Alcentar

RealEnginesPack 2.01 CLOSE 01.04.18

Recommended Posts

On 3/10/2018 at 2:27 AM, Alcentar said:

Thanks!   

The next stage is the Merlin engines. :)

are you making the Merlins 1D version?

On 3/20/2018 at 12:22 AM, Ninadragonborn said:

i am using this mod for more than a year does this mod work on v 1.4

Yes

Share this post


Link to post
Share on other sites

I do not understand their versions, at the moment I did this, I can say this is the basis for all version engine.

MERLINblen_3755803_29709253.png

 

Share this post


Link to post
Share on other sites
On 3/21/2018 at 7:26 AM, Alcentar said:

I do not understand their versions[snip]

 

I'll contribute...

In order of development, Merlin Engines:

Heritage Engine - FASTRAC or MC-1 (Development Engine 1998-2001?)

Related imageImage result for mc-1 rocket engine

1998. Open cycle gas generator. Ablatively Cooled. Drawings Here.

  • Mass: ~900kg
  • Thrust (Sea Level/Vacuum): Unknown/270kN
  • ISP (Sea Level/Vacuum): Unknown/314s
  • Throat diameter: 0.22 m
  • Nozzle Diameter: ~1.22 m
  • Area Ratio: ~30

SpaceX Merlin 1A (Flown 2006, 2007)

SpaceX_Merlin_engine.gifMerlin-1A.jpg

Open cycle gas generator. Ablatively Cooled. Video Here.

Key Evolutions: Upscale. New turbopump. TWR Optimized. Turbopump exhaust can be steered for roll control.

Retained Features: Power Cycle, Turbopump supplier. Cooling Type.

  • Mass: Unknown. Ballpark 500 kg
  • Thrust (Sea Level/Vacuum): 325kN/370kN
  • ISP (Sea Level/Vacuum): 253.7s/288.5s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.91 m
  • Area Ratio: 14.5

SpaceX Merlin 1B (Canceled 2007?)

Open cycle gas generator. Ablatively Cooled.

Key Evolutions: Improved Turbopump to Merlin 1C Spec.

Retained Features: Everything but the Turbopump. Turbopump Exhaust Steering.

  • Mass: Unknown. Ballpark 550 kg
  • Thrust (Sea Level/Vacuum): 380kN/420kN
  • ISP (Sea Level/Vacuum): 261s/303s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.91 m
  • Area Ratio: 14.5

SpaceX Merlin 1Ci (Flown 2008-2009)

Image result for merlin 1a rocket  engine

Open cycle gas generator. Regeneratively Cooled. Visible nozzle cooling hoops.

Key Evolutions: Switch to regenerative cooling. Larger Nozzle.

Retained Features: Turbopump, combustion chamber geometry.

  • Mass: 630 kg
  • Thrust (Sea Level/Vacuum): 350kN/395kN
  • ISP (Sea Level/Vacuum): 265s/303s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.96 m
  • Area Ratio: 16

SpaceX Merlin 1C (Flown 2010-2012)

Merlin-1C.jpg

Open cycle gas generator. Regeneratively Cooled. Visible nozzle cooling hoops.

Key Evolutions: Thrust Structure Adaptations. Changed Turbopump exhaust to fixed system. Uprated for higher Thrust.

Retained Features: Pretty Much Everything Else.

  • Mass: 630 kg
  • Thrust (Sea Level/Vacuum): 423kN/483kN
  • ISP (Sea Level/Vacuum): 267s/305s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.96 m
  • Area Ratio: 16

SpaceX Merlin 1C-Vacuum (Flown 2010-2012)

Merlin-1CV.jpg

Open cycle gas generator. Regeneratively Cooled Combustion Chamber & Initial Nozzle. Radiatively Cooled Nozzle Extension.

Key Evolutions: Steerable Turbopump exhaust. Vacuum Optimized Nozzle.

Retained Features: Combustion Chamber Geometry, Turbopump.

  • Mass: ~650 kg
  • Thrust (Sea Level/Vacuum): NA/520kN
  • ISP (Sea Level/Vacuum): NA/336s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~2.5 m
  • Area Ratio: 117

SpaceX Merlin 1C+ (Canceled 2012?)

Merlin-1Cplus.jpg

Open cycle gas generator. Regeneratively Cooled. Channel-Wall nozzle cooling.  Polished Nozzle.

Key Evolutions: Turbopump Evolution. New Nozzle with Channel Wall Cooling (smooth)

Retained Features: Turbopump Hardware, Combustion Chamber.

