Open Research Proposal : Reusable Vacuum Lock Mechanism for Rocket Stage Separation
VACUUM LOCK: NO MOVING PART ROCKET STAGE SEPARATION MECHANISM WITHOUT TRADITIONAL BOLT AND NUT
1. Executive Summary
The current two-stage separation mechanism in the existing rocket uses pyrotechnic bolts, which have limitations in reusability, complexity, and weight inefficiency. This proposal suggests the development of the Vacuum Lock, a mechanism that can lock, hold, and separate the two-stage rocket without bolts and nuts. It is easier to inspect, cheaper, lighter than the existing mechanism, and finally, it provides extra payload capacity for the mission.
2. Background & Objectives
as space rocket payload become heavier as the complexity of the mission, there is and increasing need for lighter mechanism to separating 2 stage rocket with more reusable, easier to inspect, reusable, efficient way.
The Vacuum Lock can provide :
1.Reducing rocket weight, make extra space for the rocket payload.
2.Easier to inspect, oring and the oring groove easier to inspect than pyrotechnic
3.using less component to separate rocket stage, through manipulation on vacuum lock mechanism using natural pressure of earth atmosphere and the vacuum of space.
3. Methodology
Design and Explanation of the Vacuum System
The vacuum locking system will be placed in an environment room with an atmospheric pressure of 1 bar. The vacuum chamber holding the two stages of the rocket will maintain a low pressure (vacuum) inside, while the environment room will have a pressure of 1 bar. This system will use O-rings to prevent air leakage in the vacuum chamber, as well as solenoids to release air from the environment room to the outer space and trigger separation.
Separation Process
The pressure difference between the vacuum chamber and the environment room with 1 bar gas will lock the two rocket stages together. When the rocket is in space (with near 0 bar pressure), the solenoid releasing gas from environment room to the outerspace and collapsing the vacuum lock. Then propellant gas will assist in separating the two rocket stages and make the collapse of the vacuum lock quicker.
Equations for Explaining the Pressure in the System:
Ideal Gas Law (Pressure and Volume in the Vacuum Tank)
According to the ideal gas law, the relationship between pressure (P), volume (V), number of gas moles (n), and temperature (T) is given by:
PV=nRT
Where:
P: is the pressure inside the vacuum chamber,
V: is the volume of the vacuum chamber,
n: is the number of gas moles,
R: is the gas constant (8.314 J/(mol·K)),
T: is the temperature in Kelvin.
In the vacuum state, P will be very small, but this pressure change is sufficient to provide the force needed to lock the two rocket stages.
Pressure Force on the O-Ring
The force experienced by an O-ring installed in the groove (slot) can be calculated using the pressure force equation caused by the pressure difference between the vacuum chamber and the outside atmosphere (1 bar):
F=P×A
Where:
F: is the force acting on the O-ring,
P: is the pressure difference between inside and outside the tank (1 bar or 100 kPa),
A: is the contact area of the O-ring with the groove.
Pressure and Volume in the Vacuum Chamber
Initially, the vacuum tank will be filled with a low internal pressure (e.g., 10^-3 bar), and after the lock is engaged, the environment room will have a pressure of 1 bar. When the separation occurs (solenoid releasing 1 bar pressure to the outer space)), the pressure difference will be zero between vacuum chamber, environment room, and outer space, cause the vacuum chamber lock mechanism to collapse, This can be predicted using the pressure difference equation:
ΔP=P outside−Pinside
Where:
ΔP (Delta P) = Pressure difference between two areas.
This shows how much pressure differs between the outside and inside of a system.
Units: Pascals (Pa) or bar.
P_outside = Pressure outside the system (e.g., atmospheric pressure outside the tube, which could be 1 bar or another pressure depending on the conditions).
P_inside = Pressure inside the system (e.g., vacuum space inside the tube or a closed chamber with lower pressure).
Separation occurs when ΔP is sufficient to trigger movement and the separation of the rocket stages.
4. Team & Qualifications
Hanung Bayu Adji – Heavy Equipment Mechanic
Potential Collaborators – Material scientists and aerospace engineers to support the development and testing of the system.
5. Estimated Budget & Timeline
Project Duration: 1 years
Budget: $100,000
Material Testing: $25,000
Design and Simulation: $35,000
Testing and Prototyping: $40,000
6. Conclusion
This vacuum locking system provides a simpler and more efficient solution for rocket stage separation. By utilizing the pressure difference between the vacuum chamber and the environment room, we can reduce weight, improve efficiency, and decrease mechanical complexity in the rocket stage separation system.
7. Contact
Name: Hanung Bayu Adji
Email: hanungbadji@gmail.com
Institution: -
Reusable Vacuum Lock Mechanism for Rocket Stage Separation by Hanung Bayu Adji is licensed under Creative Commons Attribution 4.0 International
