The Blue Agricultural Revolution?

 

Chinese Moon Ship Returns to Earth with Samples from the Lunar Surface

Links and References

China’s Lunar Sample Return Capsule Successfully Recovered

Chinese sample return capsule lands on Earth after round-trip flight to moon

China’s Chang’e-5 Probe Drops Off Moon Samples at the Climax of a Historic Mission

 

 

 

Artemis National Team's HLS Integrated Lander Vehicle

 

Terrestrial Energy's IMSR Hybrid Nuclear Reactor System

 

 

Links and References

Terrestrial Energy

Small Nuclear Reactors

These are the asteroids to worry about!

 

Growing Tensions Amongst Russia, China, and Japan over Vladivostok and the Kuril Islands

 

Vladivostok & Kuril Islands

China Launches its Lunar Mission to the Ocean of Storms

 

 

 

 China's Change-5 probe blasts off from the Moon

 Chinese probe completes sample collection work on the lunar surface

 Change 5 lands on the Moon

China lands sample return probe on the Moon

Change 5 Lands on Moon to Collect Fresh Samples

The Lands that Will Flood in our Lifetime

 

Why Are Nuclear Power Plants So Expensive?

 

Nuclear power plants are expensive for the same reason that  rockets are expensive. They're mostly handcrafted structures. And relatively very few are built. Plus their principal components are usually not serially mass produced.  

Currently, there are only 54 commercial nuclear reactors under construction world wide. Only two are under construction within the US. Eleven are under construction in China, seven in India, and Russia, South Korea, and the United Arab Emirates each have four under construction.

However, the US  is scheduled to build nine new-- nuclear submarines.

The advent of small nuclear reactors that are being developed within the US and around the world should resolve the high capital cost problem of building nuclear reactors-- especially if  most of the electricity produced from nuclear facilities is used to produce carbon neutral synthetic fuels through the electrolysis of water to produce hydrogen and the extraction of CO2 from the atmosphere to produce CO2.

Nuclear power produces about 20% of the electricity in the US and more than 50% of the carbon neutral electricity in the US. But existing nuclear sites in the US could easily produce at least 80% of the electricity if small reactors were gradually added to existing sites.

However, I believe that small remotely sited-- floating nuclear reactors-- used to produce renewable methanol (eMethanol) will finally end the world's dependence on fossil fuels. Methanol can be used to replace natural gas in natural gas electric power plants cheaply retrofitted to use methanol. Methanol can also be used in fuel cell automobiles and power plants. Methanol can also be converted into carbon neutral jet fuel and gasoline and dimethyl ether (a diesel fuel substitute). And methanol can power ships.


The seawater in the world's oceans contain about 4 billion tonnes of uranium which could be extracted and used to power human civilization on Earth pretty much as long as the Earth still has oceans.  The source of this uranium is the ocean's natural interaction with the Earth's continental crust which contains more than 100 trillion tonnes of uranium.

There are currently more than 160 floating vessels powered by more than 200 nuclear reactors on the high seas. And such nuclear vessels have existed since the 1950s.

Marcel  

Why are nuclear plants so expensive? Safety's only part of the story. 

Methanol as a Motor Fuel

Dragon Crew Enters the ISS

Alien Worlds

Starts December 2 on Netflix

Commercial Advantages of a Reusable SLS Deployed Lunar Cargo Lander

Notional RLV-4 Cargo vehicle in a distant  Near Rectilinear Halo Orbit awaiting depot refueling before transporting a multilevel Lunar Regolith Habitat to an outpost at one of the lunar poles. 

 

 by Marcel F. Williams

Privately financing the development of a reusable SLS deployed lunar landing vehicle should be a priority for the major  Space Launch System partners: Boeing, Lockheed Martin, Aerojet Rocketdyne, and Northrup Grumman. A reusable single stage  LOX/LH2 fueled vehicle (RLV-4 Crew) could be commercially successful as a crew lander by simply adding a-- pressurized habitat module-- already being developed by Lockheed Martin for the Blue Origin National Team. 

Notional RLV-4 Crew vehicle with Lockheed Martin derived habitat module with crew deployment davit system.

