Satellite Orbit Transfer via External Propellant Supply
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Solution Overview
Problem
Current methods for transferring satellites from initial orbits to mission orbits are costly and time-consuming, particularly due to the need for substantial thrust capabilities and complex propellant resupply processes, which increase the weight and cost of satellites and prolong transfer times.
Innovation Solution
A dedicated spacecraft, called a transfer vehicle, is equipped with reversible docking means and electrical propulsion, supplied with propellant from an external unit anchored to the satellite, allowing for efficient and rapid transfer to a mission orbit by utilizing the propellant directly from the external unit.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If electrical propulsion is used to transfer the satellite from initial orbit to mission orbit, then transfer performance is improved, but transfer time increases
Solution Approach 1:
The system is divided into two separate components: a spacecraft carrying the satellite and a separate propellant supply unit. This segmentation allows the spacecraft to access propellant externally during the transfer phase, enabling high-thrust electrical propulsion without being constrained by onboard propellant volume, thus achieving both improved transfer performance and reduced transfer time.
2Speed
If the satellite is equipped with substantial thrust capabilities for orbit transfer, then transfer speed is improved, but satellite weight and cost increase
Solution Approach 1:
The propellant storage function is extracted from the satellite and placed in a separate external propellant supply unit. This allows the satellite to have minimal onboard propellant reserves only for maintenance maneuvers, while the bulk propellant is stored externally and supplied during the transfer phase, significantly reducing satellite weight and cost.
Solution Approach 2:
An external propellant supply unit acts as an intermediary between the propellant reservoir and the spacecraft propulsion system. This intermediary provides propellant to the spacecraft during the transfer phase through docking, enabling high-speed transfer without requiring the satellite to carry substantial propellant weight.
3Productivity
If an independent spacecraft is used for orbit transfer with onboard propellant resupply, then transfer capability is improved, but system complexity and cost increase
Solution Approach 1:
The propellant supply function is extracted as a separate, dedicated unit that docks to the spacecraft only when needed for transfer operations. This extraction simplifies the overall system compared to an independent spacecraft with integrated resupply capabilities, as the external unit provides propellant without requiring complex autonomous resupply systems.
4Adaptability or versatility
If propellant is stored onboard the satellite for transfer operations, then transfer autonomy is improved, but satellite volume and weight increase
Solution Approach 1:
The propellant storage volume is extracted from the satellite and relocated to an external propellant supply unit. The satellite retains only minimal propellant reserves necessary for autonomous maintenance maneuvers, while the bulk propellant is stored externally, significantly reducing satellite volume and weight while maintaining transfer autonomy through external resupply.
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 significantly reduces transfer time, minimizes exposure to radiation, and lowers the weight and cost of satellites by eliminating the need for extensive onboard propellant storage and complex resupply processes, while maintaining satellite autonomy post-transfer.
Implementation Method 1
a spacecraft (30), called transfer vehicle, equipped with reversible docking means and electrical propulsion
Data Source
AI summary
A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.