Solid-State Oxygen Ion Propulsion for Nano-Satellites
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Solution Overview
Problem
Current propulsion systems for small space vehicles, such as nano-satellites, face challenges in miniaturization, particularly in the fabrication of leak-tight micro-valves for cold gas blow-down rocket engines, leading to undesired disturbance torques and short mission duration due to high leak rates and complexity.
Innovation Solution
A propulsion apparatus featuring a stack with a solid state oxygen-rich source layer and an active layer exhibiting impedance hysteresis behavior, where the active layer is formed with a resistive switching material, allowing for controlled oxygen ion extraction and acceleration using a cross-bar array architecture and metallic layers, with nozzles and an ion accelerating element for efficient thrust generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If miniaturized propulsion systems are used for nano-satellites, then the vehicle size is reduced, but the fabrication of leak-tight micro-valves becomes technologically challenging and complex
Solution Approach 1:
The patent replaces the mechanical micro-valve system with a solid-state ion conductor-based electrochemical oxygen extraction system. The YSZ membrane electrode assembly enables oxygen extraction through electrochemical reactions rather than mechanical valve control, eliminating the complex micro-valve fabrication requirements while maintaining miniaturization benefits for nano-satellite propulsion.
2Volume of moving object
If micro-valves are downsized to comply with miniaturization demands, then the device size is reduced, but the leak rate increases causing undesired disturbance torques and shortening mission duration
Solution Approach 1:
The patent eliminates mechanical valve structures entirely by using a solid-state electrochemical oxygen extraction mechanism. The YSZ membrane provides inherent leak-tightness through its solid-state ion-conducting properties, preventing gas leakage and disturbance torques while maintaining compact device dimensions suitable for miniaturized satellite propulsion systems.
3Quantity of substance
If YSZ is heated to about 1000 K to operate as oxygen reservoir, then oxygen permeability is improved, but reliability and cost are compromised due to high temperature operation
Solution Approach 1:
The patent modifies the operating parameters by using a solid-state oxygen reservoir that does not require heating to 1000 K. The YSZ membrane electrode assembly operates at lower temperatures through electrochemical oxygen extraction mechanisms, changing the thermal parameter from high-temperature thermal diffusion to low-temperature electrochemical reactions, thereby improving reliability while maintaining oxygen supply.
Solution Approach 2:
The patent employs a composite structure combining YSZ membrane electrode assembly with solid-state oxygen reservoir materials. This composite approach enables oxygen extraction at lower temperatures by utilizing the electrochemical properties of the YSZ composite system rather than relying on high-temperature thermal diffusion of pure YSZ, thus improving reliability and reducing thermal stress.
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 solution provides a reliable, efficient, and compact propulsion system with high thrust-to-weight ratio, long duty-cyclability, and precise control over oxygen expulsion, suitable for small satellites, offering improved reliability and safety compared to existing technologies.
Implementation Method 1
an active layer being deposited above said solid state oxygen-rich source layer, in contact with said solid state oxygen-rich source layer, said active layer being formed with a material different from said solid state oxygen-rich source layer, said material being an oxide featuring impedance hysteresis behavior
Implementation Method 2
the active layer being formed with a resistive switching material, allowing for controlled oxygen ion extraction
Implementation Method 3
a heating electrode associated to the solid sate oxygen-rich layer
Implementation Method 4
means for accelerating correspondingly extracted oxygen ions into vacuum
Data Source
Figure 1A~1F
Figure 2A~2F
Figure 3~4
AI summary
Propulsion apparatus (10) for space vehicles, comprising a solid state oxygen-rich source layer (11), means (12) for extracting oxygen from said solid state oxygen-rich source layer (11), means (16, 14, 17) for accelerating correspondingly extracted oxygen ions into vacuum. According to the invention, it comprises a stack including said solid state oxygen-rich source layer (11), an active layer (16) being deposited above said solid state oxygen-rich source layer (11), in contact with said solid state oxygen-rich source layer, said active layer (16) being formed with a material different from said solid state oxygen-rich source layer (11), said material being an oxide presenting impedance hysteresis behavior, i.e. a memristor, wherein in a low resistance state oxygen ions (22) are expelled through the active layer (16) and wherein in a high resistance state the active layer (16) ceases expelling oxygen ions (22).