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 payloads become heavier along with increasing mission complexity, there is an increasing need for a lighter mechanism to separate two-stage rockets in a more reusable, easier to inspect, and efficient way.
The Vacuum Lock can provide:
- Reducing rocket weight, making extra space for the rocket payload.
- Easier to inspect — O-ring and the O-ring groove are easier to inspect than pyrotechnics.
- Using fewer components to separate rocket stages, through manipulation of the vacuum lock mechanism using natural pressure of Earth’s 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 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 releases gas from the environment room to outer space, 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 = pressure inside the vacuum chamber
- V = volume of the vacuum chamber
- n = number of gas moles
- R = gas constant (8.314 J/(mol·K))
- T = 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 = force acting on the O-ring
- P = pressure difference between inside and outside the tank (1 bar or 100 kPa)
- A = 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 outer space), the pressure difference will be zero between the vacuum chamber, environment room, and outer space, causing the vacuum chamber lock mechanism to collapse. This can be predicted using the pressure difference equation:
ΔP = Poutside − Pinside
Where:
- ΔP = pressure difference between two areas
- Poutside = pressure outside the system (e.g., 1 bar or other depending on conditions)
- Pinside = pressure inside the system (e.g., vacuum space inside the chamber)
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 year
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