Author: darkdave

UPDATE:

Oxygen is lighter than CO2 so the tunnel will need to be adjusted accordingly:

Humans can settle in the Oxygen bubble cavities that are above a lower CO2 zone that has a water lake that the nuclear thermal reactor uses as a radiator thus keeping it warm. This CO2 zone can be rich vegetation zone with algae and trees converting CO2 to oxygen that floats into the habitable region accessible by ramp.

 

ORIGINAL ARTICLE:

Considering the scale height of Mars being 11km and Earth’s 8km, the difference considering the lower Martian gravity gives us hope to live inside  rather than on Mars without preassure suits, a 55km deep tunnel on Mars with a “silo” built into the vertical shaft can allow humans to live in Mars in the lower end of the tunnel where there is 1 bar of atmospheric preassure, there and any cavity excavated out horizontally after that.

The silo could be a nuclear thermal powered structure with a built in drill bit. We can have artificial lighting powered by a nuclear thermal reactor and waste heat from it could keep the air warm by heating artificial lakes.

What is a scale height:

https://en.wikipedia.org/wiki/Scale_height

 

If built at the equator we get sunlight directly under the vertical shaft, if built at the poles we will need a system of mirrors and crystals to light the bottom portion. The poles is more guaranteed to provide us with ice and water that we will need to live on that our thermal reactor can heat and melt.

Inspiration of the megastructure from the TV series SILO:

 

The Space Plane Corporation

space-plane.org

Video:

https://fb.watch/xfXW2HlEqL/

Performance Summary:

MTOW: 250 tons

Dry Mass: 75 tons

Useful Payload: 5-10 tons

When considering 500km ISS orbital insertion and de-orbit fuel burn the useful payload does shrink to between 5-10 tons.

Telemetry:

https://drive.google.com/file/d/1zLmh4odwt-ejBSnMvJu-8BUq4YvuFtzn/view?usp=sharing

Introduction:

We can give the moon an atmosphere, how do I know this? Because Titan which is about the same size as our moon has a thick atmosphere. The difference is that Titan is cold, damn cold! So if we dig a 290km tunnel we can create a solar shielded section inside the moon that can sustain atmosphere and expand that section horizontally. The scale altitude I have worked out is 12.4km.

Main Article:

Similar to my idea to dig in Mars I figured this would be more practical and useful for the moon. If we dig 290km deep: we can sustain an atmosphere of 1 bar. This was calculated by working out the scale altitude of the moon being 12.4km.

The illustrated vertical section will be cryogenic temperature gas. This makes mining the moon from the inside out more practical and safe with an atmosphere eliminating the risk of decompression. I had to work out the scale altitude of the moon despite it being a vacuum. It still has gravity. The main difference between our moon and Titan is that Titan is colder, this is why Titan can have an atmosphere while our hot moon cannot. So I figured we might as well replicate Titan in the moon with a tunnel that the sun cannot heat up. This way we can seal the tunnel into sections. The vertical section of the tunnel in the moon can be air sealed but not to keep in or out any pressure but instead to keep the warm air in (cold air out). The hatch only needs to be thermally shielded. It does not need to be rated to keep a vacuum in our out. If the hatch breaks we have time to to repair/replace the hatch without the risk of violent de-compresion. We will only be fighting the cold. So we can suit up in suits that are less demanding that just keep us warm while we repair it. We can also have multiple doors seals as redundancy. Let me know in the comment section if you like this idea or not!

 

 

We replaced mach-11-18 with air breathing rocket mode based on paper linked below:

https://drive.google.com/file/d/16jeWe22zYj1rESzAH-69CrnO4X_hP__9/view?usp=sharing

UPDATE:

After more optizations, the data below is now outdated and we have improved our numbers: Useful Payload with SSTO is now 18 tons, not 13 tons.

==================ORIGINAL ARTICLE BELOW

Ascent Profie in this Spreadsheet:

https://drive.google.com/file/d/1J49OjoynbX2rmvTja1ZU6C87u_y0yIom/view?usp=sharing

Computer simulations have confirmed that The Space-Plane.org works. The Space Plane Corporation is a not for profit organization designing an open source single stage to orbit aircraft. Below is a link to the proof of concept on a computer simulation of the aerodynamic ascent.

https://fb.watch/wBbj8U97V6/

What this means:

We can now ride up into space in a comfortable aircraft that takes off from a runway horizontally instead of being thrust upward in a missile. This makes space travel a lot safer and more comfortable. The normal Joe can be an astronaut now. It will also make space travel cheaper than a ride on SpaceX’s Starship.

Elon Musk’s Starship has a useful payload of 150 metric tons in re-usable mode. Our space-plane can do between 12-28 metric tons however the spaceplane is single stage to orbit and is also fully reusable. Single Stage to orbit means there are no other seperate vehicles or boosters, it’s just the one piece (the aircraft) that flies up into orbit. This makes it potentially a lot cheaper to run. Not to mention it can take off from any runway long enough. No rocket pads needed or a mechanical chopstick to catch it in mid air. It just lands like a normal plane back on the runway on it’s way down.

A scaled up model might be able to compete with the heavier useful payload of StarshipX in the future.

This illustration captures the idea of having an artificially generated magnetic field such as that envisioned to shield Mars from solar wind but instead to shield and capture the momentum from a nuclear blast from a fusion pallet with propellant encased.

This type of hypothetical ship that is rounded will also allow redundant centrifuge to sustain 1g for the crew during stationary periods. Or if it turns out that linear acceleration is too unstable to be used as artificial gravity.

Earth also absorbs momentum from the solar wind but it is massive in comparison to the solar particles that hit it’s magnetic field, in the above illustration the mass of the space craft relative to the “solar wind” from the nuke propellant are at more equal levels for the space craft magnetic field to absorb the nuclear momentum and transfer it to the ship.

After some brief interactions with volumetric & Holographic experts, there appears to be a scale limit at present with how large we can do a floating STL  model.

My idea is to have a near vacuum chamber filled with helium if required to minimize glass chamber weight and increase speed of sound to allow high frame rate 30FPS 3D images to exist. In this scenario we require a cross shaped rotating 2 panel system 36m diameter to spin up  to about 300 RPM.

For the simulation of lighter than air structures/buildings and airships especially on other planets, a responsive 3D display technology will be minimal to make investors feel secure that every engineering variable is visualized and crutinized in real time simulations factoring Earthquakes, wind and turbulance.

My idea of a space shuttle sized imager is still years away, in the mean time:

This year PhotonBytes will acquire the:

The Voxon VX1 – now available for purchase

For the pupose of RungeKutta Real Time Simuation:

from Voxon Photonics.

 

https://www.facebook.com/share/p/vkuhys2U5K4PzASK/

 

 

 

HAPs for Mars Simulation and Exploration
https://newmars.com/forums/viewtopic.php?id=10762

Small balloons for low mass payloads are useless, scale them up to 200m radius however then things get interesting! Here we see that the performance of 200m radius balloons can lift up to 100 tons of payload up to the peak of Olympus Mons due to the relationship between radius and volume of a sphere and lower Martian Gravity.

Double the radius and you increase the volume by a factor of 8. So this picture of a saucer shaped Airship in Mars’ atmosphere almost hugging the ground in a crater, is not actually the best we can do! It can go all the way to the top of mountains because of it’s sheer size. The Hindenburg on Earth will do just as well in Mars! Well, the max altitude will be roughly the same but climb rate will be slower in Mars’ atmosphere.

We can do this:

Not limited to this:
For background on this topic visit:
https://lnkd.in/gW9NUjQq