 

By financing a single stage vehicle rather than a two stage vehicle, development cost could be substantially reduced by simply developing one vehicle instead of two. Further cost reductions could result from using engines and propellant tank technology that already exist. So a notional RLV-4 could use  RL-10 derived CECE engines already developed by SLS partner Aerojet Rocketdyne  and super lightweight composite propellant tanks already developed by Boeing. 

I envision the RLV-4 Crew and RLV-4 Cargo vehicles going into operation by the year 2026. If we assume a development cost of $6 billion for the RLV-4 over the course of six years, then each SLS partner would be required to supply at least $250 million a year of funding for the development of the reusable RLV-4.

Notional RLV-4 Cargo vehicle capable of being filled with up to 56 tonnes of LOX/LH2 propellant.

 

Similar to the RLV-4 Crew vehicle, I envision the RLV-4 Cargo as being launched-- in pairs-- within the 9.1 meter in diameter dynamic envelope of a 10 meter in diameter SLS payload fairing.  At its corners, the maximum diameter of the RLV-4 octagon  would be 8.44 meters with a distance between each opposite 3.23 meter side of the octagon being approximately 7.8 meters. With the legs folded during launch, the RLV-4 could easily fit within the internal  9.1 meter in diameter dynamic envelope of the 10 meter in diameter SLS  payload fairing.  

Each RLV-4 Cargo vehicle would weigh approximately 8 tonnes. The 10 meter in diameter payload fairing would add an additional 10 tonnes in weight headed for orbit.  Since an SLS Block I would be capable of deploying up to 70 tonnes to LEO, up to 44 tonnes of propellant could be added to one of the vehicles in preparation for a mission. 

Alternatively, one RLV-4 Crew vehicle could be launched with one RLV- 4 Cargo vehicle. Before launch, the crew vehicle would be filled with enough propellant to transport a crew to NRHO. The cargo vehicle would simply remain in orbit at LEO until its ready to dock with a payload and be fueled for a mission.

The reusable  RLV-4 Cargo vehicle would be able to dock securely with large payloads (up to 10 meters in diameter) subsequently deployed to LEO by the SLS. Payloads deployed to orbit by the SLS would be equipped with flat standardized docking bases configured to securely join with the octagonal payload floor of the RLV-4. Propellant depots deployed to LEO, NRHO (Near Rectilinear Halo Orbit) and eventually on the lunar surface would be used to fuel and refuel the RLV-4 Cargo vehicles.

Octagon shaped payload floor of notional RLV-4 Cargo vehicle.

 

Fueled at LEO with up to 56 tonnes of propellant, the RLV-4 could deploy up to 10 tonnes of cargo to the lunar surface. Alternatively,  the RLV-4 could transport up to 30 tonnes of cargo to NRHO where it could then be refueled to transport its 30 tonne payload to the lunar surface.

If the SLS deployed payload has an upper attachment area that could allow an additional RLV-4 to dock then two RLV-4 Cargo vehicles could be utilized for a single cargo mission.  This could allow up to 60 tonnes of payload to be transported to NRHO. A single fully fueled RLV-4 Cargo vehicle could deploy up to 50 tonnes of payload to the lunar surface. But two vehicles would be required to deliver a 60 tonne payload to the surface. One vehicle would only travel to lunar orbit and then back to NRHO while the second vehicle would travel to the lunar surface with its 60 tonnes of payload. 

So the reusable RLV-4 cargo system would be capable of delivering 10 tonnes to 60 tonnes of payload from the lunar surface from LEO. And that means the SLS   could deploy up to 60 tonnes of payload to the lunar surface with a single launch if it used a reusable RLV-4 Cargo transport system. 

Notional RLV-4 Cargo deployed lunar crane for unloading large cargo and for lunar regolith deposition. 

