Spacecraft Engine Flow Battery Using Electrolyte for Cooling and Thrust
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Solution Overview
Problem
Existing engine arrangements for spacecraft are hindered by heavy energy supply devices, such as batteries and supercapacitors, which reduce payload capacity and specific impulse due to their weight and energy density limitations.
Innovation Solution
The integration of a flow battery arrangement, also known as a redox flow battery, which recirculates electrolytes through a galvanic cell and an electrofluid circuit, allowing used electrolytes to be redirected for cooling or thrust generation, thereby reducing mass and increasing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If heavy battery arrays are used to supply electrical energy to electric pumps and thrust generation devices, then reliable power supply is achieved, but payload capacity and specific impulse are significantly reduced due to weight
Solution Approach 1:
The electrofluid serves multiple functions: it acts as the electrolyte for electrical energy generation in the galvanic cell, and simultaneously serves as cooling fluid for the thrust chamber and/or nozzle when redirected through the electrofluid line. This multi-functionality eliminates the need for separate cooling systems and reduces overall system mass.
Solution Approach 2:
Instead of discarding the electrofluid after it has been used in the galvanic cell, the system recovers it by redirecting through the electrofluid line for further use as cooling fluid and/or thrust generation mass. This recovery approach maximizes the utility of each unit of electrofluid and reduces the mass that must be carried.
2Productivity
If electrofluid is removed from the electrofluid circuit for further use or ejection, then overall efficiency is enhanced, but the energy generation capability may be affected
Solution Approach 1:
The system dynamically adjusts the flow path of the electrofluid based on operational requirements. The electrofluid line provides a configurable pathway that allows the electrofluid to be redirected from the galvanic cell to the thrust chamber cooling system and/or ejection system, enabling flexible adaptation between energy generation mode and cooling/thrust mode.
Solution Approach 2:
The electrofluid maintains continuous useful action by circulating through different parts of the system. When redirected through the electrofluid line, it continues to provide useful functions (cooling and/or thrust) rather than being discarded, ensuring continuous contribution to system performance throughout its journey.
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
This design enhances the overall efficiency of the engine arrangement by utilizing the same electrolytes for multiple functions, including energy generation, cooling, and propulsion, thereby reducing the mass of the energy supply device and increasing fuel savings.
Implementation Method 1
electrical energy can be generated by means of at least one electrofluid (in particular at least one electrolyte) which circulates in an electrofluid circuit with an electrofluid storage device and a galvanic cell
Implementation Method 2
a membrane, and that an electrofluid line is present, by means of which the electrofluid
Implementation Method 3
electrofluid (in particular at least one electrolyte) which circulates in an electrofluid circuit
Data Source
Figure 1
Figure 2A~2C
Figure 3
AI summary
The invention relates to an engine assembly (1), in particular for a spacecraft, comprising a drive unit (50) for generating a thrust force, comprising at least one consumer (13) of electrical energy and comprising an energy delivery device (20) for generating electrical energy, in particular for supplying the at least one consumer (13). A high level of efficiency of the engine assembly (1) can be achieved by way of the energy delivery device (20) having a flow battery assembly (21), wherein electrical energy can be generated by means of at least one electrolytic fluid (24, 24') which circulates within an electrolytic fluid circuit (26) having an electrolytic fluid storage device (22) and a galvanic cell (38) which comprises a diaphragm (28), and can be achieved in that the electrolytic fluid can additionally and simultaneously be used both as a cooling medium and also as an engine pulse mass (figure 1).