  • Mass: Unknown. Ballpark 525 kg
  • Thrust (Sea Level/Vacuum): 545kN/617kN
  • ISP (Sea Level/Vacuum): 275s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

 

SpaceX Merlin 1D-Early(Flown 2013-2015)

Merlin-1D.jpg

Open cycle gas generator. Regeneratively Cooled. Polished Nozzle.

Key Evolutions: Brand new turbopump. New Mounting Structure.

Retained Features: Combustion Chamber.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 654kN/713kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-Early(Flown 2013-2015)

Image result for merlin vacuum engine

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Film-Cooled Nozzle.

Retained Features: Combustion Chamber.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/805kN
  • ISP (Sea Level/Vacuum): NA/345s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~2.5 m
  • Area Ratio: 117

SpaceX Merlin 1D-Mid Life(Flown 2015-2018)

11349137_497205827110215_523838749_n.jpg

[Black Paint for Test Article Only]

Open cycle gas generator. Regeneratively Cooled. Unpolished Nozzle.

Key Evolutions: Sub-cooled Propellants ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 763kN/825kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-Mid Life(Flown 2015-2018)

Merlin-1DV.jpg

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Sub-cooled Propellants ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/805kN
  • ISP (Sea Level/Vacuum): NA/347s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~3.08 m
  • Area Ratio: 165

SpaceX Merlin 1D-CrewRated(Flying NET April 2018)

Image result for Merlin 1D

Open cycle gas generator. Regeneratively Cooled. Unpolished Nozzle.

Key Evolutions: Evolved Turbopump ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 845kN/914kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-CrewRated(Flying NET April 2018)

 

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Evolved Turbopump ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/934kN
  • ISP (Sea Level/Vacuum): NA/348s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~3.08 m
  • Area Ratio: 165

 

Of course, there's no expectation that you model all of these. However, this lineage does contain a huge variety of engine performances, and a couple representations out of the group could be really nice.

Share this post


Link to post
Share on other sites
36 minutes ago, zekew11 said:

I'll contribute...

In order of development, Merlin Engines:

Heritage Engine - FASTRAC or MC-1 (Development Engine 1998-2001?)

Related imageImage result for mc-1 rocket engine

1998. Open cycle gas generator. Ablatively Cooled. Drawings Here.

  • Mass: ~900kg
  • Thrust (Sea Level/Vacuum): Unknown/270kN
  • ISP (Sea Level/Vacuum): Unknown/314s
  • Throat diameter: 0.22 m
  • Nozzle Diameter: ~1.22 m
  • Area Ratio: ~30

SpaceX Merlin 1A (Flown 2006, 2007)

SpaceX_Merlin_engine.gifMerlin-1A.jpg

Open cycle gas generator. Ablatively Cooled. Video Here.

Key Evolutions: Upscale. New turbopump. TWR Optimized. Turbopump exhaust can be steered for roll control.

Retained Features: Power Cycle, Turbopump supplier. Cooling Type.

  • Mass: Unknown. Ballpark 500 kg
  • Thrust (Sea Level/Vacuum): 325kN/370kN
  • ISP (Sea Level/Vacuum): 253.7s/288.5s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.91 m
  • Area Ratio: 14.5

SpaceX Merlin 1B (Canceled 2007?)

Open cycle gas generator. Ablatively Cooled.

Key Evolutions: Improved Turbopump to Merlin 1C Spec.

Retained Features: Everything but the Turbopump. Turbopump Exhaust Steering.

  • Mass: Unknown. Ballpark 550 kg
  • Thrust (Sea Level/Vacuum): 380kN/420kN
  • ISP (Sea Level/Vacuum): 261s/303s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.91 m
  • Area Ratio: 14.5

SpaceX Merlin 1Ci (Flown 2008-2009)

Image result for merlin 1a rocket  engine

Open cycle gas generator. Regeneratively Cooled. Visible nozzle cooling hoops.

Key Evolutions: Switch to regenerative cooling. Larger Nozzle.

Retained Features: Turbopump, combustion chamber geometry.

  • Mass: 630 kg
  • Thrust (Sea Level/Vacuum): 350kN/395kN
  • ISP (Sea Level/Vacuum): 265s/303s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.96 m
  • Area Ratio: 16

SpaceX Merlin 1C (Flown 2010-2012)

Merlin-1C.jpg

Open cycle gas generator. Regeneratively Cooled. Visible nozzle cooling hoops.

Key Evolutions: Thrust Structure Adaptations. Changed Turbopump exhaust to fixed system. Uprated for higher Thrust.

Retained Features: Pretty Much Everything Else.

