Side-by-side spacecraft launch configuration
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Solution Overview
Problem
Conventional dual-launch configurations for spacecraft are inefficient in terms of structural mass and cost, as they often require one spacecraft to support another, necessitating additional load-bearing structures and increasing complexity and mass, while also limiting the aspect ratio and panel arrangements of the spacecraft.
Innovation Solution
A side-by-side configuration where multiple spacecraft share a launch vehicle payload fairing volume, each with a direct structural interface to a single adapter, using releasable holddown devices to maintain clearance and resist launch loads, allowing for a larger aspect ratio and reducing the need for additional load-bearing structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional stacked dual-launch configuration is used, then one spacecraft can support the other during launch, but additional load-bearing structures are required increasing mass and complexity
Solution Approach 1:
The patent transitions from a vertical stacked configuration to a side-by-side horizontal configuration within the payload fairing. This dimensional change allows both spacecraft to interface directly with the launch vehicle adapter ring, eliminating the need for one spacecraft to support the other, thereby reducing the mass and complexity of load-bearing structures.
2Productivity
If conventional stacked dual-launch configuration is used, then spacecraft can be launched simultaneously, but structural complexity and cost increase
Solution Approach 1:
The patent divides the payload fairing into separate side-by-side compartments, each accommodating an independent spacecraft with its own direct interface to the adapter ring. This segmentation allows simultaneous launch of multiple spacecraft while maintaining structural independence, reducing overall system complexity and cost.
3Volume of stationary object
If conventional stacked configuration is used, then payload fairing volume is utilized, but aspect ratio and panel arrangement of spacecraft are limited
Solution Approach 1:
By arranging spacecraft side-by-side horizontally rather than stacking them vertically, the patent enables each spacecraft to achieve a larger aspect ratio with expanded panel areas. This dimensional reconfiguration optimizes the payload fairing volume utilization while accommodating spacecraft with improved geometric characteristics for better thermal and structural performance.
Data Source
AI summary
A launch vehicle payload that includes at least two spacecraft is disclosed. The launch vehicle includes a single payload adapter. Each spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the single launch vehicle payload adapter. The spacecraft share a launch vehicle payload fairing volume substantially side-by-side and are detachably coupled together such that a positive clearance is provided between adjacent, non-abutting structural body surfaces of each spacecraft.