Abstract: Comet-Assisted Dual-Purpose Terraforming and Regional Habitat Formation on Mars

Mars remain major obstacles to long-term human settlement. This paper investigates a conceptual planetary engineering approach in which a volatile-rich comet is deliberately redirected to impact Mars in order to restore atmospheric pressure and create localized habitable environments.

Comets are proposed in preference to asteroids for two reasons. First, their highly elliptical orbits permit relatively small perturbations applied near aphelion to produce large changes in trajectory and substantial impact velocities. Second, their abundant ice content provides an intrinsic source of reaction mass, allowing nuclear-driven vaporization to generate thrust without requiring propellant to be transported from Earth.

Although the comet itself contributes additional volatiles, the principal objective is to liberate substantially larger volatile reservoirs already present on Mars.Upon impact, the comet would deliver planetary-scale energies measured in tens of teratons of TNT equivalent. The conversion of kinetic energy into heat and mechanical work could contribute to the release of water and carbon dioxide trapped within the Martian polar caps and subsurface reservoirs, increasing atmospheric density and initiating long-term climatic modification.

Particular emphasis is placed upon the release of carbon dioxide from the southern polar deposits, which may contribute more effectively to atmospheric pressure restoration than water alone.Selection of the impact site constitutes a critical aspect of the concept. Candidate locations would be chosen to maximize the liberation of volatile materials from both polar regions, especially the carbon dioxide-rich southern polar deposits, as well as from subsurface reservoirs not yet fully characterized.

Additional consideration may be given to regions exhibiting evidence of residual volcanic or geothermal activity, with the aim of stimulating the release of carbon dioxide and other greenhouse gases from magma chambers, volcanic cavities, or partially active mantle sources. The impact location may therefore be optimized to exploit multiple atmospheric reservoirs simultaneously, including polar deposits, buried volatile-rich layers, and remnant volcanic systems that may still retain trapped greenhouse gases.

The impact angle represents an additional design parameter. Rather than merely maximizing energy deposition, the objective is to produce a crater geometry favorable to atmospheric retention. By taking advantage of the approximately 11-kilometer scale height of the Martian atmosphere, a sufficiently deep basin could potentially sustain significantly higher pressures near its floor than on the surrounding plains. Such a regional habitat could provide a favorable environment for future settlement and serve as a contingency strategy should global atmospheric restoration prove insufficient.

The proposed approach therefore incorporates a dual-purpose terraforming philosophy in which planetary-scale atmospheric enhancement constitutes the primary objective, while the creation of a naturally pressurized regional basin provides a secondary and potentially more achievable pathway toward sustained human habitation.Numerical simulations of crater formation and resulting topography would constitute an important component of the investigation.

Software such as the iSALE impact simulation code may be employed to model crater depth, geometry, ejecta distribution, and the atmospheric characteristics achievable within the resulting basin. These studies would aid in determining the optimal impact angle and location required to maximize both global atmospheric enhancement and local habitability.

This paper will discuss the orbital mechanics of comet redirection, propulsion utilizing indigenous cometary volatiles, impact energetics, strategic impact-site selection, stimulation of residual volcanic activity, crater geometry optimization, atmospheric effects, numerical crater simulations, and the engineering challenges associated with directed cometary impacts as a pathway toward the future habitation of Mars.

Sub-Orbital Fighter Jet

The ArcJet would have looked and performed similarly to the SR-72 and in fact shares simiar engine design. In Top Gun the Dark Star was a fictional version of the SR-72 and reached mach 10 before burning up at mach 10.2. However the Arcj Jet can reach those speeeds and even exceed it all the way to mach 20. Not enough to enter orbit but enough to fly to the opposite side of the Earth. The SpacePlane Corporation’s space-plane can enter orbit but that’s another design that runs on hydrogen and is 250 tons instead of 100 tons which is the mass of this sub-orbital “ArcJet”.

A: Sub-Orbital flight is a tech gap that is yet to be filled between orbital and regular flight in the atmosphere. A capability that is screaming to be  filled.

Originally intended as a private jet it could also be used for millitary for drones and/or piloted Jets to strike targets with precision. Like a non-nuclear MIRV from ballistic ICBMs.

The Arcjet was a suborbital space-plane that I felt had millitary applications but the visionary intended for civilian use as a private jet. If the airforce was just to consider adding a jet fuel powered rocket into their existing jets they could have similar performance and be able to fly over countries to strike targets. Such as Israel striking targets in Iran by flying over Arab countries(Iraq and Saudi Arabia) in the way.

====================
The specs are as follows:
18 ton dry weight
100 ton MTOW
2 ton reserved for payload.
=====================
So its dry weight to MTOW ratio is 0.18 which is pushing it slightly. It’s the dry weight, size and wingspan of an F14 and the weight of a fully fueled space shuttle orbiter(100tons).
It uses a siminar engine system like the SR-72, successor to the SR-71. However the Arc Jet also has a jetfuel rocket which the SR-72 does not have.

Much like the SR-72 the Arcjet also would have an air intake splitter to reroute airflow from jet to ramjet. Unlike the SpacePlane (space-plane.org) from The SpacePlane Corporation it uses regular jet fuel and has a seperate rocket instead of a totally combined cycle engine system.

 

 

Integrating decelerating Halley’s comet

Euler’s method reveals how many modiefied 100MT Tzar bombs we need to signficantly altering Halley’s comet by bringining it to a complete stop. If we did it did crash into the sun, we could even cause it to hit Mercurcy or Venus should we be so inclined. Mars on the other hand requires a comet with a different orbit than Halley’s such as the one that almost hit it recently.

Crater.xls

15 days to Mars

 

UPDATE:

Proabably need 4 total starships, with 3 as tankers to get 13km/s for a 15 day transit to Mars. 2 Total Starship only gets us to 10km/s which is 3km/s shy of what’s needed. Original 2 ship idea could probably get us closer to 28 days.

Numbers: https://docs.google.com/spreadsheets/d/1U_pj_0jc53wAgq37A0oYvuiZnMFLptZ3B4N1quCniVo/edit?usp=sharing

Ref: https://www.exploremars.org/wp-content/uploads/2021/09/0914_03-15_Bret-Drake_Trajectory.pdf

According to AI: 15 days to Mars using “conjunction class” orbital transfer with 2 Starships working together. One will be an uncrewed expendible fuel tank with it’s useful payload as additional fuel. The tanker flies in parallel with crewed ship at a safe distance or attached to it.

This allows 15 days transfer to Mars from Earth’s LEO and does not require risky aerobraking on the Martian side as there is sufficient fuel to de-celerate.

Still need to confirm underlying working using rocket equation. This is assuming there is another Starship there on Mars already sent uncrewed or as a robotic mission (with Tesla bots and AI) and fueled up using local resources on Mars. This is for the return trip.

New Mars Forum Thread on this topic:

https://newmars.com/forums/viewtopic.php?id=11019

55km Mars tunnel idea 2.0

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:

 

500km Oribital Insertion – The Space Plane Corporation

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

Lunar Atmosphere – Internal

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!