  • Mass: 630 kg
  • Thrust (Sea Level/Vacuum): 423kN/483kN
  • ISP (Sea Level/Vacuum): 267s/305s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~.96 m
  • Area Ratio: 16

SpaceX Merlin 1C-Vacuum (Flown 2010-2012)

Merlin-1CV.jpg

Open cycle gas generator. Regeneratively Cooled Combustion Chamber & Initial Nozzle. Radiatively Cooled Nozzle Extension.

Key Evolutions: Steerable Turbopump exhaust. Vacuum Optimized Nozzle.

Retained Features: Combustion Chamber Geometry, Turbopump.

  • Mass: ~650 kg
  • Thrust (Sea Level/Vacuum): NA/520kN
  • ISP (Sea Level/Vacuum): NA/336s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~2.5 m
  • Area Ratio: 117

SpaceX Merlin 1C+ (Canceled 2012?)

Merlin-1Cplus.jpg

Open cycle gas generator. Regeneratively Cooled. Channel-Wall nozzle cooling.  Polished Nozzle.

Key Evolutions: Turbopump Evolution. New Nozzle with Channel Wall Cooling (smooth)

Retained Features: Turbopump Hardware, Combustion Chamber.

  • Mass: Unknown. Ballpark 525 kg
  • Thrust (Sea Level/Vacuum): 545kN/617kN
  • ISP (Sea Level/Vacuum): 275s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

 

SpaceX Merlin 1D-Early(Flown 2013-2015)

Merlin-1D.jpg

Open cycle gas generator. Regeneratively Cooled. Polished Nozzle.

Key Evolutions: Brand new turbopump. New Mounting Structure.

Retained Features: Combustion Chamber.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 654kN/713kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-Early(Flown 2013-2015)

Image result for merlin vacuum engine

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Film-Cooled Nozzle.

Retained Features: Combustion Chamber.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/805kN
  • ISP (Sea Level/Vacuum): NA/345s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~2.5 m
  • Area Ratio: 117

SpaceX Merlin 1D-Mid Life(Flown 2015-2018)

11349137_497205827110215_523838749_n.jpg

[Black Paint for Test Article Only]

Open cycle gas generator. Regeneratively Cooled. Unpolished Nozzle.

Key Evolutions: Sub-cooled Propellants ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 763kN/825kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-Mid Life(Flown 2015-2018)

Merlin-1DV.jpg

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Sub-cooled Propellants ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/805kN
  • ISP (Sea Level/Vacuum): NA/347s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~3.08 m
  • Area Ratio: 165

SpaceX Merlin 1D-CrewRated(Flying NET April 2018)

Image result for Merlin 1D

Open cycle gas generator. Regeneratively Cooled. Unpolished Nozzle.

Key Evolutions: Evolved Turbopump ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 470 kg
  • Thrust (Sea Level/Vacuum): 845kN/914kN
  • ISP (Sea Level/Vacuum): 282s/311s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~1.08 m
  • Area Ratio: 21.4

SpaceX Merlin 1D-Vacuum-CrewRated(Flying NET April 2018)

 

Open cycle gas generator. Regeneratively Cooled. Film Cooled Nozzle Extension.

Key Evolutions: Evolved Turbopump ---> Higher Mass Flow.

Retained Features: Almost Everything.

  • Mass: 490 kg
  • Thrust (Sea Level/Vacuum): NA/934kN
  • ISP (Sea Level/Vacuum): NA/348s
  • Throat diameter: ~0.24 m
  • Nozzle Diameter: ~3.08 m
  • Area Ratio: 165

 

Of course, there's no expectation that you model all of these. However, this lineage does contain a huge variety of engine performances, and a couple representations out of the group could be really nice.

Thank you for your efforts !!! This will simplify the work!!!

Share this post


Link to post
Share on other sites
9 minutes ago, Alcentar said:

Thank you for your efforts !!! This will simplify the work!!!

Very happy to help. PM me if you have questions, aesthetic or functional.

Share this post


Link to post
Share on other sites

All these historical part mods! How does one even choose between this and Tantsres LV and Contares and BDB? :confused:

Kind of an academic question for me though, as I only have 8GB of RAM on my potato.

Edited by theonegalen

Share this post


Link to post
Share on other sites
22 hours ago, theonegalen said:

I only have 8GB of RAM on my potato

Consider having 16 GB of RAM also being a potato ...
I suggest an SSD at least if you don't have one and a dynamic page file with a max. of 16 GB on it.

Share this post


Link to post
Share on other sites
1 hour ago, Gordon Dry said:

Consider having 16 GB of RAM also being a potato ...
I suggest an SSD at least if you don't have one and a dynamic page file with a max. of 16 GB on it.

And I remember when a single GB of hard drive storage was ludicrously huge.

