Stackable Pancake Satellite for Launch Cost Reduction
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Solution Overview
Problem
The high cost of launching satellites is constrained by the limited number of satellites that can be supported by a launch vehicle and the geometry of the payload fairing, necessitating improved satellite designs that optimize storage and deployment within these constraints.
Innovation Solution
A stackable pancake satellite design comprising hingedly attached sections that fold into a flat configuration for launch, unfolding into separate components upon reaching orbit, including a satellite body with a thermal radiator, solar panels, and a splash plate reflector, allowing for efficient stacking and deployment within a launch vehicle fairing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites are launched individually, then each satellite can be optimized for its specific mission, but the launch cost per satellite is high due to limited payload capacity utilization
Solution Approach 1:
The satellite system is divided into modular stackable units that can be launched together as a group. Each satellite maintains its individual mission optimization while being part of a stacked configuration, allowing multiple satellites to share a single launch vehicle and reduce per-satellite launch costs
Solution Approach 2:
Multiple satellites are merged into a single stacked payload configuration for launch. The satellites are combined in a vertical stack within the payload fairing, enabling them to be transported and deployed together while maintaining individual functional independence
2Device complexity
If the payload fairing geometry is fixed, then the launch vehicle structure is simplified, but the satellite geometry is constrained limiting design flexibility
Solution Approach 1:
The satellite design transitions from traditional horizontal or complex 3D configurations to a vertical stacked arrangement within the payload fairing. This dimensional reorganization allows satellites to fit within the fixed fairing geometry while maintaining design flexibility through modular stacking and varied satellite orientations
3Productivity
If multiple satellites are stacked in a payload fairing, then launch cost per satellite is reduced, but the deployment complexity increases
Solution Approach 1:
Satellites are pre-configured in a stacked arrangement within the payload fairing before launch. The modular design allows for pre-assembled units that can be deployed sequentially through predetermined mechanisms, reducing the complexity of in-orbit assembly while maintaining cost efficiency
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
This design enables multiple satellites to be launched simultaneously at reduced costs by minimizing deployment complexity and using a modest propulsion system, while optimizing thermal management and signal reflection, thus enhancing reliability and reducing launch expenses.
Implementation Method 1
a first one of the sections is a satellite body having a first side that acts as a thermal radiator
Implementation Method 2
a second one of the sections includes at least one solar panel... wherein light from the Sun is converted to electricity by the solar panel
Implementation Method 3
a third one of the sections includes at least one splash plate reflector... wherein radio frequency signals between Earth and the antenna of the satellite are reflected by the splash plate reflector
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.