Rotating Landing Shell for Stable Non-Tubular Rocket Recovery
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Solution Overview
Problem
Current methods for retrieving non-tubular rocket stages, which have non-circular cross sections, face challenges in achieving safe and stable vertical landings without adding weight, as they require additional landing elements that decrease fuel efficiency and increase refurbishment costs.
Innovation Solution
A non-tubular rocket stage landing apparatus comprising a platform, dampening cushioning device, exhaust diffuser device, hollow shell, and supporting, positioning, and rotating device, which guides and stabilizes the landing without adding weight, using a separate system to manage hot gases and ensure safe landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If landing elements are incorporated into the non-tubular rocket stage, then the rocket can achieve stable vertical landing, but the rocket weight increases and fuel efficiency decreases
Solution Approach 1:
The landing system is divided into two separate components: the non-tubular rocket stage and the landing apparatus. The rocket stage retains its lightweight non-tubular structure for payload capacity, while the landing apparatus with stabilization fins and cushioning elements provides the necessary landing stability. This segmentation allows each component to be optimized independently - the rocket for payload efficiency and the landing apparatus for stable retrieval.
2Reliability
If landing elements are incorporated into the non-tubular rocket stage, then the rocket can achieve stable vertical landing, but refurbishment costs increase
Solution Approach 1:
By separating the landing elements from the rocket stage, the patent enables independent refurbishment. The landing apparatus can be recovered, inspected, and repaired separately from the valuable non-tubular rocket stage, reducing overall refurbishment costs and simplifying maintenance operations.
Solution Approach 2:
The landing apparatus is designed as a disposable or easily replaceable component. If damaged during landing, it can be replaced more economically than repairing the expensive non-tubular rocket stage, thus reducing overall refurbishment costs while maintaining landing reliability.
3Use of energy by moving object
If a separate landing apparatus is used, then fuel efficiency is improved, but the complexity of the landing system increases
Solution Approach 1:
The landing apparatus is designed as a universal platform that can accommodate multiple non-tubular rocket stages with different configurations. The standardized interface and positioning system allow the same landing apparatus to retrieve various rocket designs, reducing overall system complexity despite the added component.
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
Enables safe and stable vertical landing of non-tubular rocket stages with minimal fuel consumption and reduced refurbishment needs, facilitating cost-effective reuse.
Implementation Method 1
a dampening cushioning device configured to reduce the force of impact when the landing non-tubular rocket stage contacts the platform
Implementation Method 2
an exhaust diffuser device configured to direct hot gases from ignited fuel away from the dampening cushioning device on the platform, and avoid having the hot gas blowing back to the landing non-tubular rocket stage
Data Source
AI summary
A non-tubular rocket stage landing apparatus for more reliably landing and returning a non-tubular rocket stage for reuse in subsequent main missions. The non-tubular rocket stage landing apparatus comprises a platform, a dampening and cushioning device, an exhaust diffuser device, a hollow shell, and a rotational device for angular aligning the hollow shell with the pass-through non-circular circumference of a vertically landing non-tubular rocket stage.