Deployable Spacecraft Modules for Launch Fairing Constraints
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Solution Overview
Problem
There is a need for a high capacity spacecraft that is compatible with conventional launch vehicle constraints while meeting increasing payload capacity and heat dissipation requirements, with existing designs often compromising on these aspects.
Innovation Solution
The spacecraft configuration includes two large deployable modules with separate axes of rotation, a central structural portion, and thrusters, allowing for reconfiguration from a launch to an on-orbit configuration with increased payload and thermal dissipation surface areas, while maintaining compatibility with launch vehicles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If a single large spacecraft is designed to meet payload capacity requirements, then the payload capacity is improved, but the spacecraft cannot fit within conventional launch vehicle fairing envelopes
Solution Approach 1:
The spacecraft is divided into multiple deployable modules that can be stacked together to form the complete satellite. Each module contains its own solar arrays and payload equipment, allowing the spacecraft to fit within launch vehicle fairing envelopes while achieving high payload capacity when deployed in orbit
Solution Approach 2:
The spacecraft transitions from a compact three-dimensional configuration during launch to an extended planar configuration in orbit, with solar arrays deployed perpendicular to the launch direction, effectively utilizing the radial dimension to achieve large surface area without increasing launch volume
2Power
If the solar array surface area is increased to meet power requirements, then the power generation capability is improved, but the solar arrays become vulnerable to thruster plume impingement
Solution Approach 1:
The solar arrays are segmented and mounted on separate deployable modules positioned at different locations along the spacecraft structure. This spatial separation ensures that solar arrays are not in the direct path of thruster plumes during orbital maneuvers, eliminating plume impingement damage while maintaining large total surface area for power generation
Solution Approach 2:
The deployable module structure acts as an intermediary between the thrusters and solar arrays, positioning the solar arrays in locations that avoid direct exposure to thruster plumes while still allowing large surface area deployment for adequate power generation
3Adaptability or versatility
If multiple antenna apertures are added to meet communications requirements, then the communications capability is improved, but the spacecraft complexity increases
Solution Approach 1:
Multiple antenna apertures are distributed across separate deployable modules rather than concentrating all communication equipment in a single complex structure. Each module can be independently configured with appropriate antenna types, simplifying the overall system architecture while providing versatile communications capabilities
Solution Approach 2:
The deployable module design provides a universal platform that can accommodate different types of antenna apertures and payload equipment. The same modular structure supports various communication frequencies and antenna configurations, reducing overall spacecraft complexity through standardization
Data Source
AI summary
A spacecraft includes a first deployable module and a second deployable module and is reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable module is adjacent to the second deployable module. The first deployable module includes a first solar array, the first solar array being rotatable, in the on-orbit configuration, about a first axis of rotation, and the second deployable module includes a second solar array, the second solar array being rotatable, in the on-orbit configuration, about a second axis of rotation, the second axis of rotation being separated by a substantial distance from the second axis of rotation.