Large lunar cranes might be one of the most valuable initial payloads for the RLV-4 Cargo. Using a davit system, a pair of large cranes could be deployed to the lunar surface.  Such electric or hybrid electric (pressurized hydrogen fuel cell/battery) vehicles could be used to unload large and heavy payloads from a large variety of lunar landing craft. If we assume that each lunar crane weighs at least 8 tonnes, lunar regolith could be used to provide an additional 24 tonnes of counter weight. So each lunar crane should be capable of offloading more than 30 tonnes of payload. However, if the iron and other metals that inherently exist within lunar regolith are magnetically extracted to increase the counterweight capabilities of lunar regolith then payloads weighing more than 60 tonnes could be unloaded. Lunar cranes could also be used to deposit regolith within the surrounding walls of large habitats and within the foundation floor for inflatable biospheres and surrounding bio-tori.

RLV-4 Cargo vehicle carrying twin lunar regolith cranes to be deployed to the lunar surface using davit system.

 

Pressurized 8.4 meter in diameter cylinders derived from SLS propellant tank technology could provide multilevel habitats for the lunar surface up to  20 meters tall if deployed within an SLS 10 meter in diameter payload fairing. With a self deploying regolith walls, lunar cranes could provide appropriate radiation shielding by simply dumping lunar regolith within the cavity of the surrounding wall. 

Lunar regolith crane about to remove a Lunar Regolith Habitat from a RLV-4 Cargo vehicle.

But even longer 8.4 meter in diameter cylinders could be deployed to the lunar surface after being to deployed to LEO by the SLS. 40 meter habitats could be deployed to the lunar surface using the RLV-4 Cargo. Such habitats could be unloaded by large  lunar cranes and deployed horizontally to the lunar surface and then covered with lunar regolith bags. The use of the larger horizontal  habitats for agriculture could even allow for the growing of orchard trees for the production of apples, oranges, peaches, lemons, etc. The horizontal habitats could also be used for aquaculture, raising shrimp, crabs, fish, clams, etc. 

X-Ray of an SLS propellant tank technology derived Lunar Regolith Habitat

If the RLV-4 Cargo is used to deploy inflatable Kevlar biosphere and bio-tori then substantially larger habitats could be deployed. 50 meter in diameter  Kevlar biospheres that are pressurized with half the atmospheric pressure on Earth could easily be deployed to the lunar surface by an RLV-4 Cargo.  An additional SLS launch would be required to launch the surrounding  25 meter wide  bio-torus. And another SLS launch would be required to deploy the expandable connecting tunnel and regolith base for the biosphere and bio-torus on top. 

 A 15 meter high  SLS deployed lunar regolith hab might provide five spacious 8.4 meter in diameter habitat floor levels (55 square meters per floor). 

But the bottom half of a 50 meter in diameter biosphere could provide up to 9 habitat levels with each floor averaging about 25 meters in diameter (490 square meters per floor). That would be up to 16 times the floor area for just the bottom half of the biosphere. The upper half of the biosphere (the biodome) would provide the astronauts, military personal, and guest with spacious recreational area with a ceiling up to 25 meters high. Such an area could easily accommodate a large circular recreational swimming pool 30 meters in diameter. This might also be room enough to strap on a pair of wings and fly about within the 50 meter wide biodome.  The surrounding bio-torus or tori could be used for agriculture and aquaculture and storage.

Notional lunar biosphere and bio-torus covered with regolith bags and connected to twin Lunar Regolith Habitats on the sintered surface of a lunar outpost area.

 Once propellant is being produced on the lunar surface, extraterrestrial vehicles like the RLV-4 crew should make it substantially cheaper to travel to the lunar surface after departing the Earth's surface aboard a commercial crew vehicle. If a lunar habitat was deployed to the lunar surface and utilized as a hotel for astronauts, tourist, and military personal, the owners could reasonably charge its guest perhaps $10 million each for a 30 day stay. This, of course, doesn't include the cost of the round trip from Earth to the Moon. If we assumed that an individual habitat was continuously occupied by at least 4 to 8 personal (astronauts, military personal, tourist) then an individual habitat could make between  $480 million to $960 million per year in revenue. With up to 16 times the floor area for the bottom half of a biosphere, a single biosphere/bio-tori complex could make more than $15 billion a year in revenue if it were continuously fully occupied with up to 128 people.   Providing water, food, and air for the lunar guest would be insignificant if such resources are derived from ice and carbonaceous and nitrogenous resources in the lunar regolith at the poles or from similar resources deep within lava tubes. Assuming a minimum 20 year lifetime for such habitats, such SLS deployed facilities should be highly profitable.

