recursal/Fanatic-Fandom huggingface dataset:
RL-10A-4

The **RL-10A-4** is an American rocket engine.

Vacuum thrust was upgraded from to 20800 Ib (a derating of its 22,000 Ib design point) with changes to the thrust chamber, upgrading of the turbomachinery. The thrust chamber geometry in the RL-10A-3-3A with the addition of a silver insert at the throat were incorporated into the basic shape of the chamber. The liquid oxygen pump was completely redesigned, other revisions to the turbomachinery. Increase in propellant flow and chamber pressure. Other engine components were redesigned for compatibility with the increased operating pressures. A columbium nozzle extension is fitted (either extensible or fixed).

First production models delivered in June 1991.
RO Designation Scheme

The RO-XX is a rocket engine designation scheme adopted around the year 1990 by the US, Russia, and European countries to name their new rocket engines.

It is named after Dr. Raymond Owens.

Engines are only given an RO designation when they reach production.

## Scheme:

* RO-1`X` - Kerosene-based fuel
* RO-2`X` - Light hydrocarbon fuel (basically just methane, but also applicable to other hydrocarbons lighter than kerosene)
* RO-3`X` - Hydrogen fuel
* RO-4`X` - Hypergolic fuel
* RO-5`X` - Solid-core NTR
* RO-6`X` - Gas or liquid-core NTR
* RO-7`X` - Electric propulsion
* RO-8`X` - Reserved
* RO-9`X` - Reserved
* Tripropellant engines use a mixed scheme
	+ Kerosene-Hydrogen triprop - RO-T13`X` (`RO-T131`, `RO-T132`, `RO-T133`, etc)
	+ Kerosene-something else triprop - RO-T1N`X` (`RO-T1N1`, `RO-T1N2`, `RO-T1N3`, etc)
	+ `T` stands for Tripropellant

Solid rocket motors are notably omitted from the scheme.
Othrys 10

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **Othrys 10** was the 3rd refuelling mission, flown by the MLV Saturn V-23-M1.

A failure of the 2nd stage resulted in an explosion and total loss of the vehicle and payload.
MLV Saturn V-24-L-TSCC

The **MLV Saturn V-24-L-TSCC** is an American rocket that launched once for Othrys program.

The entire payload, once in orbit, weighed 445t.

## Design:

The rocket consists of an MS-IC-337, with 4 MS-IC-LFB-337 boosters mated to it.

The 2nd stage (ordinarily the MS-II) was replaced by the TSCC, and on top of that it carried additional SOM-2, and SOM-3 stages - the same configuration as present on the SOM spacecraft.

The TSCC second stage was used for the majority of orbital insertion. This was done in order to reduce the number of launches required for the mission.

The SOM-2 and SOM-3 were both partially fuelled, otherwise the rocket would've been too heavy to make it into orbit.

At the time of liftoff, it was the heaviest rocket stack ever launched.
MS-IVB

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Engines

* 1x J-2S
* 2x Auxiliary Propulsion System

## Launch History

### First flight

1976 or 1975

The **MS-IVB** is a strenghtened version of the S-IVB rocket stage.

## Design:

No stretch was performed, both stages have identical dimensions.

The strenghtening was required to handle heavy payloads. This stage can hold up to around 200t of payload and fairing at 9 Gs of acceleration.
MLV Saturn V-24-L-NOM-RS

The **MLV Saturn V-24-L-NOM-RS** is an american launch vehicle.

## Design:

It is an MLV Saturn V-24-L with the Neptune Orbital Module Return Stage payload mounted on top.

It uses an adapter based on the NOM-STS adapter to connect the 12.2 m wide maneuvering stage to the 10.06 m wide Saturn.

It launched with 2 boosters.
MS-IC-240

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Engines

* 5x F-1A
OR
5x F-1A-CW

## Launch History

### First flight

1976 or 1975

The **MS-IC-240** is an American rocket stage.

## Design:

its a S-IC stage stretched 240 inches and strengthened to be able to mount side boosters and heavier upper stages.

This stage can handle either UA1205, UA1207 or MS-IC-LFB boosters.

### LOX Tank:

The LOX Tank was stretched 147 in (3.73 m).

### RP-1 Tank:

The RP-1 Tank was stretched 93 in (2.36 m).

## See Also:

S-IC

MS-IC-337

MS-IC-2
LT1

The **LT1** was a nuclear-powered train set operated on the Lunar surface.

It was the first model to successfully complete the trip from the International Lunar Surface Station to the Lunar Titanium Plant, which happened in the year 2076.

It was used to haul titanium, and other minerals.

## Design:

The set consisted of a locomotive containing the nuclear reactor on one end, cooling units in a car attached to it, 2 cabs (one at the locomotive, and one more on the opposite side). The train could haul several specially designed carriages and had a maximum permitted operating speed of around 30 mph.

The train was heavily automated, but required personnel to monitor its systems.
Apollo 19

The **Apollo 19** performed a manned flyby of Venus.

The mission lifted off of LC-39B on October 31, 1973, and flew by Venus on March 3, 1974, returning to Earth on December 1, 1974.

## Trivia:

The S-IVB stage was used as a "wet workshop", to increase astronauts' living space.

## See Also:

Apollo 18 - test of the hardware for the venus flyby.
Lunar Structural Production and Test Plant

The **Lunar Structural Production and Test Facility** was a large "industrial" complex located at the International Lunar Surface Station, at the Lunar south pole.

It was used to build rocket tankage, rocket structural parts, parts of the base itself, some tools and machinery, and more.

