Deployable Micro-Concentrator Module for Space Solar Energy
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Solution Overview
Problem
MEMS-based micro-concentrator modules for solar energy collectors are bulky and delicate, making them unsuitable for spacecraft applications, as they require significant volume and are vulnerable to compression and acoustic loads during launch.
Innovation Solution
A deployable micro-concentrator module with a thin cover glass and MEMS-based reflectors, where leaf springs bias the cover glass to hover above the substrate, and flexible tethers constrain its displacement to maintain solar cells at the focal length of the reflectors, allowing for stowage during launch and deployment in space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the module is designed with fixed spacing between cover glass and substrate to position solar cells at focal points, then solar energy conversion efficiency is improved, but the module volume increases and vulnerability to launch loads worsens
Solution Approach 1:
The patent transitions from fixed rigid spacing to dynamic deployable spacing using springs and tethers. The cover glass is held against the substrate during launch (stowed configuration) and deployed to the focal distance position in space using spring force, allowing the system to adapt its spacing dynamically based on operational requirements versus launch constraints.
Solution Approach 2:
The cover glass is nested against the substrate during launch by compressing the springs, effectively reducing the module volume to a minimal stowed configuration. Upon deployment, the springs expand to separate the cover glass to the required focal distance, achieving both compact stowage and proper operational spacing.
2Manufacturing precision
If rigid framing or spacers are used to maintain spacing, then manufacturing precision is improved, but device complexity and vulnerability to launch loads worsens
Solution Approach 1:
The patent changes the mechanical state parameters of the spacing system from rigid and fixed to flexible and deployable. Springs provide controlled elastic deformation to achieve precise spacing, while tethers maintain structural integrity during both stowed and deployed states, reducing complexity compared to rigid framing.
3Use of energy by moving object
If the cover glass is positioned at focal length from substrate, then solar energy concentration is improved, but the module cannot be stowed for launch
Solution Approach 1:
The system dynamically changes its configuration between stowed and deployed states. During launch, the cover glass is compressed against the substrate; in space, spring force deploys it to the focal distance position, enabling both stowage capability and optimal energy concentration.
Solution Approach 2:
The springs are pre-loaded during assembly to store elastic potential energy. This preliminary action enables the cover glass to be automatically deployed to the correct focal position when released in space, without requiring additional actuators or complex deployment mechanisms.
4Strength
If rigid structures are used to maintain spacing, then structural strength is improved, but the module becomes more vulnerable to compression and acoustic loads during launch
Solution Approach 1:
The patent uses flexible elements (springs and tethers) instead of rigid structures to maintain spacing. These flexible components can elastically deform under compression and acoustic loads during launch, absorbing stress without causing damage, while still maintaining precise spacing when deployed in the weightless space environment.
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 module minimizes volume during launch, survives G-forces and compression, and efficiently deploys to maximize solar radiation concentration, ensuring reliable operation in deep space while reducing the risk of damage from launch-related stresses.
Implementation Method 1
Leaf springs bias the cover glass away from the underlying substrate during deployment
Implementation Method 2
MEMS based reflectors that concentrate and reflect incident solar radiation onto the solar cells
Implementation Method 3
the solar cells are respectively positioned at the focal points of the MEMS-based reflectors
Data Source
AI summary
A micro-concentrator module includes a cover glass provided with solar cells on one side thereof. The cover glass is adapted to hover above a substrate containing an array of MEMS based reflectors. Springs between the cover glass and the substrate displace the cover glass from a stowed position during transport to a deployed operational position above the substrate. Tethers connecting the cover glass with the substrate limit the displacement of the cover glass to a distance corresponding to the focal length of the reflectors.