Modular Spacecraft Bus with External Docking for Payload Replacement
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Solution Overview
Problem
The increasing number of non-functional spacecraft in Low Earth Orbit (LEO) due to mismatched operational needs and design conventions of single-purpose spacecraft, leading to high failure rates and lack of viable methods for repairing or replacing failed spacecraft.
Innovation Solution
A modular spacecraft design that separates the payload from the spacecraft bus, allowing payloads to dock and undock externally, providing access to resources like electrical power, data communications, sensor data, and thermal management, and enabling the replacement of failed or outdated payloads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If single-purpose spacecraft design is used, then spacecraft can be launched with specific payload, but spacecraft cannot be repaired or replaced once failed
Solution Approach 1:
The spacecraft system is divided into two independent segments: a reusable spacecraft bus and replaceable payload modules. The bus contains all support systems (power, propulsion, control) while payloads are separate dockable units. This segmentation allows the bus to remain operational while failed payloads are replaced, directly resolving the contradiction between adaptability and reliability.
Solution Approach 2:
The spacecraft design transitions from a static single-purpose configuration to a dynamic multi-purpose platform. Payloads can be docked, undocked, and replaced during the spacecraft's operational lifetime through standardized interfaces. This dynamic capability enables the same bus to support multiple different payloads, improving both adaptability and mission success rates through redundancy.
2Productivity
If more program resources are allocated to payloads rather than spacecraft bus, then payload capability increases, but spacecraft support system reliability decreases
Solution Approach 1:
By segmenting the spacecraft into a robust, well-resourced bus and separate payload modules, the invention allows disproportionate resource allocation to the bus without compromising payload capability. The bus becomes a reliable platform that can support multiple payloads over time, resolving the trade-off between payload capability and bus reliability.
Solution Approach 2:
The spacecraft bus is designed as a universal platform with standardized docking interfaces and resource provision systems that can support multiple different payload types. This multi-functionality allows the bus to serve as a reliable foundation for diverse payloads, enabling resource allocation optimization without sacrificing either payload capability or bus reliability.
3Adaptability or versatility
If single-purpose spacecraft are launched, then each spacecraft serves one mission, but the number of non-functional spacecraft in orbit increases
Solution Approach 1:
Segmenting the spacecraft into a reusable bus and replaceable payloads enables the bus to remain in orbit and continue providing services (power, propulsion, control) even when individual payloads fail or complete their missions. This reduces the number of completely non-functional spacecraft entering orbit, mitigating orbital debris while maintaining mission flexibility through payload replacement.
Solution Approach 2:
The invention implements a discard-and-recover strategy where failed or completed payloads are undocked and removed from orbit, while the main bus is recovered and kept operational. This selective discarding of only the payload portion rather than the entire spacecraft significantly reduces orbital debris generation while preserving mission flexibility.
Data Source
AI summary
The method and the system of this invention center around the innovative concept of an orbit-independent spacecraft comprised of a physical structure that provides multiple docking devices placed in a spatial relationship and orientation on the exterior of the spacecraft. The docking devices provide a standard interface to the spacecraft by which to attach and detach modular components (payloads). Payloads to be docked to the spacecraft have identical docking devices as part of their physical assemblies. A payload that has been launched into space is navigated towards the spacecraft using a transfer vehicle. Payload and spacecraft docking devices are brought into physical contact where internal locking mechanisms create a secure attachment of the payload to the spacecraft. Physical connections within the payload and spacecraft docking devices are made, allowing the payload to access bus capabilities such as electrical power, data communications, sensor readings, and thermal management from the spacecraft.