Quality and metallurgical testing was conducted at the site.
Apollo Program

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

Apollo was a spaceflight program ran by NASA from 1961 to 1973, culminating in the manned flyby of Venus.

## History:

The genesis of the Apollo program can be traced back to the year 1960. Initially envisioned as a three-person spacecraft that would follow the one-person Project Mercury, it was subsequently dedicated to the Kennedy's goal of landing a man on the moon, and ran in parallel with the two-person Project Gemini.

JFK would live to see his ambitious goal finally materialize when the Apollo 11 mission softly touched down in the lunar Sea of Tranquility on July 20, 1969.
Kennedy Space Center/LC-69

Three super-heavy launchpads LC-69A, LC-69B, and LC-69C as well as a 200m tall high-bay with a crawlerway connecting it to the pads.

## Construction:

Launch Complex 69's construction started in 1994, and ended in 2004.

In 1993, following the last launch of Coelus Program, a test vehicle MLV Saturn V-24-L SA-701 exploded while lifting off from Launch Complex 39B, completely levelling it to the ground. Launchpad Complex 39A also received minor damage as a result of the blast that was estimated at 2-5kt of TNT. The cause was ultimately tracked down to faulty ground support equipment.

This opened the eyes of officials at NASA - a bigger launch complex was needed to handle the increasingly more massive launch vehicles. The LC-69 was born.

Pads were completed in:

* LC-69A - 1998
* LC-69B - 1999
* LC-69C - 2004

High-bay construction started in 1995 and ended in 1998.

## Design:

   The LC-69 complex is located about 5-10km north of the LC-39B.

All 3 of the pads are built very close to the coast, similarly to the LC-39, with the 200m high-bay about 2 kilometers south-east of the LC-69A.

The pads are also connected to the Vehicle Assembly Complex via a series of crawlerways.

High-bay is placed at a 45 degree angle with respect to the LC-69A (with walls roughly facing the cardinal directions), to protect it better in case of an explosion on the pad.
LR87-AJ-3

The **LR87-AJ-3** was an American rocket engine developed and built by Aerojet.

This version featured changes to reduce parts count, reduce weight and to eliminate LR87-AJ-1's design problems. Another improvement was the incorporation of dry-jacket engine starting, which eliminated the need to pre-fill the cooling channels in the nozzle.
RD-270

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Throttle

95 - 100%

The **RD-270** is a Soviet hypergolic staged combustion rocket engine. Designed and produced by Glushko's NPO Energomash.

The engine was completed and in production by early 1972.

## Development:

The early prototype engines aimed for a chamber pressure of 26.1 MPa, but for production models it was reduced to 20.6 MPa, to increase reliability and extend the life of the engine.

## Design:

The RD-270 is a full-flow staged combustion rocket engine. It has a gimbal range of 8 degrees.

## Trivia:

The real engine's stats were:

* Isp: 301 / 322 s
* Thrust: 6.27 / 6.71 MN

## See Also:

RD-270K

F-1

RO-11
Asteroid Outpost

The **Asteroid Outpost** is an international propellant extraction and processing plant located on an asteroid rich in water and methane ices, and rare-earth metals.

We would fly mining and refinery equipment to the target asteroid, set it up there, and let it mine.

It would be highly autonomous.

It would need several launches at least.

It’d use extremely large durable solar arrays for power.

The storage facilities for processed LOX will be separated from the storage for processed LH2 and CH4.

The metal mining facility will be separate from the two.

We would also need a flat and solid landing pad for the transport spacecraft.

We would also fly large storage tanks with 0-boiloff technology to the site for storage. Tanks and mining facilities could be expanded as the demand grows.

I estimate that the actual mining rig can be developed and built by 2040, launched into orbit using a Cronus 3 launch vehicle, rendezvous with multiple European Nuclear Tugs, and be set up on the asteroid by 2045.
MLV Saturn V-1

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Stages

### Stage 3

MS-IVB (optional)

The **MLV Saturn V-1** is an American launch vehicle.

The most basic of MLV Saturn Vs. It was the 3rd "Advanced Saturn" to ever fly.

The first 3 flights (SO-1, SO-2, SO-3) were used to validate the Apollo Interplanetary Heatshield.

## Variants:

### Stages:

The rocket can launch with either 2 or 3 stages (depending on the mission requirements).

### Fairings:

There are 3 fairing sizes to choose from:

* **6.6 x 27 m**
* **10.1 x 30 m**
* **10.1 x 45 m**
* **12.2 x 45 m (special)** - The 12.2m fairing was developed in response to the 10 m wide habitation module of Coelus Program Ship.

## See Also:

MLV Saturn V-23-L - A variant with either 2 or 4 liquid boosters.
Cronus 1

The **RLS Cronus Block 1** (RLS - Reusable Launch System, also known as simply **Cronus 1**) was an experimental international launch vehicle, which started development in 2002.

It served as a stepping stone between the Saturn family and the Cronus 3.

Several components of the recovery system were tested on Cronus 1, notably parachutes, a heatshield and attitude control.

## Design:

Cronus 1 was an RO-11 / HG-3-2 launch vehicle, evolved from the "Saturn VI" project, that was proposed a decade earlier. It also used SMART style reuse, limited production, maybe 3 launched.

## See Also:

Cronus 2

Cronus 3
Kennedy Space Center/LC-39

The **Launch Complex 39 (LC-39)** was the United States' main gateway to space until LC-69 was constructed.

It consisted of two pads:

* LC-39A
* LC-39B

LC-39C was also planned, with some work on preparing the ground done, but it was scrapped due to budget constraints.

