Launch Vehicle Payload Modules Abutting Support
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Solution Overview
Problem
Launching multiple spacecraft with a single launch vehicle is costly due to the weight added by existing frameworks that do not contribute to the mission, such as the SPELTRA structure used with the Ariane rocket, which adds significant non-mission benefiting weight.
Innovation Solution
A system and method involving launch modules with package elements that are arranged in an abuttingly supporting relation and secured by restraining members to maintain a launch orientation parallel to the launch vehicle's axis, allowing for the deployment of multiple independent payloads without adding significant weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a specialized framework like SPELTRA is used to affix multiple satellites atop the rocket vehicle, then multiple payloads can be launched with a single launch vehicle, but the framework adds considerable weight to the payload that does not contribute to the mission
Solution Approach 1:
The payload is divided into multiple independent modules (first module, second module, third module) that can be separately attached to the launch vehicle. Each module contains its own payload, allowing multiple payloads to be launched without requiring a heavy integrated framework like SPELTRA. The modules are segmented and distributed along the launch vehicle body.
Solution Approach 2:
Instead of stacking payloads vertically along the longitudinal axis (as with SPELTRA), the invention distributes modules in multiple spatial dimensions - attaching modules to the sides and rear of the launch vehicle body. This dimensional redistribution eliminates the need for a heavy central framework while still achieving multi-payload deployment.
2Weight of moving object
If modules are distributed away from the longitudinal axis of the launch vehicle, then weight is reduced and flexibility is improved, but the center of gravity may shift away from the longitudinal axis affecting flight stability
Solution Approach 1:
Different modules are attached at different locations with different orientations. The first module is attached at the front with its longitudinal axis aligned with the launch vehicle, the second module is attached at the side, and the third module is attached at the rear. This local variation in attachment positions and orientations allows weight distribution that maintains flight stability while reducing overall framework weight.
Solution Approach 2:
The module attachment system allows for flexible configuration where modules can be positioned at different locations along the launch vehicle. This dynamic arrangement enables the center of gravity to be adjusted and maintained along the longitudinal axis during flight, ensuring stability while allowing weight reduction through optimized module placement.
Data Source
AI summary
A system for deploying a plurality of independent payloads with a launch vehicle, the launch vehicle being longitudinally oriented about an axis, includes a plurality of launch modules. Each respective launch module of the plurality of launch modules includes a plurality of package elements. A respective predetermined set of package elements of the plurality of package elements comprises a respective payload of the plurality of payloads. Each respective launch module of the plurality of launch modules is situated in an abuttingly supporting relation with at least one adjacent launch module in a facing relation at an interface in a launch orientation. The interface is generally parallel with the axis. At least one restraining member cooperates with the plurality of launch modules to effect compressingly maintaining the plurality of launch modules in the launch orientation.