Exoskeletal Launch Support Structure for Spacecraft
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Solution Overview
Problem
Current spacecraft structural arrangements are inefficient in managing launch loads, leading to a significant portion of the mission cost being attributed to launch costs, and they do not maximize payload mass delivery to operational orbits for a given launch mass.
Innovation Solution
An exoskeletal launch support structure with a 3-D truss configuration, including coupling nodes and strut elements, provides the primary load path between the spacecraft and the launch vehicle upper stage, allowing the spacecraft to separate and remain with the launch vehicle, while the secondary structure carries minimal launch loads, enabling orbit raising with reduced dry mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional internal load-bearing structures are used in spacecraft, then the spacecraft can withstand launch loads, but the secondary structure mass increases reducing payload capacity
Solution Approach 1:
The invention divides the load-bearing function into two separate structures: an exoskeletal launch support structure that carries launch loads, and a secondary structure that only supports payload equipment. This segmentation allows the secondary structure to be minimized in mass while still fulfilling its specific function of supporting payload equipment during launch and operation.
Solution Approach 2:
The exoskeletal launch support structure acts as an intermediary between the launch vehicle and the spacecraft secondary structure. It temporarily carries launch loads during launch and then is jettisoned, allowing the secondary structure to be much lighter than traditional designs where the secondary structure must carry all launch loads.
2Strength
If the exoskeletal launch support structure remains attached to the spacecraft after launch, then launch loads are well-supported, but the mass for orbit raising is increased
Solution Approach 1:
The exoskeletal launch support structure is designed to be discarded after serving its purpose during launch. It is jettisoned once the spacecraft is in orbit, removing its mass from the spacecraft system. This allows the spacecraft to have reduced dry mass for orbit raising maneuvers while still having robust launch load support during the critical launch phase.
3Reliability
If more mass is allocated to secondary structure for launch load support, then launch reliability improves, but payload mass delivery capability decreases
Solution Approach 1:
By segmenting the load-bearing functions between the exoskeletal launch support structure and the secondary structure, the invention allows the secondary structure to be minimized. This enables more of the launch vehicle's mass budget to be allocated to payload while maintaining robust launch load support through the dedicated exoskeletal structure.
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
A spacecraft includes payload equipment and bus equipment, each of the payload equipment and the bus equipment being coupled with a secondary structure arrangement. The spacecraft is configured to structurally interface with a launch vehicle upper stage only by way of an exoskeletal launch support structure (ELSS) that provides a first load path between a launch vehicle upper stage and the secondary structure arrangement. The spacecraft is configured to deploy from the launch vehicle upper stage by separating from the ELSS. In some implementations, the first load path is the only load path between the spacecraft and the launch vehicle upper stage, and substantially all of the ELSS remains with the launch vehicle upper stage. Because the secondary structure may be substantially less massy then the ELSS, subsequent orbit raising maneuvers may then be executed with a spacecraft having a reduced dry mass.