Share this post


Link to post
Share on other sites
On 3/27/2018 at 12:05 AM, Alcentar said:

Thank you for your efforts !!! This will simplify the work!!!

For even more info, try these links:

http://www.b14643.de/Spacerockets/Specials/U.S._Rocket_engines/engines.htm

http://www.b14643.de/Spacerockets/Specials/Russian_Rocket_engines/engines.htm

http://www.b14643.de/Spacerockets/Specials/European_Rocket_engines/engines.htm

http://www.b14643.de/Spacerockets/Specials/Asian_Rocket_engines/engines.htm

Fills in the missing information about the engines from the first post.

For the general website with other rocket info:

http://www.b14643.de/Spacerockets/

Edited by Jamesbowser

Share this post


Link to post
Share on other sites

I'm sorry, but I'm suspending work on all the add-ons, maybe I will not do modding any more.
Thank you to everyone who supported me all this time!

Share this post


Link to post
Share on other sites

It is very unfortunate, that the engines were excellent.

 

Edited by Grem

Share this post


Link to post
Share on other sites

That‘s sad to hear, your parts are excellent.

Share this post


Link to post
Share on other sites

That sucks, I really enjoyed the detail in these. Thank you for the work you accomplished, maybe let someone take it up? Your engines are better detailed than the ones that come with the spacex mods, they possibly would like them.

Share this post


Link to post
Share on other sites
On ‎01‎.‎04‎.‎2018 at 8:20 AM, Alcentar said:

I'm sorry, but I'm suspending work on all the add-ons, maybe I will not do modding any more.
Thank you to everyone who supported me all this time!

At first I really believed it was an April fool joke, but I'm starting to wonder if it isn't real.
It would really be a shame. 

Share this post


Link to post
Share on other sites
On 12.04.2018 at 3:53 PM, Thomot512 said:

At first I really believed it was an April fool joke, but I'm starting to wonder if it isn't real.
It would really be a shame. 

This is real, not a joke on April 1. :sticktongue:

Share this post


Link to post
Share on other sites
On ‎14‎.‎04‎.‎2018 at 10:09 AM, Alcentar said:

This is real, not a joke on April 1. :sticktongue:

Oh, sad to hear it, your engines are really beautiful.

Thanks for all the work you've already done.

I wish you all the best.

Share this post


Link to post
Share on other sites

Hello Alcentar! I again recently studied data on rocket engines and found that the RD-0124 engine for Phoenix / Zenith rocket will have two combustion chambers and only two nozzles, not 8. This engine will be called RD-0124M. RD-0124A, now available in RealEnginesPack, is a modification of the basic engine RD-0124 for the Angara rocket. It does not differ from the basic RD-0124 by anything other than the construction of the connection and fuel supply. RD-0124M will have two combustion chambers and two nozzles, as I said. The thrust of the engine will be 289.4kN for each chamber with a nozzle, thus a total of 578.8kN.  The number of ignitions will apparently be the same as that of RD-0124A is 2 or more. I ask to redesign the engine model and its properties.

rd0124m.jpg

Edited by Fenyx

Share this post


Link to post
Share on other sites
On 3/29/2018 at 7:06 AM, theonegalen said:

And I remember when a single GB of hard drive storage was ludicrously huge.

Well, in the spirit of oneupmanship.

I can remember when 5MB was a large hard drive, both figuratively and literally (Tandy external 5 MB was approx 500mm x 500mm x 150 mm).

Share this post


Link to post
Share on other sites

mode rs ro the engines of the Raptor have the wrong old characteristics.according to new reports, the raptors have a much modest features

Edited by serg1983

Share this post


Link to post
Share on other sites

Hey Alcentar, huge fan of your work! I'm looking for some ortho 3D renders of 6 engines (all but the F-1 and Merlin you have modeled out already), what's a good way to contact you to see if it'd be possible to get some nice clean .png's of some of your engines for use in a YouTube video? HMU at info@everydayastronaut.com if you see this! :)

Share this post


Link to post
Share on other sites

Hi. Can you add RD-57 (D-57 or 11D57). This is upper stage hydrolox from late 60`s. There is nice model in DECQ's mod and some comfig in RO.

Share this post


Link to post
Share on other sites
This thread is quite old. Please consider starting a new thread rather than reviving this one.

Join the conversation

You can post now and register later. If you have an account, sign in now to post with your account.
Note: Your post will require moderator approval before it will be visible.

Guest
Reply to this topic...

×   Pasted as rich text.   Paste as plain text instead

  Only 75 emoji are allowed.

×   Your link has been automatically embedded.   Display as a link instead

×   Your previous content has been restored.   Clear editor

×   You cannot paste images directly. Upload or insert images from URL.