## Upgrades:

The LC-39A and B underwent many upgrades over their lifetime.

Before to the first launch of MLV Saturn V-23-L the launchpads were equipped with a new water deluge system fed from a water tower located at the launchpad.
Kennedy Space Center/Vehicle Assembly Complex

The Vehicle Assembly Complex was enlarged in 1973-1975 to increase maximum height and width of rockets that can be assembled.

This had to be done without stopping the assembly of existing rockets. So a new VAB was constructed north of the existing one, measuring an astounding 220m tall.

The maximum height of a rocket able to be assembled went from 410ft (124.96 m) all the way up to 580ft (176.78 m). This brand new VAB also had wider doors to accomodate bigger rockets.

This new VAB, named VAB2 had smaller footprint than the main VAB and both were be often used together.

In 1975-1979, the widened doors of VAB2 were also retrofitted to the original VAB1. This was done one by one, to keep the rockets' construction going.

This retrofitting of doors enabled full assembly of the MLV Saturn V-23-L to be done within the original VAB1. Previously the boosters had to be attached on the pad or inside VAB2.
MLV Saturn V-25-L-NOM-MS

An MLV Saturn V-25-L with a Neptune Orbital Module Maneuvering Stage bolted to the top of the first stage.

## Design:

The VAB constrained the maximum height of the vehicle. To get around this, the engineers decided to replace the 2nd stage with the payload and use it to do the orbit insertion.

The standard avionics unit, which ordinarily sat on top of the 2nd stage was put on the first instead.
Mobile Launcher 2

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **Mobile Launcher #2** was one of the original Saturn V MLs.

## Missions:

### Saturn V launcher:

* Apollo 8
* Apollo 10
* Apollo 13
* Apollo 15

### MLV Saturn V-23-L (franken-launcher pt.1):

Following the late October 1973 launch of the Apollo 19, the ML-2 was modified to support the V-23-L.

The first round of modifications were tailored for the MLV Saturn V-23-L specifically, to make sure the ML-2 was ready for its scheduled test flight.

* 1974 - SA-601

### MLV Saturn V-23-L (franken-launcher pt.2):

And after the successful test of the MLV Saturn V-23-L first stage and boosters, the ML-2 returned to the parking site and completed its modifications.

Its height was greatly increased, to be record-breaking. It supported launching MLV Saturn V-24-L-TSCC, as well as MLV Saturn V-23-M1. To do that, it used a lot of double-purpose arms, as well as similar arms at different levels.

* 1976 - SA-602
* 1976/07 - Othrys 1
* Othrys 10
* Othrys 13
* Othrys 16
* Othrys 19
* Othrys 22
* Othrys 25

### NERVA launcher:

The Forward TSCC umbilical arm was replaced with one designed for the new MS-IVN NERVA stage.

* 1979 - NERVA In-Flight Test 1
* 1982 - NERVA In-Flight Test 2

### MLV Saturn V-24-L-MS / MLV Saturn V-24-L-TSCC-U (franken-launcher pt.3):

The ML-2/LUT was selected to be modified to support the V-24-L-MS and V-24-L-TSCC-U. Many already existing arms were repurposed, others were replaced, but the result was the same - many dual-purpose arms supporting 2 different umbilical schemes of 2 different rockets.

* 1990 - Coelus 1
* SA-603
* Coelus 14
* Coelus 17
* Coelus 20
* Coelus 23

### MLV Saturn V-25-L-NOM-MS launcher:

Following Coelus program, the ML-2 was stripped down and rebuilt at the parking site. Now sporting only 4 umbilical arms, designed to support the largest rocket ever flown up to that time.

* Arion 2
* And more...

## Trivia:

The ML-2 was the heaviest of all Mobile Launchers, had the highest number of arms, and was the tallest.
MLV Dynamic Test Stand

The **MLV Dynamic Test Stand** is a test stand that was used for the dynamic load testing on the SA-600F.

MLV Saturn V-23-L dynamic test articles was tested there.

They didn't need a separate vehicle to validate the MLV Saturn V-1, as the V-1 is identical to the V-23-L, just with the boosters removed, and changes to the control software.
RO-63

The **RO-63** was a cooperative project between Russia, USA, France, and Germany to develop a gas-core nuclear thermal engine in the thrust range of 400-600 kN and Isp in the range of 1,500-2,000 s.

It used the "nuclear lightbulb" technology

RO-61 - first test article, first firing: 2033

RO-62 - second test article, first firing: 2037

**RO-63** - production starts in 2039

RO-64 - upgraded version made with advanced materials, first firing in 2055, 3000 s Isp.

RO-65 - the final update, using exotic materials and containment methods to raise the core temperature by 20% compared to the RO-64. First firing in 2070s, 3300 s Isp.
M-1

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Throttle

unknown

The **M-1** is an American rocket engine, designed and built by Aerojet.

## Usage:

M-1 engines were used on the MLV Saturn V-23-M1, and the uprated M-1A was used on the MLV Saturn V-24-L-MS rockets.

The M-1 was the preferred option over a large (7x) cluster of J-2S engines. However, its use was limited, due to size (as only one could be fitted to a stage at a time), and relatively low specific impulse. The stages using the M-1 engine were also a lot larger than the J-2S-equipped MS-II.

The introduction of the M-1A reduced the problem of thrust and specific impulse.

## See Also:

M-1A - Uprated variant

MLV Saturn V-23-M1 - The first launch vehicle using the M-1 engine.

