Mega-Constellation Propellant Planning for Controlled Reentry
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Solution Overview
Problem
There is a risk that satellites constituting a mega-constellation may remain in outer space in large numbers after completing their missions, leading to an increased risk of collisions and space debris accumulation.
Innovation Solution
Artificial satellites are designed with a specific amount of propellant to operate for a designated period and then re-enter the Earth's atmosphere within that period, preventing them from lingering in orbit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites are designed with sufficient propellant for long-duration orbital operations, then the satellite's operational reliability is improved, but the risk of satellites remaining in orbit as space debris after mission completion increases
Solution Approach 1:
The patent applies preliminary action by pre-calculating and allocating propellant quantities during the design phase to ensure both sufficient operational duration and adequate deorbit capability. The propellant is predetermined to cover the full operational lifetime plus the deorbit phase, preventing satellites from becoming long-term debris while maintaining reliability throughout the mission.
Solution Approach 2:
The patent employs parameter changes by optimizing the propellant mass fraction and depletion schedule throughout the satellite's lifecycle. By dynamically adjusting propellant consumption rates and final reserve quantities, the system ensures satellites maintain reliability during operation while guaranteeing atmospheric reentry within a specified time frame after mission completion.
2Productivity
If satellites operate in mega-constellations for extended periods, then the productivity and utility of the satellite system is improved, but the number of satellites in orbit increases leading to higher collision risk
Solution Approach 1:
The patent applies preliminary action by pre-planning the end-of-life deorbit trajectory and propellant allocation for each satellite in the mega-constellation. This ensures that while satellites can operate productively for their full design life, they are guaranteed to reenter the atmosphere within a controlled timeframe, preventing indefinite accumulation and reducing collision risks.
Solution Approach 2:
The patent implements feedback mechanisms through ground-based tracking and propellant management systems that monitor satellite status and adjust operations to ensure timely deorbiting. This feedback loop allows the constellation to maintain high productivity while actively managing orbital population and minimizing collision risks through coordinated end-of-life disposal.
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 approach effectively manages satellite deorbiting, maintaining a controlled number of objects in orbit, thereby reducing the risk of collisions and preventing the Kessler syndrome.
Implementation Method 1
a propulsion device; the artificial satellite has propellant to be used by the propulsion device
Data Source
AI summary
An object is to prevent satellites constituting a mega-constellation from remaining in outer space in large numbers after completing their missions. An artificial satellite includes a propulsion device. The artificial satellite has propellant to be used by the propulsion device, and the propellant is in an amount required for the artificial satellite to operate in orbit for a first period of L1 years, which is a satellite design life, and then enter the atmosphere within a period less than the first period of years after deorbit. A ground facility controls the artificial satellite so that the artificial satellite has the amount of propellant required to operate in orbit for the first period of L1 years, which is the satellite design life, and then enter the atmosphere within a period of less than the first period of L1 years after deorbit.