Open-Sided Spacecraft Central Cylinder Mass Reduction
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Solution Overview
Problem
Conventional 3-axis stabilized spacecraft have redundant structural elements that increase mass and cost, reducing the operational life by limiting the amount of propellant that can be carried for orbit insertion and station-keeping.
Innovation Solution
A spacecraft design featuring a central cylinder as the only closed cross-section along its longitudinal axis, with open sides devoid of rigid members, supported by non-rigid closeouts and a propellant tank housed within the central cylinder, which transfers loads to the launch vehicle and provides structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional box-like structural arrangement is used, then structural strength and component mounting capability are improved, but structural mass increases
Solution Approach 1:
The patent removes redundant outer panels from the spacecraft structure, extracting only the essential load-carrying function and eliminating unnecessary mass. The structure transitions from a fully enclosed box-like arrangement to an open-sided configuration where only the minimum required structural elements remain, directly addressing the contradiction by taking out excessive structural components while maintaining essential strength.
Solution Approach 2:
The central structure and remaining panels are designed to perform multiple functions simultaneously - providing structural support, mounting components, and maintaining spacecraft integrity with minimal elements. This multi-functionality allows the reduced structure to compensate for the removed panels through enhanced functional integration of remaining components.
2Strength
If redundant outer panels are included, then load-carrying capability is improved, but spacecraft mass increases
Solution Approach 1:
The patent extracts and removes the redundant outer panels that provided excessive load-carrying capability, retaining only the essential structural function. The central structure and remaining panels are optimized to carry necessary loads without the mass of unnecessary outer panels, directly resolving the contradiction between load-carrying capability and spacecraft mass.
3Stability of the object's composition
If increased structural mass is used, then structural integrity is improved, but propellant capacity decreases
Solution Approach 1:
The patent extracts unnecessary structural mass through the removal of redundant outer panels, reducing the overall spacecraft mass to allow for increased propellant capacity. The remaining central structure and panels maintain structural integrity through optimized design, enabling the trade-off between structural integrity and propellant capacity in favor of increased propellant.
4Ease of manufacture
If conventional closed box structure is used, then component mounting capability is improved, but access for payload integration is reduced
Solution Approach 1:
The patent removes outer panels to create open sides, extracting the barrier that limited access while maintaining the central structure's ability to mount components. This creates direct access to the spacecraft interior for payload integration while the central structure continues to provide mounting capabilities for essential components.
Data Source
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AI summary
A spacecraft (146) may include a module structure (302) having a plurality of module sides (304). The spacecraft (146) may include a central cylinder (150) extending through a center of the spacecraft (146). The central cylinder (150) may be the only closed cross-section extending along a longitudinal axis of the spacecraft (146).