MLV Saturn V-24-L-MS - The second (and last) launch vehicle using the M-1 engine (M-1A variant)
Cronus 2

The **RLS Cronus Block 2** (RLS - Reusable Launch System, also known as simply **Cronus 2**) is an international launch vehicle, developed in the 2010s onwards.

The Cronus 2 was used mostly as a testbed to develop new reusability techniques and procedures.

It tested the maneuvers that would be later used on the Cronus 3 launch vehicle.

## Design and Development:

The Cronus 2 vehicle was developed directly from Cronus 1 and based on it.

The Cronus 2 project ran in 3 main steps, which were its primary variants. But despite that, practically no Cronus 2 was identical, as incremental changes and improvements were applied after each flight.

The first 2 variants were powered by the RO-11 engine, the last variant by RO-21.

They all launched from LC-39A at Cape Canaveral.

### Cronus 2-I:

A testbed for powered landing of the 1st stage. It used landing legs to land on a separate landing pad at Landing Site 1 at Cape Canaveral.

### Cronus 2-II:

A testbed for powered landing of both the 1st and the 2nd stage. Used landing legs and a landing pad (1st stage), and parachutes and retrorockets (2nd stage).

For this stage, the LS-1 was expanded and another landing pad (named LS-2) was built nearby.

### Cronus 2-III:

A testbed for powered landing of both stages. Landed on a simulated launch mount built at the landing site.

A semi-functional structural replica of the launch stand was built at the 1st stage landing site. The booster was equipped with RO-21 engines, and used to land on that structure, to validate the rapid reuse system proposed for the future Cronus 3 vehicle.

## See Also:

Cronus 1

Cronus 3
MS-IC-337

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Engines

* 5x F-1A
OR
5x F-1A-CW

## Launch History

### First flight

1976

The **MS-IC-337** is an American rocket stage designed by MSFC and Boeing and manufactured by Boeing.

## Design:

It's a S-IC stage stretched 337 inches and strengthened to be able to mount side boosters and heavier upper stages.

This stage can handle either UA1205, UA1207 or MS-IC-LFB boosters.

### LOX Tank:

The LOX Tank was stretched 208 in (5.28 m).

### RP-1 Tank:

The RP-1 Tank was stretched 129 in (3.28 m).

## See Also:

S-IC

MS-IC-240

MS-IC-2
Neptune Orbital Module Maneuvering Stage

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Engines

* 8x RO-51
* 48x R-4D-11 (164:1) (RCS)
* 4x R-8D (Ullage)

## Launch History

### First flight

unknown

The **Neptune Orbital Module Maneuvering Stage (NOM-MS)** is an American rocket stage, built by Boeing.

## Design:

It's the biggest single rocket stage ever built and flown, measuring an astounding 12.2 m in diameter and almost 100 m long.

The stage consists of following components:

### Forward Skirt:

The Forward Skirt is 3 meters tall and 12.2 meters in diameter.

### LH2 Tank:

The main LH2 Tank is made from a composite material, designed to be very light and very strong. It's lined with <something> to prevent hydrogen leakage that was a problem on Othrys and Coelus programs.

It's covered by approximately 7 tons of advanced multilayer insulation.

The LH2 Tank can be considered to be a "semi-balloon" tank. It can support itself when not pressurized, but only when no loads are applied to it.

### Aft Skirt:

The AftSkirt is 3 meters tall and 12.2 meters in diameter.

### Thrust Structure:

The Thrust structure consists of internal structural elements embedded inside the tank. The engines were mounted directly to the tank, to composite protrusions, permanently embedded in the tank's structure.

### Heat/Sun Shield:

The Heat/Sun Shield protects the tank and engines from excess heating. It's a circular structure made out of carbon fiber composite honeycomb covered in MLI blankets, with 8 slots cut out for engines.

### Hydrogen Recirculation System:

The Hydrogen Recirculation system was a complex system designed to mitigate boiloff. It did it by actively cooling the hydrogen tank contents.

The hydrogen inside the tank, when the engines were off, was constantly being pumped through a series of pipes connected to cooling modules, which kept the fuel at below liquid temperature.

It required quite a lot of power, which was achieved by plugging it into the reactor module of the spacecraft.

### Aerodynamic Fairing:

The Aerodynamic Fairing protected the NOM-MS's MLI on ascent from Earth.

## See Also:

Neptune Orbital Module Return Stage

Synergistic Transfer Stage
Mobile Launcher 3

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **Mobile Launcher #3**.

## Missions:

### Saturn V launcher:

* Apollo 11
* Apollo 14
* Apollo 16
* Apollo 17

### MLV Saturn V-23-M1 combo launcher:

After SA-600F, ML-3 was modified to additionally support the overgrown V-23-M1. This happened in the around 1 year time between early 1974 and mid 1975.

* 09/1975 - Spacelab 1
* SO-1
* SO-2
* SO-3
* Othrys 6
* Othrys 8
* Othrys 11
* Othrys 14
* Othrys 17
* Othrys 20
* 1977 - Othrys 23

### MLV Saturn V-24-L-MS launcher:

* 1991 - Coelus 12
* Coelus 15
* Coelus 18
* 1992 - Coelus 21

### MLV Saturn V-25-L launcher:

Between 1992 and 1998 ML-3 was modified to support the new V-25-L.

* 2001 - SA-703
* Arion 8
* Arion 9
* and more...

## Part of:

Mobile Launcher
HG-3-1

The **HG-3-1** is an American rocket engine built by Rocketdyne.

Used by the Othrys Program. First version to feature a medium-to-long duration capability. Rated to restart up to 5 times and up to 3 years between restarts, although it should be possible to leave it dormant for much longer, it was never tested on this variant.