Links and References

Commercial Advantages of a Large SLS Deployed Reusable Extraterrestrial Crew Landing Vehicle

Inflatable Biospheres and Bio-Tori for Large Outpost and Colonies on the Lunar Surface

NASA selects proposals to demonstrate in-space refueling and propellant depot tech

Delta V calculator

Puerto Ricans Vote to Become the 51st US State

Last Tuesday, 52% of Puerto Ricans voted in favor of statehood.  The  US island territory of more than three million people that has been under US control since 1898. 

 

Puerto Rico votes in favor of statehood. But what does it mean for the island?

The Future of Renewable Methanol Conference

 

 Links and References:

Methanol Fuel Cells: Powering the Future Conference

The Production and Utilization of Renewable Methanol in a Nuclear Economy

Utilizing Renewable Methanol to Power Electric Commuter Aircraft

Producing Renewable Jet Fuels from Carbon Neutral Methanol

Siting Ocean Nuclear Power Plants in Remote US Territorial Waters for the Carbon Neutral Production of Synfuels and Industrial Chemicals

 

Methanol Fuel Cells: Powering the Future Conference

 

Methanol Institute

Commercial Advantages of a Large SLS Deployed Reusable Extraterrestrial Crew Landing Vehicle

Notional SLS deployed RLV-4 Crew lunar landing vehicle with a crew davit deployment system. 

by Marcel F. Williams

 

Before the end of the decade, the deployment of orbital propellant depots to LEO and NRHO (Near Rectilinear Halo Orbit) will probably make the SLS/Orion vehicle-- obsolete-- as part of an affordable and efficient crew transport  architecture to the lunar surface. So the-- crewed-- SLS/Orion configuration could be haulted just a few years after it started.  

 

However, the four major partners in SLS manufacturing and operations (Boeing, Northrup Grumman, Aerojet Rocketdyne, and Lockheed Martin) could take full economic advantage of the coming  propellant depot architecture by using the Space Launch System to deploy large-- reusable-- lunar landing vehicles into orbit to transport crews or heavy cargo to the lunar surface. 

 

I'll  call such a notional extraterrestrial landing vehicle, in this article, the RLV-4 (Reusable Landing Vehicle Four). And I seriously believe that if Boeing and their SLS partners finance and build a  RLV-4 type of vehicle for both crew and heavy cargo transport to the lunar surface, their partnership could easily end up economically dominating cis-lunar space and probably the rest of the solar system for the next 25 to 30 years-- with such a  simple single stage extraterrestrial vehicle and its inherently useful variants.

LOX/LH2 tank configuration in Boeing's Altair lunar lander concept (Credit: Boeing)

The notional  RLV-4 would be octagon shaped like Boeing's Altair lunar descent vehicle concept. But it will use a simplified propellant tank architecture requiring just two LH2 tanks and two LOX tanks, similar to Blue Origin's octagon shaped Blue Moon lunar lander which is basically a smaller-- simplified-- version of of the Altair lunar lander. 

Top view of LOX/LH2 tank configuration for Boeing's Altair lunar lander concept (Credit: Boeing)

 

The propellant tanks for the RLV-4 will be derived from Boeing's super light weight composite cryotank technology with the two large 3.8 meter in diameter hydrogen tanks and and the two smaller liquid oxygen tanks approximately 2.4 meters in diameter. Both cryotanks will stand nearly 6 meters high within the interior of the RLV-4 octagon. Gaseous compressed hydrogen will be used to pressurize the liquid hydrogen tanks and compressed gaseous oxygen for pressurizing the liquid oxygen tanks during liftoff and trajectory burns-- replacing gaseous helium. Gaseous hydrogen and oxygen will also be utilized for the vehicle attitude thrusters in this notional vehicle design. So hydrogen and oxygen will provide the propellant, attitude control, and tank pressurization for the RLV-4. 

Notional Boeing 3.8 meter in diameter composite LH2 tank and 2.4 meter in diameter LOX tank.

