Modular Spacecraft with Dual Propulsion for Multi-Mission Power Delivery
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Solution Overview
Problem
Existing spacecraft systems for distributing electrical energy to client vehicles in space are limited to one-off missions, requiring multiple separate systems that increase mass and cost, and provide insufficient power capacity.
Innovation Solution
A modular spacecraft equipped with an electric thruster, chemical thruster, and variable geometry solar generator, allowing for removably coupled fuel containers to perform multiple electrical power distribution missions, including launch, orbit transfer, and celestial body landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple separate systems (launch system, orbit transfer system, descent system) are used to bring solar electrical energy generator to client spacecraft, then the mission can be completed, but the device complexity and mass increase significantly
Solution Approach 1:
The patent combines the launch system, orbit transfer system, and descent system into a single integrated spacecraft. The spacecraft includes a main body with solar electrical energy generator, propulsion systems, and docking mechanisms all integrated into one vehicle that can perform all functions from launch to delivery to client spacecraft, eliminating the need for multiple separate systems.
Solution Approach 2:
The spacecraft is designed as a multi-functional platform that can perform launch, orbit transfer, and descent operations simultaneously. It equipped with both chemical and electric propulsion systems, allowing it to adapt to different mission phases and requirements, making it a universal vehicle for solar electrical energy distribution missions.
2Adaptability or versatility
If multiple separate systems are used for launch, orbit transfer, and descent, then the mission can be accomplished, but the mass of equipment increases
Solution Approach 1:
By merging the launch system, orbit transfer system, and descent system into a single spacecraft, the total mass of equipment is reduced. Instead of having separate vehicles for each function, all systems are integrated into one platform, eliminating redundant components and reducing overall mass while maintaining full mission capability.
3Productivity
If solar electrical energy generator is used in one-off missions, then the mission requirements are met, but the operational area is limited and cannot be reused for new missions
Solution Approach 1:
The spacecraft is designed to be reusable after completing its mission. After delivering the solar electrical energy generator to the client spacecraft, the main spacecraft can return to Earth orbit and be prepared for new missions. The modular design allows for recovery and reuse of critical components, enabling the operational area to be expanded beyond single-use missions.
4Ease of operation
If separate launchers are used for solar electrical energy generator and fuel containers, then the launch flexibility is improved, but the number of launchers required increases
Solution Approach 1:
The solar electrical energy generator, fuel containers, and spacecraft are integrated into a single launchable unit. This allows all components to be launched together in one mission, reducing the number of launchers required while maintaining launch flexibility through the modular design of the integrated system.
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 autonomous, high-power electrical energy distribution to client vehicles at various points in space and on celestial bodies, reducing the need for multiple systems and launchers, and enabling successive missions without being limited to a single operational area.
Implementation Method 1
a solar generator of electrical energy
Implementation Method 2
a main structure equipped with an electric thruster
Implementation Method 3
a chemical thruster
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
The invention relates to a spacecraft (1) for the distribution of electrical energy to client craft (2) at points situated in free space, in orbit and/or on a celestial body, the spacecraft (1) comprising a main structure (10) equipped with an electric thruster (10A), with a chemical thruster (10B) and with a solar generator (10C), a first fuel container (11) for fuel intended for the electric thruster (10A), and a second fuel container (12) for fuel intended for the chemical thruster (10B), the spacecraft (1) being able to be modulated such that: the main structure (10) can be coupled/decoupled alternatively to/from the first container (11) or the second container (12), the first container (11) and the second container (12) being able to be coupled/decoupled to/from one another, the solar generator (10C) being intended to be deployed or retracted.