## See Also:

HG-3-2

HG-3-3
RD-0412

The **RD-0412** (GRAU: 11B92B) was Soviet (and later Russian) nuclear thermal rocket engine.

## Design:

The Engine was designed in the early 1980s, as a cheap upgrade to the RD-0411 engine.

The main difference between RD-0411 and RD-0412 is the nozzle. RD-0412 has a nozzle extension, while RD-0411 does not.

Due to the nozzle extension as well as increased fuel flow to the engine, it was uprated from 40 to 45 tons of thrust.

The RD-0412's nozzle extension is roughly 25% the length of the standard RD-0411 nozzle.
RL-10A-3-3A

The **RL-10A-3-3A** is an American rocket engine.

A final refinement to the RL-10A-3 model was the RL-10A-3-3A. In this configuration, the throat diameter was once again reduced, resulting in a higher expansion ratio. Chamber pressure was also increased, resulting in the first uprating of engine thrust (to 16,500 Ib) since the RL-10A-1.

First flight on 26.09.1975
Proposals/MS-VII

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Launch History

### First flight

Around early 2000s

The **MS-VII** (pronounced "ms-seven") stage is an American advanced rocket stage, proposed for the MLV Saturn V-27-L rocket.

## Design:

The stage would use seven RO-51 nuclear thermal rocket engines as main propulsion.
European Launcher Development Organisation

The **European Launcher Development Organisation (ELDO)** was a former European space research organisation. It was first developed in order to establish a satellite launch vehicle for Europe.

The organisation consisted of Belgium, Britain, France, Germany, Italy, and the Netherlands. Australia was an associate member of the organisation.

## History:

In 1961, Britain and France announced that they would be working together on a launcher that would be capable of sending a one-ton satellite into space.
Coelus 12

The **Coelus 12** was the twelveth mission of Coelus program, and the second one to suffer a partial failure.

The failure was related to the M-1A engine underperforming. As a result, the refuelling vehicle was put into a lower than expected orbit, but managed to rendezvous with the mothership after expending nearly all of its rendezvous propellant.

## See Also:

Coelus 2 - the other flight that suffered a partial failure.
Cronus 3 RV

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Engines

* 4x HG-3-3,
* unknown landing motor

The **Reentry vehicle of Cronus 3** is a spacecraft/rocket stage.

Each tank has 2 sumps, one at the bottom, and one on the side. This allows for feeding the landing motors, when the reentry vehicle is in its "skydive" flight.

The motors are fed by a single turbopump, in effect acting like one engine.
MLV Saturn V-25-L

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Stages

### Stage 2

MS-VB

The **MLV Saturn V-25-L** is an American launch vehicle. It's the first launch vehicle designed using the MS-IC-2 core stage.

This is the first vehicle in the 3rd generation of Saturn V rocket family to fly.

Fairing options:

* 12.2 x 60 m (composite)

## See Also:

MLV Saturn V-5 - A variant with no boosters and a shorter 2nd stage, and a 12.2 x 45 meter fairing.

MLV Saturn V-25-L-R - Variant with partially reusable core stage.
Mobile Launcher

The Mobile Launcher is what Saturn rockets sit on during rollout and liftoff.

## Several were built:

The crane could swing from side to side, and its trolley could move back and forth along the length of the crane arm. This allowed workers to raise equipment beside the LUT or the mobile service structure and then manhandle it into position at the appropriate level.

Two high-speed elevators ran from level 340 to level B inside the launcher. These elevators traveled at 600 ft (183 m) per minute. They could be operated from within the elevator cab, and could also be controlled remotely from the Launch Control Center in the event of an emergency.

### ML-4:

First launch - 1973/04/01.

Saturn III/IV and commercial MLV Saturn III launcher.

### ML-5:

First launch - 1976/07.

MLV Saturn III/IV-TSCB, MLV Saturn III/IV-TSCB-U and later commercial MLV Saturn III/IV launcher.

Does not have the crew access arm.

### ML-6:

First flight - 1976. Built for MLV Saturn V-23-M1.

### ML-7†:

First flight - 1991.

MLV Saturn V-1, destroyed when SA-701 exploded on the launchpad.

### ML-8:

First flight - 1990.

MLV Saturn III/IV-TSCB-U.

### ML-9:

First flight - 1995.

Construction started 2 months after ML-7 was lost.

MLV Saturn V-24-L-STSB dual-purpose.
HG-3

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **HG-3** was an American upper stage hydrogen/oxygen engine family. The HG-3 engines were built by Rocketdyne at their Canoga plant.

## Development:

The HG-3 was developed directly from the J-2S engine.

It was designed as a high-performance replacement of the J-2S, in places where the extra thrust and specific impulse was needed. Most notably, for deep space maneuvers required by Othrys and Coelus programs.

The first HG-3-1 engine was ready for flight in november 1976 or earlier.

## Design:

The prototype engine's nozzle was initially very similar to the J-2S', but reinforced with extra rings. The throat was shrunk, elongating the top of the nozzle. The powerhead was completely different however, the only thing in common was overall placement of the fuel/ox inlets (however, they were slightly shifted outwards).

The production versions (HG-3-1 onwards) used a different nozzle, with larger exit diameter and expansion ratio however.

The engine is heavier than the J-2S.

## Usage:

At first, its use was limited, due to complexity and high cost. The simpler and cheaper J-2S worked just fine in most applications. However, HG-3s were selected to power the TSCC and TSCB, due to their greater efficiency.

