Modular Power-Distribution Spacecraft for Multi-Mission Energy Delivery

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Solution Overview

Problem

Existing electrical energy distribution systems for spacecraft are limited in operational area, require multiple distinct systems, and are costly due to high mass equipment, with solar generators providing insufficient power and limited to single-use missions.

Innovation Solution

A modular spacecraft equipped with an electric thruster, chemical thruster, and a solar electrical energy generator with variable geometry, allowing removably coupled fuel containers for flexible mission execution, including deployment and retraction for multiple energy distribution missions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If multiple distinct systems (launch system, transfer system, descent system) are used to bring solar electrical energy generator to client craft, then the mission can be completed, but the device complexity and cost increase due to high mass equipment

Engineering Contradiction:

Improvemission completionVSAvoidsystem complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent combines the launch system, transfer system, and descent system into a single integrated spacecraft. The spacecraft includes a main body with solar electrical energy generator, fuel tanks, and propulsion systems that can perform all functions from launch to delivery to client craft in one unified platform, eliminating the need for multiple separate systems.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The spacecraft is designed as a universal platform that can perform multiple functions: launching from Earth, transferring to orbit, descending to celestial bodies, and delivering electrical energy to client crafts. The same spacecraft can serve different missions and clients without requiring dedicated systems for each function.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Adaptability or versatility

If solar electrical energy generators are used for one-off missions, then the operational area is limited, but the device complexity remains high

Engineering Contradiction:

Improveoperational areaVSAvoidsystem complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The spacecraft includes dynamic capabilities with adjustable solar electrical energy generator deployment, variable geometry structures, and flexible propulsion system configuration that allow adaptation to different mission requirements and operational areas while maintaining a relatively simple base system architecture.

Inventive Principle:

Principle #15Dynamics

3Power

If solar electrical energy generators provide small quantity of electrical energy (a few kW), then the system remains simple, but the power capacity is insufficient for powered client crafts

Engineering Contradiction:

Improveelectrical energy quantityVSAvoidsystem complexity

Core Design Contradiction:

PowerVSDevice complexity

Solution Approach 1:

The solar electrical energy generator is designed with variable geometry that can be deployed or retracted based on mission needs. The generator can be configured to provide different power levels, and the spacecraft can adjust its operation mode (powered or unpowered) to match the requirements of different client crafts and missions.

Inventive Principle:

Principle #15Dynamics

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

Facilitates autonomous, multi-mission electrical energy distribution to various points in space and celestial bodies, combining launch, transfer, and descent functions, enhancing operational flexibility and power capacity.

Implementation Method 1

a solar electrical energy generator with variable geometry

Methodology Applied

Scientific EffectSolar energy conversion: Photovoltaic Effect

Implementation Method 2

a main structure equipped with an electric thruster

Methodology Applied

Scientific EffectElectromagnetic propulsion: Electromagnetic Propulsion

Implementation Method 3

a chemical thruster

Methodology Applied

Scientific EffectChemical propulsion: Combustion

Data Source

PatentUS12545440B2Electrical distribution spacecraft, and associated method

Publication Date: 2026.02.10 SAFRAN SPACECRAFT PROPULSION

AI summary

A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.