The RLV-4 would be somewhat similar in height with Boeing's Altair concept. But it would be able to store more than twice as much propellant (56 tonnes) thanks to the substantially larger  cryotank diameter of the liquid hydrogen tank and the larger diameter and height of the liquid oxygen tanks relative to those conceived for the Altair. So the RLV-4 would be capable of accommodating up to 56 tonnes of propellant which would be more than enough fuel to land a 16 tonne crew vehicle from LEO to the surface of the Moon.

The restartable engines for the RLV-4 could be provided by SLS partner, Aerojet Rocketdyne, who is currently developing the expendable RS-25 engines for the  SLS core vehicle and the RL-10 engines for the upper stage vehicle. The RL-10 derived CECE engines would be capable of throttling between 104% down to just 5.9% and would be capable of at least 50 in space starts. So the CECE engines should be capable of performing at least 12 round trip missions between NRHO and the lunar surface before having to be replaced. Using them in pairs would give the RLV-4 engine-out capability, enhancing crew safety.

However, the RLV-4 propellant tanks should be capable of at least 50 refills (50 round trips if  missions between NRHO and the lunar surface are conducted on a single fueling of propellant). So if two more engines were added to the RLV-4, 24 round trips could be possible if only two engines were used during a journey-- while propellant flow was shut off to the other pair of engines. Replacing the engines after 24 round trips with four more CECE engines could maximize the RLV-4's reusability allowing the vehicle to conduct up to 48 round trips to the lunar surface before-- if it is refueled less than 50 times. 

Basic RLV-4 cargo lunar lander with solar panels on four sides of the octagon shaped vehicle and radiators on four sides of the vehicle

At its corners, the maximum diameter of the RLV-4 octagon  would be 8.44 meters with a distance between each opposite 3.23 meter side of the octagon being approximately 7.8 meters. With the legs folded during launch aboard an SLS vehicle within a 10 meter fairing, the RLV-4 could easily fit within the internal  9.1 meter dynamic envelope of the payload fairing. 

 

Notional RLV-4 LOX/LH2 cyotank configuration within the octagon shaped vehicle

While NASA currently envisions only an 8.4 meter fairing for it's use of  the SLS, it would be in the economic interest for the  SLS partnership to quickly develop its originally intended 10 meter fairing in order to have a clear competitive advantage over vehicles like the Space X's future Starship which will have a 9 meter payload bay with probably an 8.1 meter dynamic envelope. However, Blue Origin's 7 meter in diameter New Glenn launch vehicle could be competitive since it should  also be capable of accommodating payload fairings up to 10 meters in diameter. With an 8.4 meter diameter for the SLS core vehicle, the SLS should be capable of accommodating  payload fairing sizes up to 12 meters in diameter with internal dynamic envelopes up to 11.1 meters in diameter.

SLS partner, Lockheed Martin, could supply basically the same Orion derived crew habitat module for the RLV-4 as it will for the Artemis National Team (Blue Origin, Lockheed Martin, Northrup Grumman, Draper) that will deploy a lunar crew lander to the Moon for NASA-- but without the added complexity and the expense of the ascent propellant architecture. 

A tall 10 meter in diameter SLS fairing should  be able to easily deploy two RLV-4 crew vehicles and other variants into orbit per launch-- cutting  RLV-4 deployment cost in half per launch. And the SLS should be able to deploy each vehicle to orbit with enough propellant for each vehicle to self deploy practically anywhere within cis-lunar space.

Utilizing propellant depots deployed at LEO, the RLV-4 should be able to transport crews from LEO to NRHO with less than 24 tonnes of propellant. 

But round trips between NRHO and the lunar surface could require nearly 48 tonnes of LOX/LH2.

Supplying a propellant depot at LEO with enough propellant for a RLV-4 crew mission to NRHO would only require a single Vulcan-Centaur launch (Vulcan-Centaur 562). 

However, supplying water or propellant to depots located at NRHO for a single lunar mission would require eight Vulcan-Centaur launches for the round trip between NRHO and the lunar surface plus an additional  four Vulcan-Centaur launches to NRHO to fuel the return trip of the RLV-4 back to LEO from NRHO. 