When the HG-3 was selected to be the primary upper stage engine of the 2.5nd generation of Saturn rockets, great efforts were made to decrease the cost the engine.

## Variants:

### HG-3-1

An HG-3 with improved reliability, a redesigned (and reinforced) nozzle, and ability to restart up to 5 times. In total, 44 production engines were delivered for the Othrys program. Starting in January 1976, only 7 months before launch of Othrys 1.

Almost immediately after the HG-3 program was started, a more rugged version was proposed, for use in crewed interplanetary missions. The specifications were put forth in 1973, and the first prototype was constructed in late 1975, as part of Othrys program. The engine was extensively tested and scrutinized, to ensure it would work properly after 3 years of coasting in interplanetary space.

### HG-3-2

An improved HG-3 used for Coelus program as well as the 2.5nd generation of Saturn rockets. First prototype was tested in mid 1980s, first flown in 1991. Able to restart up to 5 times.

The improvements include redesign of the turbopump assemblies, changes to the injector plate, slightly reduced throat diameter, and switch to a channel wall nozzle construction.

The HG-3-2 was significantly cheaper, as well as lighter than its predecessors, this was achieved as part of the requirements to use it as a standard upper stage engine for 2.5nd generation of Saturn rockets.

* Isp (vac): 458 s.

## See Also:

J-2

J-2S
MLV Saturn V-3

The **MLV Saturn V-3** is a version of the MLV Saturn V-24-L, without any boosters.

The design was finalized in 1991, alongside the MLV Saturn V-24-L.

Would needs to launch slightly underfuelled, due to its 5 F-1A engines not having quite enough thrust when the boosters are removed.

## See Also:

MLV Saturn V-24-L - A variant with 2 or 4 liquid boosters.
LR91-AJ-3

The **LR91-AJ-3** was an American rocket engine developed and built by Aerojet.

This version featured changes to reduce parts count, reduce weight and to eliminate LR87-AJ-1's design problems. As with the LR87-AJ-3, the **LR91-AJ-3** incorporated dry-jacket engine starting. The LR91-AJ-3 also replaced the reinforced plastic gaseous helium start bottle with one made from titanium that was less prone to leak.
Lyndon B. Johnson

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

**Lyndon Baines Johnson** was a US president, he succeeded John F. Kennedy.

Johnson won the 1964 presidential election, and was later re-elected in the 1968 election, and served until August 9, 1974.

His administration withdrew from the Vietnam War during 1968 peace talks.
M-1A

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Throttle

unknown

The **M-1A** is an American rocket engine, built by Aerojet.

It's an M-1 engine uprated to produce 1.8 Mlbf of thrust.

## Design:

Redesigned injector plate, 5% smaller throat, and some minor changes to the turbopumps.

The changes resulted in the engine being easier to manufacture, having higher specific impulse, and being more durable.
MLV Saturn V-24-L-TSCC-U

A MLV Saturn V-23-L adapted to lift the enormously heavy Transfer Stage Common Core unit along with the main capture and escape stages. Was launched with its payload partially fuelled.

The payload, once in orbit weighed 540t.

## Trivia:

The rocket's second stage was completely removed to make room for the payload. The first stage of the payload was used for the majority of orbit insertion.

The "-U" stands for "Uranus".
RO-12

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Throttle

60% - 100%

The **RO-12 (a.k.a RD-370)** is essentially an RO-11 engine adapted to run on FLOx 30/70.

Notable modifications done to the engine include revised injector assembly and updated coatings on the inner side of various pipes.

Oxidizer:fuel ratio = 3.2:1

## Specifications:

Switching to a FLOx 30/70 oxidizer resulted in a great increase in performance without the extreme difficulty in using pure Lqd Fluorine.
MS-II-2

The **MS-II-2** is an American rocket stage built by Rockwell International.

The the first flight article ready by early 1993.

## Design:

The basic design of the stage is very similar to the MS-II, but on the inside, they differ a lot on manufacturing methods.

It's stretched extra 146 in compared to the MS-II (total stretch of 187 in) and with J-2S engines replaced by 5 HG-3s.

This stage's hydrogen tank and forward skirt are covered by spray-on foam insulation, while the lower section is painted white, making it look very distinctive.

### Forward Skirt:

The Forward Skirt is a cylindrical section 11 ft 5 in (137 in, 3.47 m) tall.

## See Also:

S-II

MS-II

MS-V

MS-VB
Proxima Centauri system

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

Proxima Centauri is a red dwarf star located 4.2465 ly from the Sun.

The Proxima Centauri system consists of:

* Proxima Centauri
* Proxima Centauri d (0.029 AU) (rocky planet)
* Proxima Centauri b (0.05 AU) (rocky planet)
* Dust ring (~0.4 AU)
* Proxima Centauri c (1.5 AU) (gas-dwarf)
* Ice/Dust ring (~1-4 AU)
* Ice ring (~30+ AU)
F-1A

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### Throttle

100%

The **F-1A** was a gas generator cycle engine developed from the F-1 engine by the United States in the early 1970s, for use in the "Advanced Saturn" project.

## Design:

The engine was a simplified and uprated version of the F-1, better suited towards mass production. The design of the engine became much more standardized. Compared to the craftsmanship required to assemble the F-1, F-1A's parts were more interchangeable.

The F-1A was also substantially cheaper overall, which was a result of both the simplifications, as well as the sheer amount of engines that were produced, driving the cost down by the economy of scale.

