compromising operational life.
Solution Approach 2:
The service satellite acts as an intermediary that performs preliminary propulsion operations (orbit insertion, correction, positioning) before the host satellite begins its operational phase. This intermediary action ensures the host satellite's propellant is preserved for its primary station-keeping function, maintaining both versatility and extended operational life.
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
Extends the operational life of host satellites by compensating for gravitational and solar forces, reducing fuel consumption, and allowing for efficient station keeping and orbital maneuvers.
Implementation Method 1
A satellite in a geostationary orbit around the earth experiences gravitational and solar forces, which tend to move the satellite away from its desired geostationary position.
Implementation Method 2
A satellite in a geostationary orbit around the earth experiences gravitational and solar forces, which tend to move the satellite away from its desired geostationary position.
Implementation Method 3
The service satellite may include at least two thrusters and at least one controller. Such a controller may be configured to maintain the interconnected unit in a substantially stationary orbit, and may do so by selectively moving each of the at least two thrusters to angular orientations such that during thruster firing, thrust vectors from each of the at least two thrusters avoid passing through the combined center of mass
Data Source
Figure 1A~1B
Figure 2
Figure 3
AI summary
A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.