Reconfigurable Model Rocket Staging Adapter
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Solution Overview
Problem
Conventional multi-stage model rockets often lose stages during return due to separation issues and experience frequent failure of the second stage to ignite, leading to inefficiencies in propulsion and recovery.
Innovation Solution
A reconfigurable model rocket system that can operate in single-stage or dual-stage configurations, utilizing a staging adapter and staging cone to efficiently transfer combustion gases from the booster stage to the upper stage, ensuring optimal ignition of the upper stage propellant.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional multi-stage rockets separate stages after propellant expenditure, then each stage can be recovered independently, but stages are lost during return fall and second stage ignition fails frequently
Solution Approach 1:
The patent implements nesting by placing the second stage engine and propellant inside the first stage structure. The second stage is housed within the first stage's tail section, creating a compact multi-stage configuration where stages are nested rather than separately mounted. This reduces overall rocket complexity while maintaining reliable staged operation.
Solution Approach 2:
The patent introduces a staging adapter as an intermediary component that facilitates controlled separation and ignition transfer between stages. The adapter includes a separation pin mechanism and ignition transfer channel that mediate the transition from first to second stage, ensuring reliable ignition while simplifying the overall separation process.
2Use of energy by moving object
If multi-stage configuration is used to reach higher altitudes, then propulsion efficiency improves, but stages get lost during return fall
Solution Approach 1:
The patent merges the recovery function across both stages by designing them as a coordinated system. The first stage acts as a protective container and deployment mechanism for the second stage during recovery. Both stages are recovered together as an integrated unit, preventing loss of individual stages while maintaining the propulsion efficiency benefits of multi-stage configuration.
Solution Approach 2:
The patent segments the recovery process into controlled phases: descent with stages connected, controlled separation at appropriate altitude, and individual stage recovery. This segmentation allows the rocket to benefit from multi-stage propulsion while systematically managing recovery to prevent stage loss.
3Device complexity
If second stage is housed within first stage structure, then overall rocket complexity is reduced, but combustion gases transfer for ignition becomes difficult
Solution Approach 1:
The patent uses pneumatic principles by designing a dedicated combustion gas transfer channel within the staging adapter. The channel utilizes pressure differential and gas flow dynamics to efficiently transfer combustion gases from the first stage to ignite the second stage propellant, solving the ignition transfer problem while maintaining structural compactness.
Solution Approach 2:
The patent applies local quality by creating a specialized ignition transfer channel with specific geometric properties optimized for combustion gas flow. The channel includes features such as appropriate diameter, length, and orientation to ensure efficient gas transfer from the first stage combustion chamber to the second stage propellant, addressing the local ignition requirement without increasing overall complexity.
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 efficient propulsion in both single and dual-stage configurations, with the dual-stage configuration allowing the rocket to reach higher altitudes than when flown as a single-stage rocket, while ensuring reliable ignition and separation of stages for improved recovery.
Implementation Method 1
The first tail section accommodates a first rocket engine having a combustible propellant to propel the model rocket by allowing gases from the combustible propellant to escape from the bottom end of the first tail section
Implementation Method 2
The second tail section accommodates a second rocket engine having a combustible propellant to propel the model rocket by allowing gases from the combustible propellant to escape from the bottom end of the second tail section
Implementation Method 3
The staging cone is configured to transfer combustion gases from the top of the second tail section into the bottom of the first tail section, via the staging adapter, so as to ignite the first rocket engine when the combustible propellant of the second rocket engine has been depleted
Data Source
AI summary
A reconfigurable model rocket that can be flown either in a single-stage or a two-stage configuration is disclosed. The model rocket has a main body tube, a nose cone, a first tail section, a second tail section, and a staging adapter. The nose cone is removably coupleable to a top end of the main body tube and the first tail section is removably coupleable to a bottom end of the main body tube. The first tail section accommodates a first rocket engine to propel the model rocket by allowing gases from a combustible propellant to escape from the bottom end of the first tail section. The second tail section is removably coupleable to a bottom end of the first tail section and accommodates a second rocket engine to propel the model rocket by allowing gases from a combustible propellant to escape from the bottom end of the second tail section.