Satellite Constellation Deployment Using Gravitational Drift
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Solution Overview
Problem
Deploying a satellite constellation with multiple angularly offset orbits requires multiple launches or excessive on-board propellant, making it costly and mass-intensive.
Innovation Solution
A method using a single launcher to deploy satellites at the same initial altitude, controlling them to drift altitudes that shift due to Earth's gravitational potential, and then moving them to final orbits with angular offsets, allowing for identical trajectories with different longitudes, thus avoiding the need for multiple launches and propellant.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If multiple launchers are used to deploy satellites on distinct angularly offset orbits, then the satellite constellation can be deployed with correct orbital positions, but the launch cost and operational complexity increase significantly
Solution Approach 1:
The patent merges multiple satellite deployment operations into a single launcher by deploying all satellites on the same initial orbit, then using Earth's gravitational potential to naturally drift them into their respective angularly offset final orbits. This eliminates the need for multiple separate launchers while achieving the same orbital distribution result.
Solution Approach 2:
The invention makes the satellites self-service by utilizing Earth's gravitational potential as a natural mechanism to drift satellites from their initial common orbit to their final angularly offset orbits. The Earth's gravity field itself performs the orbital modification function that would otherwise require active propulsion, reducing the need for complex onboard propulsion systems.
2Manufacturing precision
If on-board propellant is used to modify satellite orbits after deployment, then the satellites can reach their final angularly offset orbits, but the on-board mass requirement increases significantly
Solution Approach 1:
The invention makes the satellites self-service by utilizing Earth's gravitational potential as a natural mechanism to drift satellites from their initial common orbit to their final angularly offset orbits. The Earth's gravity field itself performs the orbital modification function that would otherwise require active propulsion, reducing the need for complex onboard propulsion systems.
Solution Approach 2:
The patent replaces the mechanical propulsion system (engines, fuel tanks, thrust vectors) with a gravitational field-based system. Instead of using onboard propellant to actively change orbital parameters, the invention uses the passive gravitational influence of the Earth to naturally drift satellites into their target orbits, substituting active mechanical control with passive gravitational dynamics.
3Device complexity
If a single launcher is used to deploy multiple satellites on the same initial orbit, then the launch cost is reduced, but the satellites cannot naturally drift to angularly offset final orbits without additional propellant
Solution Approach 1:
The invention makes the satellites self-service by utilizing Earth's gravitational potential as a natural mechanism to drift satellites from their initial common orbit to their final angularly offset orbits. The Earth's gravity field itself performs the orbital modification function that would otherwise require active propulsion, reducing the need for complex onboard propulsion systems.
Solution Approach 2:
The patent replaces the mechanical propulsion system (engines, fuel tanks, thrust vectors) with a gravitational field-based system. Instead of using onboard propellant to actively change orbital parameters, the invention uses the passive gravitational influence of the Earth to naturally drift satellites into their target orbits, substituting active mechanical control with passive gravitational dynamics.
4Weight of moving object
If multiple launches are performed to deploy satellite constellations, then the deployment can be completed with minimal on-board propellant, but the deployment time and operational constraints increase
Solution Approach 1:
The patent merges multiple satellite deployment operations into a single launcher by deploying all satellites on the same initial orbit, then using Earth's gravitational potential to naturally drift them into their respective angularly offset final orbits. This eliminates the need for multiple separate launchers while achieving the same orbital distribution result.
Solution Approach 2:
The invention employs continuous gravitational drift action to gradually move satellites from their initial common orbit to their final angularly offset orbits. Rather than requiring discrete propulsion events, the Earth's gravitational field continuously acts on the satellites, naturally drifting them into their target positions over time, thereby maintaining continuous useful action without additional propellant consumption.
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 the deployment of multiple satellites in a single launch, reducing propellant consumption and launch frequency, and efficiently placing a satellite constellation in less than a year with orbits that can be mutually shifted using Earth's gravitational potential.
Implementation Method 1
the orbits of the various satellites shifting relative to one another at the respective drift altitudes under the effect of the gravitational potential of the Earth
Data Source
AI summary
A method of deploying a constellation of satellites includes using a single launch vehicle to deploy a plurality of satellites at an initial altitude on a same initial orbit, controlling said satellites such that an altitude of some of the satellites is modified while their inclination relative to an equatorial plane and a type of trajectory, of the some of the satellites, remains identical so that each satellite reaches a drift altitude selected from a drift set, with orbits of various satellites shifting relative to one another, and controlling the satellites to be moved sequentially in order to reach a same final altitude, said sequential movement being performed in such a manner that the satellites describe final orbits having trajectories with a same angle of inclination relative to the equatorial plane, a same apogee and perigee, and the same final altitude but presenting distinct longitudes for ascending nodes.