Spaceborne System Configuration Simulation for Rideshare Missions
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Solution Overview
Problem
Current spacecraft design is typically custom-made for single use cases, limiting flexibility and efficiency in accommodating multiple payloads for rideshare missions.
Innovation Solution
A system and method that describe, simulate, and optimize hardware system configurations for spaceborne systems, allowing for the selection and validation of system configurations for rideshare missions using existing, off-the-shelf satellite buses without design modifications.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If custom-designed spacecraft are used for single use cases, then system performance for specific payloads is optimized, but flexibility and efficiency for accommodating multiple payloads are limited
Solution Approach 1:
The patent applies universality by using off-the-shelf satellite buses that can accommodate multiple different payloads through standardized interfaces and mounting mechanisms. The satellite bus is designed with universal payload adapters and standardized electrical interfaces that allow different payloads to be interchangeable, enabling a single platform to serve multiple missions without custom design for each payload.
Solution Approach 2:
The patent segments the spacecraft system into modular components: a standardized satellite bus platform and interchangeable payload modules. This segmentation allows the payload to be separated from the platform, enabling independent selection and replacement of payloads while maintaining the same core satellite bus, thereby improving versatility without increasing overall system complexity.
2Productivity
If off-the-shelf satellite buses are used without design modifications, then development time and cost are reduced, but system configuration optimization for specific rideshare missions is limited
Solution Approach 1:
The patent applies preliminary action by pre-configuring the satellite bus with standardized payload interfaces, mounting structures, and electrical connections before the actual mission payload is selected. This preliminary standardization allows rapid integration of different payloads without requiring design modifications, thereby maintaining fast development speed while enabling systematic optimization of payload configurations for rideshare missions through pre-established compatibility frameworks.
3Reliability
If multiple system configurations are evaluated for rideshare missions, then optimal configuration selection is improved, but evaluation time and computational resources increase
Solution Approach 1:
The patent uses digital twins or virtual models of the satellite bus and payload configurations to perform simulations and evaluations. Instead of physically testing multiple configurations, the system creates digital copies that can be rapidly simulated and validated computationally, thereby maintaining high configuration validation accuracy while significantly reducing the time and physical resources required for evaluation.
Data Source
AI summary
Systems and methods for describing, simulating and/or optimizing spaceborne systems and missions. Configurations for spaceborne systems are generated and validated based on simulation output.