Phased Array Thermal Subsystem Fluid Loop Simulator
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Solution Overview
Problem
The challenge lies in facilitating the testing and verification of spacecraft payloads before integration with the on-board heat transfer system, as current methods require extensive disassembly and reassembly, leading to time-consuming and costly procedures.
Innovation Solution
A portable apparatus that can be coupled to the payload's thermal subsystem to receive and dissipate heat, allowing for testing of the payload in a simulated thermal environment without the need for extensive disassembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If payloads are integrated with the on-board heat transfer system before testing, then the thermal environment can be maintained, but the testing process becomes extremely time-consuming and complex
Solution Approach 1:
The invention divides the testing process into two independent segments: (1) functional testing of the payload with a simplified test heat transfer system using quick-connect couplings, and (2) subsequent integration with the actual on-board heat transfer system. This segmentation allows the payload to be tested without requiring integration with the complex final system, dramatically reducing testing time while maintaining thermal environment control during the test phase.
Solution Approach 2:
The invention performs preliminary testing of the payload using a test heat transfer system before final integration with the on-board system. Quick-connect couplings are pre-installed on the payload, enabling rapid connection and disconnection for preliminary tests. This preliminary action allows functional verification to occur independently of the final integration, avoiding time-consuming disassembly later.
2Temperature
If payloads are integrated with the on-board heat transfer system, then thermal dissipation can occur, but disassembly and reassembly require extensive work including cutting and welding
Solution Approach 1:
The fluid transfer lines are segmented into modular sections with quick-connect couplings installed at strategic locations. This allows the fluid lines to be divided into separable segments that can be quickly connected and disconnected without cutting or welding, while still maintaining thermal dissipation capability when connected.
Solution Approach 2:
Quick-connect couplings serve as intermediary devices between the payload fluid lines and the test or on-board heat transfer system. These couplings enable easy connection and disconnection of fluid lines, acting as a mediator that simplifies the joining process while maintaining the thermal dissipation function when connected.
3Reliability
If payloads are tested after integration with other payloads, then the complete system can be verified, but access to individual payloads becomes difficult
Solution Approach 1:
The payload system is segmented into independently testable units with quick-connect couplings. This allows individual payloads to be separated from the integrated assembly for focused testing or modification, while the overall system verification can still be performed by reconnecting the segments. The segmentation enables both individual and system-level testing without compromising accessibility.
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 solution enables efficient testing and verification of spacecraft payloads during development, reducing the overall time and cost associated with testing, while also allowing for testing at the payload developer's facility rather than a centralized launch site.
Implementation Method 1
a heat transfer system configured to be coupled to the payload and dissipate heat from the payload
Implementation Method 2
a pumped fluid loop (PFL) system for transporting and distributing the heated fluid and transferring or dissipating the heat from the fluid
Data Source
AI summary
The present application relates to systems, methods, and apparatus for facilitating the testing of a payload. An exemplary apparatus may include a fluid inlet port configured to receive fluid from a thermal subsystem of the payload. The apparatus may also include an actuating device configure to supply the fluid to a heat exchanger. A valve may be configured to receive the fluid from the heat exchanger and separate the fluid into a first fluid line and a second fluid line. A first fluid outlet port may be configured to supply the fluid to the thermal subsystem of the payload and a second fluid outlet port may be configured to supply the fluid to the thermal subsystem of payload.