So a single lunar mission would require at least 13 Vulcan-Centaur propellant launches costing more than a billion dollars in propellant cost alone for a single mission. But such cost  would still be competitive with architectures that require at least one SLS/Orion launch plus additional commercial launches for a lunar crew missions. 

However, propellant cost for the RLV-4 architecture would fall dramatically once hydrogen and oxygen were being produced on the lunar surface. And that would mean that only a single Vulcan-Centaur propellant launch to LEO would be required for a lunar mission. 

Propellant destined for depots located at NRHO could come from the lunar surface. And a RLV-4 tanker variant could supply nearly 50 tonnes of water or propellant to an NRHO depot per launch from the surface of the Moon, up to 1200 tonnes of water or propellant until its four engines would have to be replaced, and up to 2400 tonnes of water or propellant to NRHO before the entire vehicle would have to be replaced. So two RLV-4 tanker vehicles deployed-- by a single SLS launch-- might be able to deploy 2400 to 4800 tonnes of lunar propellant to NRHO.

Simple solar  powered RLV-4 variants could serve as orbital propellant depots at LEO and NRHO and on the lunar surface.  Each depot could store up to 56 tonnes of propellant plus up to 100 tonnes of water for possibly making propellant.  The appropriate solar arrays for lunar and orbital RLV-4 derived propellant depots could be developed by SLS partner Northrup Grumman which already specializes in developing and deploying extraterrestrial solar arrays. 

By sharing the cost for the development and deployment of the RLV-4, starting in 2021, Space Launch System partners: Boeing, Aerojet Rocketdyne, Lockheed Martin, and Northrup Grumman could have the RLV-4 lunar lander and its variants ready to be deployed within a 10 meter in diameter SLS payload fairing by the year 2027.

By 2030, future RLV-4 passengers (astronauts and tourist) would simply have to take a Vulcan-Centaur-Dream Chaser or another commercial crew configuration to a commercial orbital habitat at LEO-- such as a commercial SLS derived Dry/Wet Shop mega habitat.  At the orbiting habitat,  passengers would transfer to an RLV-4 that has already docked at the habitat and already refueled at a nearby RLV-4 derived propellant depot or another commercial depot. 

It would take the RLV-4 about four days to transport up to 8 people to another private microgravity  habitat located at NRHO which would serve as a gateway to the lunar surface. There, passengers would transfer to another RLV-4 vehicle that was fueled on the lunar surface at a lunar outpost with enough propellant to transport them to the surface of the Moon in just 12 hours time. Or the RLV-4 that they arrived in could be refueled to transport them to the lunar surface. 

The RLV-4 Crew vehicles located at NRHO  could also utilize the cheap lunar propellant exported to NRHO depots for bi-weekly crewed missions to other areas on the lunar surface-- lasting 6 days-- before returning the the NRHO Gateway.  But if two RLV-4 vehicles are available at an NRHO Gateway, then weekly missions practically anywhere on the lunar surface could be conducted by a group of astronauts on a weekly basis.

Once passengers have completed their stay on the lunar surface, lunar propellant could be used to transport them on a four day trip from the Moon all the way back to LEO where they could take a Dream Chaser back to Earth, landing at any accommodating airport or spaceport in America.  

But as advantageous the RLV-4 would be as a commercial extraterrestrial crew lander, it would be even more economically viable as a lunar cargo vehicle for transporting exceptionally large and heavy SLS LEO launched payloads to the lunar surface. The RLV-4 as a heavy cargo vehicle will be discussed in my next article on the Reusable Landing Vehicle IV. 
 
Links and References

 Lunar Lander Vehicle Design Overview

Concept for a Crewed Lunar Lander Operating from the Lunar Orbiting Platform-Gateway

System Architecture Design and Development for a Reusable Lunar Lander

Boeing's Composite Tank Could Greatly Improve Launch Vehicles

CECE: Expanding the Envelope of Deep Throttling Technology in Liquid Oxygen/Liquid Hydrogen Rocket Engines for NASA Exploration Missions

 Blue Origin's National Team Lunar Lander

Vulcan-Centaur

Deploying a Ginormous SLS Derived Dry/Wet Workshop Habitat with a Single SLS Launch

Delta V Calculator