Satellite Payload Coupling Device with Bellows Decoupling
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Solution Overview
Problem
Satellite payloads cause vibrations during launch, which can damage the drive unit due to their weight, leading to parasitic loads and potential mechanical stress.
Innovation Solution
A device with a coupling member that decouples the drive unit from the payload during launch using a conical interface and a bellows mechanism, preventing torque transfer and allowing re-coupling post-launch for precise alignment and torque transmission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the drive unit is coupled to the satellite payload during launch, then torque transfer is possible for actuation, but the drive unit suffers from vibrations and parasitic loads due to the heavy payload weight
Solution Approach 1:
The coupling device is divided into distinct functional segments: a drive unit interface, a payload interface, and a coupling member with bellows. This segmentation allows the system to independently control the coupling state - connected during normal operation for torque transfer, and decoupled during launch to protect the drive unit from vibrations and parasitic loads.
Solution Approach 2:
The coupling member incorporates a bellows mechanism that provides dynamic adaptability. The bellows can compress to allow relative axial motion between the drive unit interface and payload interface during launch, effectively decoupling them. During normal operation, the bellows expand to establish rigid coupling for torque transfer, enabling the system to transition between operational states.
2Object-affected harmful factors
If the payload is decoupled from the drive unit during launch, then vibrations are avoided, but torque transfer is prevented
Solution Approach 1:
The coupling member with bellows acts as an intermediary element between the drive unit interface and payload interface. During launch, it mediates by allowing relative motion and isolating the drive unit from payload vibrations. During normal operation, it mediates by establishing rigid coupling to enable torque transfer, thus serving dual functions through a single intermediate component.
Solution Approach 2:
The system changes the coupling parameter dynamically - during launch, the coupling member allows axial separation (changing the rigid connection parameter), isolating vibrations. During normal operation, the bellows expand to restore rigid coupling (returning the parameter to its original state), enabling torque transmission. This parameter change allows the system to avoid vibrations when needed while maintaining torque transfer capability when required.
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 solution effectively avoids damage to the drive unit by isolating it from payload vibrations during launch and ensures reliable torque transfer post-launch, maintaining high precision and reliability with a passive, actuator-free design.
Implementation Method 1
The bellows may be adapted to provide a spring force in the direction of the longitudinal axis if released by the coupling member for pressing the device unit interface, i.e. the first transmission interface, against the payload interface, i.e. the second transmission interface.
Data Source
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AI summary
The invention relates to a device for coupling a satellite payload to a drive unit for actuating the satellite payload in orbit. The device comprises a drive unit interface (10) connectable to the drive unit and having a first transmission surface (13), a payload interface (20) connectable to the payload and having a second transmission surface (23) and a coupling member (40) adapted for decoupling the drive unit interface (10) from the payload interface (20) by lifting the first transmission surface (13) from the second transmission surface (23) that they cannot interact with each other during launch of the satellite payload and adapted for coupling the drive unit interface (10) to the payload interface (20) by engaging the first transmission surface (13) with the second transmission surface (23) after launch.