Dual-Use Deployable Spacecraft Panel for Solar and RF Aperture
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Solution Overview
Problem
Current spacecraft designs face challenges in efficiently integrating solar power collection and radio frequency (RF) apertures, particularly for smaller satellites, due to volume constraints and the need for separate components that do not scale down well, leading to increased costs and complexity.
Innovation Solution
A deployable spacecraft element with a solar energy collection and conversion layer on one side and a radio frequency reflection layer on the other, oriented in opposite spatial directions, mounted via a gimbal to allow simultaneous collection and transmission, and optionally using a gimbal or subreflector for orientation flexibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate solar arrays and reflectors are used, then high performance is achieved, but volume savings opportunity is lost
Solution Approach 1:
The patent combines separate solar arrays and reflectors into a single integrated structure where the same surface performs both solar power collection and RF reflection functions. This merging eliminates the need for separate components, achieving volume savings while maintaining the performance of both functions through careful design of the dual-layer structure.
Solution Approach 2:
The integrated element serves multiple functions simultaneously: it acts as both a solar array for power generation and an RF reflector for communications. This multi-functionality allows a single component to replace what would traditionally require separate dedicated components, optimizing volume utilization.
2Ease of manufacture
If smaller satellites are used, then cost savings are achieved, but aperture requirements become more challenging
Solution Approach 1:
By merging solar array and reflector functions into one element, the patent effectively doubles the aperture utilization within the same volume constraint. This allows smaller satellites to achieve sufficient aperture area for both power collection and RF communications without requiring proportionally larger structures that would increase cost and complexity.
Solution Approach 2:
The patent utilizes the third dimension (depth/volume) to accommodate dual functionality by stacking functional layers (solar cells on one side, RF reflector on the other). This dimensional approach allows sufficient aperture area to be achieved in a compact volume suitable for small satellites.
3Volume of stationary object
If deployable elements are used, then volume savings are achieved, but device complexity increases
Solution Approach 1:
The patent merges the deployment mechanisms for solar arrays and reflectors into a single coordinated system. This consolidation reduces the number of independent deployment mechanisms required, thereby reducing overall device complexity while still achieving the volume savings benefits of deployable structures.
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 simultaneous solar power collection and RF transmission with reduced volume requirements, cost-effective integration, and improved mission flexibility, while managing center of gravity and torque effects.
Implementation Method 1
The first layer comprises a solar-to-electric collection and conversion means
Implementation Method 2
The second layer comprises a radio frequency reflection means
Data Source
AI summary
A deployable spacecraft element which has a solar energy collection and conversion means on one side of the deployable element and a radio frequency reflecting means on the other side of the deployable element. While the solar collection and conversion means and the radio frequency reflecting means are nominally oriented in opposite spatial directions and dependent on the orientation of the spacecraft to orient for solar collection or radio frequency transmission, one or more deployable elements may be mounted to a gimbal to allow for simultaneous solar collection and radio frequency collection by the spacecraft.