Dual-Mode Water Propulsion for Nanosatellites
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Solution Overview
Problem
Current miniaturized satellites face challenges with propulsion systems, requiring separate low and high thrust systems, which increase weight, reduce volume, and complicate operations, leading to inefficient maneuvering and reduced satellite lifespan.
Innovation Solution
A dual-mode propulsion system using liquid water as the primary propellant, capable of performing both low and high thrust maneuvers through water electrolysis for high thrust and vapor expansion for low thrust, integrated into a compact design suitable for nanosatellites.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single low thrust propulsion system is used for all maneuvers, then the satellite structure is simplified, but the time required to complete orbit change maneuvers increases substantially
Solution Approach 1:
The propulsion system dynamically switches between two operational modes: low thrust mode using electric propulsion for attitude control and repositioning, and high thrust mode using chemical propulsion for orbit changes. This dynamic adaptation allows the system to optimize performance for different maneuver types without requiring permanently installed high-thrust hardware, resolving the contradiction between system simplicity and maneuver speed.
Solution Approach 2:
The system changes key operational parameters by switching propulsion modes: thrust level (from millinewtons to newtons), propellant type (from xenon to hydrazine), and operational duration. This parameter switching enables the same propulsion subsystem to deliver appropriate performance for different maneuver requirements, eliminating the need for separate dedicated propulsion systems.
2Force
If a second propulsion system is added for high thrust maneuvers, then orbit change capability is improved, but weight increases and volume available for payload is reduced
Solution Approach 1:
A single propulsion subsystem is designed to perform multiple functions by switching between two propellants: xenon for low-thrust electric propulsion mode and hydrazine for high-thrust chemical propulsion mode. This multi-functionality eliminates the need for separate propulsion systems, reducing overall satellite weight and volume while maintaining both low-thrust and high-thrust capabilities.
Solution Approach 2:
The patent merges the functions of electric propulsion and chemical propulsion systems into a single integrated propulsion subsystem. By combining the thrust chambers, propellant storage, and control systems into one unified unit that can operate with different propellants, the design achieves high thrust capability without the weight penalty of separate propulsion systems.
3Force
If a second propulsion system is added for high thrust maneuvers, then thrust capability is improved, but the cost increases
Solution Approach 1:
The propulsion subsystem is designed as a universal platform that can operate with different propellants (xenon and hydrazine) and deliver different thrust levels. This multi-functionality reduces the need for separate dedicated systems, thereby reducing overall manufacturing costs while maintaining both low-thrust and high-thrust capabilities.
Solution Approach 2:
By merging electric propulsion and chemical propulsion functions into a single subsystem with shared components (thrust chambers, valves, control electronics), the patent reduces the total bill of materials and assembly complexity, leading to lower manufacturing costs compared to installing two separate propulsion systems.
4Force
If a second propulsion system is added for high thrust maneuvers, then orbit change capability is improved, but reliability is reduced
Solution Approach 1:
The patent combines electric and chemical propulsion functions into a single integrated subsystem with shared critical components. This reduction in the number of independent systems decreases the overall system complexity and potential failure points, thereby improving reliability while maintaining both low-thrust and high-thrust capabilities.
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
The system achieves efficient and versatile propulsion, enabling rapid maneuvering and extending satellite lifespan by eliminating the need for multiple propulsion systems, while maintaining a compact and lightweight design.
Implementation Method 1
a water splitting device for splitting the liquid water into gaseous hydrogen and gaseous oxygen
Implementation Method 2
a combustion chamber, in which the gaseous hydrogen reacts with the gaseous oxygen
Implementation Method 3
a vaporization chamber (31-3n) and an expansion nozzle (41-4n) downstream of the vaporization chamber (31-3n)
Data Source
AI summary
A spacecraft is equipped with a low and high thrust space propulsion system including at least one water reservoir (1) containing liquid water, a high thrust propulsion part and a low thrust propulsion part. The high thrust propulsion part has a high thruster including a regulation valve (V1) for drawing water from the liquid water reservoir (1), a device for splitting (2) liquid water into gaseous hydrogen and gaseous oxygen, relative storage tanks (3, 4), a combustion chamber (5) in which the gaseous hydrogen reacts with the gaseous oxygen and an exhaust nozzle (6) from the combustion chamber (5). The low thrust propulsion part comprises a liquid water supply line (10) and a plurality of liquid water outlets in a plurality of branches (11-1n) individually including a regulating valve (21-2n), a vaporization chamber (31-3n) and an expansion nozzle (41-4n).