Artificial Satellite Electric Propulsion Orbit Control
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Solution Overview
Problem
Current satellite monitoring systems face challenges in achieving high-resolution Earth monitoring due to limitations in geostationary orbit satellites, such as distance and angle constraints, and the high construction costs of multiple satellite systems required for effective coverage.
Innovation Solution
A monitoring system utilizing an artificial satellite with an electric propulsion system that adjusts its orbit altitude and speed to maintain synchronization with Earth's rotation, allowing for high-resolution imaging and flexible positioning to cover mid-latitude areas effectively, using a combination of geostationary and elliptical orbits with controlled propulsion to extend monitoring periods and improve resolution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If geostationary orbit satellite is used for monitoring, then the satellite can maintain a fixed position relative to Earth and provide continuous monitoring of a specific point, but the monitoring resolution is low due to the long distance (about 36,000 kilometers) and oblique viewing angles for mid-latitude areas
Solution Approach 1:
The satellite transitions from a static geostationary orbit to a dynamic elliptical orbit with varying altitude and speed. The orbit is designed so that the satellite passes close to the target area at perigee for high-resolution imaging, then moves to apogee to adjust timing and maintain synchronization with Earth's rotation over multiple orbital periods
Solution Approach 2:
The satellite orbit parameters (altitude, speed, eccentricity) are changed to optimize monitoring performance. By using an elliptical orbit with controlled eccentricity and inclination, the satellite achieves varying distances from Earth - close at perigee for high resolution, far at apogee for timing adjustment - while maintaining synchronization with Earth's rotation
2Speed
If chemical propulsion is used to put the satellite into geostationary orbit, then the satellite can reach the required orbit position, but a large amount of propellant is required which limits the space available for installing photographing means with large aperture and long focal length
Solution Approach 1:
The patent replaces chemical propulsion with electric propulsion to insert the satellite into an elliptical transfer orbit. Electric propulsion systems have much higher specific impulse than chemical engines, requiring significantly less propellant mass. This substitution frees up volume on the satellite for installing larger aperture photographing means with longer focal lengths, directly improving monitoring resolution
3Productivity
If multiple observation satellite groups are deployed to observe a target area, then the observation coverage and frequency are improved, but the construction cost of the system becomes high
Solution Approach 1:
The patent designs a single satellite system that can perform multiple functions: high-resolution imaging of mid-latitude areas, continuous monitoring capability, and flexible repositioning. By making one satellite multi-functional through elliptical orbit operations, the system achieves coverage comparable to multiple satellites without the high construction costs and complexity of deploying satellite groups
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
Enables high-resolution monitoring of target areas with reduced propellant requirements, allowing for longer operational periods and cost-effective coverage of mid-latitude regions without the need for multiple satellites.
Implementation Method 1
the artificial satellite includes an electric propulsion device that accelerates or decelerates the artificial satellite
Data Source
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AI summary
An artificial satellite (101) comprises a monitoring device, a propulsion device, and a monitoring control device. The monitoring control device controls the propulsion device while the artificial satellite circulates around Earth (120). Consequently, a relative position of the artificial satellite with respect to a target area in a target time zone is adjusted. Further, a circulation cycle of the artificial satellite is fixed to a rotation cycle of the Earth.