Modular Reflector Assembly Using Kinematic Magnetic Interfaces
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Solution Overview
Problem
Current spacecraft reflector aperture sizes are limited by launch vehicle fairing dimensions, restricting payload capacity and optical performance, as existing techniques fail to enable large-aperture reflectors without compromising launch vehicle compatibility.
Innovation Solution
A spacecraft reconfigurable from a launch to an on-orbit configuration using deployable modular reflector elements, assembled by a robotic manipulator into a large-aperture, self-supporting reflector with kinematic and magnetic interfaces, allowing for a larger aperture diameter and improved optical performance without external mechanical support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If a rigid reflector is used to maintain optical quality, then the reflector surface accuracy is improved, but the aperture diameter is limited by the launch vehicle fairing dimensions
Solution Approach 1:
The reflector is divided into multiple deployable modular panels that can be stowed in a compact configuration during launch and deployed to form a large-aperture surface in orbit. This segmentation allows the reflector to bypass fairing dimension constraints while maintaining the required optical surface accuracy through precise panel alignment mechanisms.
Solution Approach 2:
The reflector transitions from a static, fixed-size structure constrained by launch vehicle dimensions to a dynamic, deployable structure that can achieve a large aperture in orbit. The modular panels are designed to be movable and reconfigurable, enabling the system to optimize its aperture size after launch without compromising structural integrity or surface accuracy.
2Area of stationary object
If an unfurlable reflector is used to increase aperture diameter, then the aperture size is improved, but the optical quality deteriorates compared to rigid reflectors
Solution Approach 1:
By dividing the reflector into rigid modular panels with precise edge alignment features, the system maintains optical quality across the entire aperture. Each panel acts as a rigid segment with controlled surface accuracy, and the segmented design allows for thermal expansion compensation and structural support that preserves optical performance across the large aperture.
Solution Approach 2:
The patent replaces traditional mechanical support structures with self-aligning interfaces between modular panels. The panels utilize precision-machined edges and alignment features that automatically position themselves to maintain the required optical surface accuracy, eliminating the need for complex mechanical support systems while preserving optical quality.
3Area of stationary object
If modular reflector elements are assembled on-orbit to exceed fairing dimensions, then the aperture diameter is improved, but the assembly complexity increases
Solution Approach 1:
The reflector is segmented into standardized modular panels that can be manufactured, tested, and validated independently before launch. This standardization reduces assembly complexity by ensuring interchangeability and consistency across all modules, allowing for systematic assembly procedures and simplified integration processes during on-orbit deployment.
Solution Approach 2:
The modular panels incorporate self-aligning interfaces and automated connection mechanisms that reduce the complexity of on-orbit assembly. The panels are designed to automatically position and connect to adjacent modules through precision-machined features and alignment mechanisms, minimizing the need for complex manual assembly procedures and reducing the skill level required for deployment operations.
4Stability of the object's composition
If external mechanical support structures are used to maintain reflector shape, then the structural stability is improved, but the device complexity and weight increase
Solution Approach 1:
The patent extracts and eliminates the need for external mechanical support structures by incorporating rigid, self-supporting modular panels with inherent structural stability. Each panel is designed as a self-contained unit with sufficient rigidity to maintain its shape and position without requiring additional external supports, thereby reducing overall system complexity and weight while preserving reflector shape stability.
Solution Approach 2:
The modular panels utilize self-aligning interfaces and built-in structural features that automatically maintain the reflector's shape and position. The panels are designed to self-support through their own rigidity and alignment mechanisms, eliminating the need for external support structures and reducing system complexity while ensuring structural stability.
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
Enables the formation of large-aperture reflectors exceeding launch vehicle fairing dimensions, enhancing payload capacity and optical performance while maintaining launch vehicle compatibility, and reducing the need for backup structural elements.
Implementation Method 1
The assembly of the modular reflector elements may include one or both of self-aligning kinematic and magnetic interfaces that couple adjacent modular elements
Data Source
AI summary
A spacecraft includes a main body structure and a plurality of deployable modular reflector elements, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the modular reflector elements are disposed in a storage system that includes an arrangement for supporting the modular reflector elements with respect to dynamic launch loads. In the on-orbit configuration, in some implementations, an assembly of the plurality of modular reflector elements forms a large-aperture, offset fed, reflector, the reflector being coupled with a boom or yoke with the main body structure by way of a two or three axis positioning mechanism configured to steer the reflector with respect to the main body structure. In some implementations, in the on-orbit configuration, the plurality of modular reflector elements are assembled to form a large aperture reflective surface that is self-supporting.