Lattice Payload Interface Cone for Spacecraft Vibration Isolation
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Solution Overview
Problem
Existing vibration control systems for spacecraft and other dynamic environments are costly, complex, and add unnecessary mass, often requiring multiple isolators and additional components that increase parasitic mass and manufacturing complexity, while active systems are prone to failure and passive systems lack sufficient vibration attenuation.
Innovation Solution
A tuned lattice attenuator with integrated vibration control capabilities, which can be used as a drop-in replacement for existing components, providing structural support and attenuating vibrations without the need for additional isolators or dampening devices, thereby reducing parasitic mass and simplifying installation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If traditional vibration control systems with multiple isolators and dampening devices are used, then vibration attenuation is achieved, but parasitic mass and device complexity increase
Solution Approach 1:
The patent combines multiple vibration control functions (isolation, dampening, attenuation) into a single integrated lattice structure. The lattice geometry itself provides vibration control capabilities without requiring separate isolators or dampening devices, thereby reducing device complexity while maintaining effective vibration attenuation across multiple frequency domains.
Solution Approach 2:
The lattice structure serves multiple functions simultaneously: it provides structural support, vibration isolation, and vibration attenuation across different frequency ranges. This multi-functional design eliminates the need for multiple specialized components, reducing both device complexity and parasitic mass while achieving comprehensive vibration control.
2Object-affected harmful factors
If traditional vibration control systems with multiple isolators are used, then vibration attenuation is achieved, but parasitic mass increases
Solution Approach 1:
The patent merges the functions of multiple isolators and dampening devices into a single lattice structure, eliminating the need for separate components. This integration significantly reduces parasitic mass while maintaining effective vibration attenuation through the lattice's inherent geometric properties.
Solution Approach 2:
The patent extracts and eliminates unnecessary parasitic mass by removing separate isolators and dampening devices from the system. The vibration control functionality is achieved through the lattice structure itself, which provides sufficient attenuation without additional components that would add unwanted weight.
3Reliability
If spacecraft structure is strengthened to survive launch vibrations, then vibration resistance is improved, but mass increases reducing payload capacity
Solution Approach 1:
The patent employs lattice structures that combine lightweight materials with optimized geometric configurations to achieve high vibration resistance. The lattice geometry provides structural strength and vibration attenuation simultaneously, allowing the spacecraft to survive launch vibrations without adding excessive mass that would reduce payload capacity.
Solution Approach 2:
The patent changes the structural parameters by transitioning from solid traditional structures to lattice configurations. This parameter change optimizes the strength-to-weight ratio, providing sufficient vibration resistance during launch while minimizing mass to preserve payload capacity for the orbital mission.
4Object-affected harmful factors
If active vibration control devices are used, then vibration control performance is improved, but cost and complexity increase
Solution Approach 1:
The patent employs passive vibration control through the lattice structure's inherent geometric properties, which automatically attenuate vibrations without requiring active control systems. This self-service approach provides effective vibration control performance while eliminating the complexity and cost associated with active sensors, actuators, and control algorithms.
Solution Approach 2:
The patent replaces expensive active vibration control devices with simpler, more cost-effective passive lattice structures. The lattice geometry provides sufficient vibration attenuation without the need for costly active components, reducing both device complexity and overall system cost while maintaining adequate performance.
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 lattice attenuator effectively reduces vibration transfer, enhances payload capacity, and decreases design and manufacturing costs by eliminating the need for separate vibration control devices, while maintaining structural integrity and simplifying installation processes.
Implementation Method 1
the latticed portions are configured to attenuate a transfer of vibrations between the first and second support structures
Data Source
AI summary
Embodiments of the disclosure are directed to a vibration control system and a vibration control device for structurally isolating a load from a vibration source. In various embodiments a vibration isolation device includes a first and support structure and a sidewall extending between and defining a body of the vibration isolation component. In embodiments the sidewall is configured to structurally support the load. In embodiments the sidewall includes one or more lattice portions occupying at least part of a total area of the sidewall, the lattice portions configured to attenuate a transfer of vibrations through the sidewall between the first and second support structures for reducing vibration transfer from the spacecraft vibration source and the load. In embodiments the body of the vibration isolation device is approximately the same as a component without one or more lattice portions such that the payload interface cone is a drop-in replacement.