## Usage:

It was most notably used in MS-IC family of rocket stages, which included MS-IC-240, and MS-IC-337, as well as the MS-IC-LFB, a side booster for "Advanced Saturn" rockets.

Over 600 F-1A and F-1A (late) engines were produced between 1972 and 2015.

## Variants:

* **F-1A**
* F-1A (late), a.k.a F-1A-CW

## See Also:

F-1

RO-11
MLV Saturn III-IV-TSCB

A modified version of MLV Saturn III/IV, with its payload fairing and payload adapter removed and a 10m diameter Transfer Stage Common Booster mounted on the top.

## Design:

Two different conversions were made. One for the 8.4m booster, and one for the 10.1m booster. The main difference being redesigned payload adapters.

It was originally planned that the boosters for Othrys Program would be launched using MLV Saturn V-1s, but budget cuts necessitated that the MLV Saturn III/IV be chosen instead.
MLV Saturn V-23-L

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Stages

### Stage 3

MS-IVB (optional)

The **MLV Saturn V-23-L** is an American launch vehicle.

## Development:

In 1966 NASA launched a study on how to increase the payload capacity of the Saturn V rocket. This study concluded that stretching and strenghtening stages, along with the uprated versions of F-1 and J-2 would increase the payload by about 20 tons, to the total of 160t (this version would be later known as MLV Saturn V-1).

Adding boosters was also something that was studied. At first, 4 UA1205 or UA1207 were studied as possible boosters for Saturn V. Custom liquid boosters were also designed at that point. The core stage would need even more strenghtening to be able to handle them.

It was the 2nd "Advanced Saturn" to ever fly.

## Design:

### MLV Saturn V-23-L:

The **MLV Saturn V-23-L** exists in 2 variants: 2-stage and 3-stage. They're sometimes represented by an additional number after the designation - *"MLV Saturn V-23-L-2"* and *"MLV Saturn V-23-L/2-2"*.

The rocket can launch with either 2 or 4 boosters. The configuration can be represented by adding */2* or */4* to the end of the designation. If no number is present, it can be assumed that the rocket has 4 boosters.

It shares the core stage with the unboostered variant. They are identical, minus the external booster attachment points.

The design was finalized in 1972, with the first launch - SA-601 (a test of the first stage cluster) taking place in early 1975.

The 2nd launch lifted off later in 1975, launching the Spacelab 1 mission.

### MLV Saturn V-23-M1:

The MLV Saturn V-23-M1 is an upgraded version with a more powerful 2nd stage.

## See Also:

MLV Saturn V-1 - A variant with no boosters
Proton-K

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Stages

### Stage 3

Block V

The **Proton K** (Russian: Протон-К) (GRAU: 8K82K) was a Soviet/Russian launch vehicle.

The first Proton rocket was launched in 1965. The first Proton-K was launched in 1967.

It was crew-rated.
Coelus Docking Tug

The **Coelus Docking Tug** was the vehicle used to dock together parts of the Coelus Program Ship.

## Design:

There were 2 main types of the docking tug.

### Baseline:

Had 1 AJ-10/147 hypergolic engine.

A modified version of it was used to dock boosters. It needed to be modified in order to attach it to the boosters.

### Double:

Had 2 AJ-10/147 hypergolic engines.

A modified version of it was also a part of the refuelling vehicle used to refuel the Coelus Program Ship.
Continuous Fission Reaction Drive

The Continuous Reaction Fission Drive (CRFD) is a type of propulsion that utilize salts of Uranium to achieve something similar to a small continuous nuclear bomb detonation.

A.k.a. Nuclear Saltwater Engine.

They can have thrust values in excess of 10 000 kN

There are regulations on where and how it can be fired, due to its radioactive exhaust.

In general - don't point it at any celestial body in the vicinity.
International Lunar Surface Station

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **International Lunar Surface Station (ILSS)** is a lunar base established in the early 2020s.

The proposal dates back to the late 1990s and early 2000s.

It's located at the south pole.

Its initial goals were to study the feasibility of mining and manufacturing on the moon, and other celestial bodies. To confirm and test the various different methods developed.

Welding, smelting, 3D-printing, and more were all tested and proven here.

Later on a mining and processing facility for the lunar regolith and various subsurface ices was built at the base.

The various manufacturing methods for a mass-scale production of aerospace-grade aluminum alloys from lunar soil were developed in the 2030s and 2040s. Resulting in creation of the Series 10000 aluminum alloys, specifically for describing alloys using lunar materials.

In late 2040s the Lunar Structural Production and Test Plant at the base opens and begins production and testing of rocket tankage and other structural elements made primarily from series 10000 aluminum alloys.

Around the same time, a LOX / LH2 / CH4 storage facility is built, facilitating propellant for hotfire testing of the stages. Engines and other more complex components are delivered from Earth.

In the 2050s the base begins to get deliveries of propellant (mostly LH2) from the newly opened Asteroid Outpost.

Another plant is established at the Mare Tranquillitatis, producing lunar titanium.

Some time later, around 2060, the Trek for the Sea of Tranquility begins - a railway laying operation aimed to connect the lunar station with the titanium extraction facility at Mare Tranquillitatis. it lasts for around 15 years before the railway opens.

Nuclear powered trains start running on the track, delivering titanium to the station where it's smelted and turned into hardware.
Proposals/Iapetus Explorer Probe

## Iapetus Explorer Probe (cancelled)

The **Iapetus Explorer Probe** was a cancelled American deep-space probe that was to be carried by the Othrys Program Ship, separate mid-flight and insert itself into Iapetus' orbit to collect data.

Proposal called for launch using the MLV Saturn III/IV rocket.

