Spacecraft Docking System With Stowable Assembly
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Solution Overview
Problem
Current spacecraft designs have limited lifespans due to fuel constraints, particularly for geostationary telecommunication satellites, making it economically challenging to extend their operational life without increasing propellant mass or launch costs.
Innovation Solution
A reusable docking system for spacecraft comprising an end ring and a docking assembly with linear actuators, support rings, and elastic connections, allowing the docking assembly to be stowed within the spacecraft for integration and deployment, enabling docking with target satellites without interfering with launch operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If a Mission Extension Vehicle is launched to dock with and extend the lifespan of geostationary satellites, then the operational lifespan of satellites can be extended, but the launch cost and design/fabrication cost increase significantly
Solution Approach 1:
The satellite adapter is designed to perform multiple functions: it serves as the launch vehicle structure during launch, then transforms into a service satellite with docking capability after payload separation. The docking assembly integrates directly into the adapter structure, eliminating the need for a separate MEV and reducing overall system complexity and cost.
Solution Approach 2:
The satellite adapter, which would otherwise be discarded after launch, is recovered and repurposed as a service satellite. The docking assembly is stowed during launch and then deployed after payload separation, transforming waste into a valuable resource for extending target satellite lifespans.
2Adaptability or versatility
If the docking assembly is integrated into the satellite adapter, then the adapter can function as a service satellite, but the docking assembly must be compact to not interfere with launch operations
Solution Approach 1:
The docking assembly is nested within the satellite adapter structure during launch, with the support ring and docking platforms folded or retracted into the limited space available. The linear actuators and elastic means are configured to occupy minimal volume when stowed, allowing the adapter to maintain its launch function while harboring the docking capability.
Solution Approach 2:
The docking assembly transitions from a compact, space-efficient configuration during launch to an expanded, functional configuration after payload separation. The linear actuators extend the support ring outward, and the docking platforms deploy from their stowed positions, transforming the assembly's volume to accommodate docking operations.
3Ease of operation
If the support ring is connected to linear actuators for deployment, then the docking assembly can be extended, but the mechanism becomes more complex
Solution Approach 1:
The elastic means (springs) provide self-powered deployment assistance, reducing the complexity of the actuation system. The springs store potential energy during stowing and automatically assist in extending the support ring and docking platforms when released, minimizing the need for complex motorized systems while maintaining ease of operation.
4Reliability
If the docking assembly uses elastic means to connect the support ring and end ring, then the assembly can absorb shock during docking, but the structure becomes more complex
Solution Approach 1:
The elastic means use simple, inexpensive spring elements that can be easily replaced if needed. These basic mechanical components provide reliable shock absorption without requiring complex active control systems or sophisticated mechanisms, maintaining simplicity while enhancing docking reliability.
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 reduces design and fabrication costs, eliminates launch costs for the satellite adapter, and shortens development time by allowing the reuse of satellite adapters in orbit, enabling extended satellite missions while maintaining operational efficiency.
Implementation Method 1
the support ring and the end ring being connected by elastic means
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
Docking system (1) for spacecraft, comprising an end ring (3) and a docking assembly (2), the docking assembly (2) comprising: - a support ring (4) connected to a plurality of linear actuators (6) for deployment and retracting, and - at least three docking platforms (5) hinged to the support ring (4), each docking platform (5) comprising: - a main body (7), - a guide member (8), - initial engagement means (9), and - a docking mechanism (10) fixed to the main body (7) and articulated to the end ring (3), the support ring (4) and the end ring (3) being connected by elastic means (11), such that in a stowed position the docking assembly (2) is placed inside the end ring (3) and in a deployed position the docking assembly (2) is placed out of the end ring (3).