Dual Detent Release Structure for Preventing Rocket Separation
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Solution Overview
Problem
Existing detent apparatuses for rockets lack a mechanism to prevent unintentional separation during launch, which can compromise the stability and safety of the rocket launch process.
Innovation Solution
A dual detent apparatus incorporating both mechanical and electrical safety devices, featuring a detent with a rotation axis, an elastic body to support the detent, and an electrical safety device with a hinge axis, solenoid, and micro switch to control detent rotation, ensuring secure fixation of the rocket.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a mechanical safety device is used to fix the rocket, then the rocket can be stably fixed before launch, but the rocket may still experience unintentional separation due to lack of additional safety mechanisms
Solution Approach 1:
The detent apparatus is divided into two independent safety devices: a mechanical safety device (including detent, elastic body, and detent holder) and an electrical safety device (including solenoid, micro switch, and hinge mechanism). Each device operates independently to provide rocket fixation, allowing the system to maintain high reliability while keeping each individual device relatively simple in structure.
2Reliability
If both mechanical and electrical safety devices are combined, then unintentional separation is prevented, but the device complexity increases
Solution Approach 1:
The mechanical safety device and electrical safety device are merged into a single integrated detent apparatus that shares common structural elements (such as the detent, detent holder, and hinge mechanism). This merging allows the system to achieve enhanced reliability through dual safety mechanisms while minimizing the increase in overall device complexity by reusing existing components.
3Reliability
If the detent is designed to rotate around a fixed axis, then the mechanical fixation is achieved, but the system lacks active control capability for preventing unintentional separation
Solution Approach 1:
The detent mechanism transitions from a purely passive mechanical structure to a dynamic system with active control capability. The detent can rotate around a fixed hinge axis to provide mechanical fixation, while the solenoid provides active electromagnetic control to adjust the detent position and prevent unintentional separation. This dynamic design allows the system to maintain mechanical stability while gaining automated control functionality.
4Reliability
If the elastic body supports the detent, then the mechanical fixation is stable, but the system lacks a mechanism to actively release or adjust the fixation
Solution Approach 1:
The purely mechanical elastic body support system is enhanced by introducing an electromagnetic actuation system (solenoid). The elastic body continues to provide stable mechanical fixation support, while the solenoid replaces the need for manual adjustment mechanisms, providing automated electromagnetic control to release or adjust the fixation as needed.
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
The dual detent apparatus effectively prevents unintentional rocket separation by combining mechanical and electrical mechanisms, enhancing launch stability and safety.
Implementation Method 1
a solenoid configured to rotate the detent support by pushing the detent support
Implementation Method 2
a first elastic body configured to elastically support the first end portion of the detent
Implementation Method 3
a micro switch activated when the detent support rotates
Data Source
AI summary
Provided is a detent apparatus for a rocket, The detent apparatus includes a detent including a first end portion, a second end portion opposite to the first end portion, an extension extending between the first end portion and the second end portion, and a detent protrusion configured to engage with the rocket, a first elastic body configured to elastically support the first end portion of the detent and connected to the first end portion, and an electrical safety device configured to prevent rotation of the detent including a hinge fixing frame having a hinge axis parallel to the detent rotation axis, a detent support configured to rotate around the hinge axis and support the detent, a hinge axis shaft arranged on the hinge axis, a solenoid configured to rotate the detent support by pushing the detent support, and a micro switch activated when the detent support rotates.