It was scrapped in favor of human landing on Iapetus.
RL-10A-4-3-3P

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

## Performance

### N.o. ignitions

50

The **RL-10A-4-3-3P** is an American rocket engine.

NLSTS engine, limited production, long-duration capable. Incorporates the full suite of improvements from the RL-10A-4 and RL-10A-4-1 engines. Has a fixed, carbon nozzle extension, ratio between the RL-10A-4 and RL-10B-2.

## See Also:

RL-10A-3-3-1P - Othrys program variant.

RL-10A-3-3-2P - Multibody Transfer System (Coelus) variant.
Orbital Construction Yard

A large orbital construction yard will be created in orbit around Earth. Utilizing the manufacturing capability of the lunar base, fuel from the asteroid outpost to transport the parts from the moon.

I predict the construction of the orbital construction yard will start in the year 2065-2075.

It would be useful if it was modular, and allowed easy access to all places around the ship that's being constructed. So a highly motorized thing.

It could also be self-propelled to move to wherever it’s needed right now.

it needs propellant storage for the nuclear engines

We are now starting to have serious orbital construction capability.

The construction ends in 2080s

Now we have the large structure orbital construction capability.

We will be able to construct very large structures, like launchpads, and more now.

We also will be able to construct very large crewed interplanetary spacecraft.

They will allow faster travel with more people - something that is crucial.

They should be fully reusable

With the direct transfer method, allowed by our new heavy spacecraft, the transfers will no longer be Hohman.

This means that more stations arranged in a ring is useful.
Michoud Assembly Facility

The **Michoud Assembly Facility** is a manufacturing complex in New Orleans, owned by NASA.

The factory's ceiling height limitation was 12 meters.

In late 1990s it was expanded with an additional building that could house stages up to 15 meters in diameter. In preparation to build the NOM-MS and NOM-RS there.

## The following rocket stages were built at Michoud:

* S-I
* S-IB
* S-IIIC
* MS-IIIC
* MS-IIIC-2
* S-IC
* MS-IC-240
* MS-IC-337
* MS-IC-2
* MS-IC-LFB-240
* MS-IC-LFB-337
* MS-IC-LFB-2
* NOM-MS
* NOM-RS
S-IVB

The **S-IVB** was an American rocket stage.

## Design:

The S-IVB consists of following elements:

### Forward Skirt:

The Forward Skirt is 260 in (6.6 m) in diameter and 10 ft 2 in (122 in, 3.1 m) tall.

It's constructed from 7075-T6 Aluminum Alloy.

### Common bulkhead:

The Common bulkhead is a 2 in thick honeycomb structure. It consists of a fiberglass reinforced phenolic honeycomb core adhesively bonded between two hemispherically shaped domes.

Forward dome is 0.125 in thick, aft dome is 0.133 in thick.

### Aft Skirt:

The Aft Skirt is 260 in (6.6 m) in diameter and 85 in (2.16 m) tall.

### Thrust Structure:

The Thrust Strucure is constructed from 7075-T6 Aluminum alloy. The engine mount fitting is constructed from 356-T6 Aluminum Alloy.

The bottom of the thrust structure ends approximately 78 in (2 m) below the bottom of the Aft Skirt.
Asteroid Mining

The first thing that is viable is mining for propellant.

Asteroids equipped with mining, processing, and storage facilities for Liquid Oxygen, Liquid Hydrogen, and Liquid Methane will be the first to be mined.

At first, a near-earth asteroid is preferred, later more mining rigs and depots will be dotted throughout the solar system.

Timeline:

2000-2020 - Searching for suitable target asteroids, development of technology, small scale tech demonstrators.

2045 - Roughly when the first mining rig is set up on an asteroid. It may take a few more years for it to become operational.

2070 - by this time, 2 or 3 more mining rigs are set up
Mobile Launcher 4

The Mobile Launcher #4 was the vanilla MLV Saturn III, and MLV Saturn III/IV launcher.

## Missions:

### MLV Saturn III/IV launcher:

Between 1973 and mid 1974 the ML-4 was modified to support the stretched MLV Saturn III/IV. It was used only once in that configuration, before being dismantled and rebuilt for the MLV Saturn III.

It was never heightened, so when MLV Saturn III/IV-TSCB was launched off of it, it was shorter than the rocket. As opposed to its "sister" ML - the ML-5

* late 1974 - Long Duration Engine Restart Test
* 1976/07 - Othrys 3
* 1976/08 - Othrys 5

### MLV Saturn III launcher:

The ML-4 was modified to support the shortened MLV Saturn III. It was then put to use on a lot of commercial launches.

* 1977/09 - Hermes Probe
* TDRS-A Commsat deployment
* Commsat deployment
* Classified DoD mission
* TDRS-B Commsat deployment
* TDRS-C Commsat deployment
* TDRS-D Commsat deployment
* Gallileo Spacecraft
* 1990/04/24 - Hubble Space Telescope launch
* Coelus 24
* 1995 - Hale Space Telescope launch
* 1995 - Hubble Servicing mission 1
* 1995/06/27 - MIR
* TDRS-G Commsat deployment
* 1999/07/23 - Chandra X-Ray Observatory launch
* 2003/12/24 - Arion 11
* and more...
NPO Energomash

*The information presented in this article is **true for my alternate history**, but either completely false, or only partly true for real life.*

The **NPO Energomash "V. P. Glushko"** is a Russian rocket engine manufacturer.

Notable for manufacturing most of the USSR's and Russia's rocket engines, including the RD-270, and later RO-11.