Spacecraft Reservoir Assembly With Elastic Membrane Propellant Feed
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Solution Overview
Problem
Existing spacecraft reservoirs face issues with liquid propellant separation in microgravity conditions, leading to insufficient supply to the rocket engine and potential gas supply instead, which compromises engine operation, and existing solutions like surface tension devices, segregation devices, and auxiliary propulsion systems have significant drawbacks.
Innovation Solution
A dual-reservoir system with a flexible, elastic membrane separating inner volumes for propellant and pressurizing gas, connected by a controllable valve system, ensures consistent liquid propellant supply by adapting to micro-acceleration conditions through a control unit that regulates fluid flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If surface tension devices (interception members) are used to capture liquid propellant, then liquid propellant supply is improved, but device weight and dimensions increase significantly
Solution Approach 1:
The invention extracts the liquid propellant from the bulk reservoir and channels it through a specific pathway (tunnel) to the outlet port. By removing the need for complex interception members and using a simple tunnel structure, the device weight is significantly reduced while maintaining reliable liquid propellant supply to the engine.
Solution Approach 2:
The tunnel acts as an intermediary structure that guides liquid propellant from the reservoir to the outlet port. This simple geometric feature serves as a mediator to ensure liquid supply without requiring heavy mechanical interception devices, thus resolving the contradiction between reliability and weight.
2Reliability
If segregation devices with flexible membranes are used to separate liquid propellant and pressurization gas, then liquid propellant supply is improved, but a significant quantity of liquid propellant is trapped and unusable
Solution Approach 1:
The invention extracts liquid propellant from deep within the reservoir through the tunnel structure, allowing even propellant near the outlet port to be accessed. This eliminates the dead volume problem associated with membrane segregation devices, ensuring that virtually all stored propellant can be used.
Solution Approach 2:
Instead of using a membrane that creates a two-dimensional barrier trapping propellant, the invention uses a three-dimensional tunnel pathway that allows liquid propellant to flow along a specific route to the outlet. This dimensional approach ensures complete propellant utilization without trapping any significant quantity.
3Reliability
If membranes are used to separate liquid propellant and pressurization gas volumes, then liquid propellant supply is improved, but the reservoir shape must be simple and regular
Solution Approach 1:
The invention extracts the liquid propellant through a tunnel structure that can be integrated into complex reservoir geometries. This approach removes the constraint of requiring simple, regular reservoir shapes, allowing the reservoir to be optimized for various mission requirements while maintaining reliable liquid supply.
4Reliability
If auxiliary propulsion apparatus is used to accelerate liquid propellant, then liquid propellant supply is improved, but device complexity and energy consumption increase
Solution Approach 1:
The invention uses the natural thrust from the rocket engine to accelerate the reservoir and thereby the liquid propellant towards the outlet port. This self-service approach eliminates the need for separate auxiliary propulsion apparatus, reducing device complexity and energy consumption while ensuring reliable liquid supply during engine operation.
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 maintains reliable propellant supply without decomposition risks, reduces unusable propellant volume, allows complex reservoir shapes, and minimizes energy consumption, suitable for various missions including re-entry and landing maneuvers.
Implementation Method 1
A reservoir assembly (10) for a rocket engine comprises a reservoir (21) having an inner volume (26) defined by a shell (21b), an elastic membrane (24) arranged so as to separate the inner volume (26) of the reservoir (21) into two distinct volumes (23, 26), a first outlet port (10a) arranged at a first end of the reservoir (22) to allow the liquid propellant to flow out towards the rocket engine
Implementation Method 2
connected by a controllable valve system, ensures consistent liquid propellant supply by adapting to micro-acceleration conditions through a control unit that regulates fluid flow
Data Source
AI summary
A reservoir assembly for a rocket engine of a spacecraft includes a first reservoir defining a first inner volume, a second reservoir having walls defining a second inner volume and comprising first walls fixed to the first reservoir, and an elastic membrane delimiting the second inner volume from the first inner volume, wherein the second reservoir comprises an outlet to allow a liquid propellant to flow out toward a propulsion apparatus of the rocket engine, characterized in that it further comprises a connecting means coupled to the first and second reservoirs and adapted to connect the first and second reservoirs.