Systems, devices, and methods for spacecraft propulsion with a heat exchanger

The non-combustive rocket propulsion system with a heat exchanger addresses inefficiencies in existing systems by transferring heat to propellants for efficient thrust generation, enabling high delta-v maneuvers with reduced mass and complexity, suitable for diverse space environments.

WO2026049715A2 Publication Date: 2026-03-05PORTAL SPACE SYSTEMS INC
0 Cites 0 Cited by

Patent Information

Application Number
PCT/US2024/038401
Authority / Receiving Office
WO · WO
Patent Type
Applications
Current Assignee / Owner
Priority Date
2023-07-18
Filing Date
2024-07-17
Publication Date
2026-03-05

AI Technical Summary

Technical Problem

Existing spacecraft propulsion systems face inefficiencies and complexities, such as high propellant mass requirements, low thrust levels, and operational complexities, particularly in low-earth orbit environments, limiting their maneuvering capabilities.

Method used

A non-combustive rocket propulsion system utilizing a heat exchanger that transfers heat from a solar collector or other heat source to a propellant, expelling it through a nozzle to generate thrust, with a heat exchanger body containing propellant and working fluid channels, manufactured via additive manufacturing using refractory metals.

Benefits of technology

The system achieves high delta-v maneuvers with reduced propellant mass and complexity, enabling efficient thrust generation and maneuvering in various space environments with minimal electrical power requirements.

✦ Generated by Eureka AI based on patent content.
Patent Text Reader

Abstract

The present disclosure relates to systems, devices, and methods for spacecraft propulsion. In an embodiment, the present disclosure relates to an apparatus comprising a heat exchanger body defining a plurality of propellant channels configured to contain a propellant, a central cavity configured to contain a working fluid and fluidically connected to a plurality of working fluid channels that extend along a radial dimension of the apparatus, and a nozzle fluidically connected to the plurality of propellant channels and configured to expel the propellant.
Need to check novelty before this filing date? Find Prior Art