Stackable Spacecraft Layout With Side Mounting Cylinder
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Solution Overview
Problem
Existing satellite launch systems face challenges in reducing costs and minimizing weight and volume by stacking multiple satellites, as central cylinders in current designs obstruct space for essential components like antennas and heat pipes, and interfere with heat removal, especially when oriented in the Y-direction through the earth deck.
Innovation Solution
A three-axis satellite design with a central mounting cylinder oriented in the east/west direction allows for unobstructed space on the earth deck for antennas and heat pipes, enabling efficient stacking and reducing interference with heat removal systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If multiple satellites are mounted to a common cylindrical dispenser within the launch vehicle, then the cost of launching each satellite is reduced, but the weight and volume of the launch vehicle increase significantly
Solution Approach 1:
The invention divides the launch vehicle into modular segments, with each satellite carrying its own stacking interface cylinder rather than relying on a single large common dispenser. This segmentation reduces the overall weight and volume of the launch vehicle while maintaining the ability to launch multiple satellites together.
Solution Approach 2:
The invention combines the stacking interface functionality directly into each satellite's structure, merging the previously separate dispenser function with the satellite body. This eliminates the need for a large common dispenser and reduces launch vehicle weight and volume.
2Adaptability or versatility
If a central cylinder extends through the satellite in the Y-direction through the earth deck and zenith deck, then the satellite can be coupled to other satellites in the launch vehicle, but space on the earth deck is limited for antennas and electronic equipment
Solution Approach 1:
The invention changes the orientation of the stacking interface cylinder from the Y-direction (through earth deck and zenith deck) to the Z-direction (through the side panels). This dimensional change allows the earth deck to be fully utilized for antennas and electronic equipment while maintaining satellite coupling capability through the reoriented cylinder.
3Adaptability or versatility
If a central cylinder extends through the satellite in the Y-direction, then satellite stacking is enabled, but heat pipe placement and heat removal are interfered with
Solution Approach 1:
The invention reorients the stacking interface cylinder from the Y-direction to the Z-direction, moving it away from the earth deck where heat pipes are typically placed. This dimensional change eliminates interference with heat pipe placement and maintains efficient heat removal pathways while preserving satellite stacking capability.
4Productivity
If the number of satellites in a single launch vehicle is increased, then the cost per satellite is reduced, but the weight of the launch vehicle increases
Solution Approach 1:
The invention segments the stacking interface functionality into individual satellites rather than using a large common dispenser, reducing the weight added per satellite and allowing more satellites to be launched together without proportionally increasing launch vehicle weight.
Solution Approach 2:
The invention changes the structural parameters of the stacking interface by integrating cylinders directly into satellite bodies with reduced dimensions compared to a common dispenser, allowing increased satellite density in the launch vehicle without proportional weight increase.
Data Source
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AI summary
A three-axis spacecraft including a spacecraft body including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck. The zenith deck faces the Earth when the spacecraft is on orbit and the first and second mounting panels face an east and west direction relative to the Earth when the spacecraft is on orbit. The spacecraft further includes a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels.