The M-1 1.5-million pound thrust LOX/H2 engine

[Blackstar]

A couple of years back I went to NASA's archives looking for information on the M-1 rocket engine. I managed to find a fair amount of information on it, including a good program chronology/overview. As a result I drafted an article about the M-1 program that I intend to publish this year.

My impression had been that the M-1 was mostly a paper project, but it turns out that Aerojet built a lot of infrastructure and started component testing before the program was canceled in January 1961. In fact, the design of the M-1 made it easier to build and test components separately compared to many other engines, so they were making progress even though they did not yet have a complete engine.

In addition to the documents, I also found and scanned quite a few M-1 engine photos. I'm including a few of them here and I'll probably upload more later. In addition, I'm going to temporarily post my draft article in case anybody has some comments or corrections.

[Blackstar]

The M-1 was originally planned as an upper stage engine for the Nova. Later it was considered as a potential future upper stage engine for a Saturn V replacement rocket, or also as a potential upper stage engine for the Saturn, replacing the J-2s. In addition, Aerojet evaluated it as a first stage engine.

[Archibald]

Here's a 1967 document about the M-1

http://ntrs.larc.nasa.gov/search.jsp?R=19680006392&hterms=kirby+vacuum&qs=N%3D0%26Ntk%3DAll%26Ntx%3Dmode%2520matchall%26Ntt%3Dkirby%252Bvacuum

[joncz]

Seems like the RS-25 SSME can trace its lineage to the M-1.  Thoughts on the issues the M-1 would have had, in particular with reference to the complex start sequence and timings the RS-25 developed through trial and error?  I can only imagine what the test failures would have looked like.

[the_other_Doug]

Here's a 1967 document about the M-1

http://ntrs.larc.nasa.gov/search.jsp?R=19680006392&hterms=kirby+vacuum&qs=N%3D0%26Ntk%3DAll%26Ntx%3Dmode%2520matchall%26Ntt%3Dkirby%252Bvacuum

Oooh -- now this would have made a Nova-class vehicle using the M-1 a bit of a sporty affair to handle and prepare for launch:

"The prototype ignition system configuration had not been selected at the time this effort was terminated. However, a fluorine gas hypergolic ignition system for both the gas generator and the thrust chamber appeared to be the best choice. Thrust chamber testing was satisfactorily accomplished using a fluorine hypergolic system."

Fluorine?  Really?  Wow!

[Blackstar]

I like what they did with the cover of their report. Effectively makes their point, huh?

[Antilope7724]

Hydrogen gas pressure vessel problems in the M-1 facilities / by J.S. Laws, V. Frick, J. McConnell.
by Laws, J. S. Published 1969

ABSTRACT
This report delineates pertinent data and information related
to a series of failures, or structural defects, experienced with high
pressure, gaseous hydrogen storage receivers procured for, installed,
and used as part of the M-1 Engine Development Program.

FOREWORD
The research described herein was conducted by the Aerojet-General
Corporation, Liquid Rocket Operations. It was performed under NASA
Contract NAS 3-2555 with Mr. W. H. Rowe, Airbreathing Engines Division,
NASA Lewis Research Center, as Technical Manager. The report was
originally issued as Aerojet-General Report No. 8800-67, April 1966.

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106732263;view=1up;seq=1

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M-1 engine subscale injector tests / Herbert E. Scott, Harry E. Bloomer, Ali H. Mansour.
by Scott, Herbert E. Published 1967

SUMMARY
Subscale tests were conducted to assess the performance-stability tradeoff of
several M-1 engine injector-element configurations. The tests were conducted at
15 000 pounds thrust with a 5. 39-inch-diameter chamber.

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106870287;view=1up;seq=1

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M-1 injector development : philosophy and implementation / Walter F. Dankhoff ... [et al.].
Published 1968

ABSTRACT
The M-1 injector design was a cooperative effort between Aerojet-General Corpora-
tion and Lewis Research Center to achieve high performance with completely stable op-
eration. The approach was based on the technology already established in the RL-10 and
J-2 engine development programs, supplemented with the latest data obtained at NASA-
Lewis. Scall-scale tests were conducted to verify design concepts prior to incorporation
into the full-scale hardware. Full-scale injector testing demonstrated that the design
goals were achieved.

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106745489;view=1up;seq=1

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Cold-air performance evaluation of scale model oxidizer pump-drive turbine for the M-1 hydrogen-oxygen rocket engine. II, Overall two-stage performance / by Richard J. Roelke, Roy G. Stabe, and David G. Evans. by Roelke, Richard J. Published 1966

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106594697;view=1up;seq=1

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COLD-AIR PERFORMANCE EVALUATION OF SCALE MODEL OXIDIZER PUMP-DRIVE TURBINE FOR THE M-l HYDROGEN-OXYGEN ROCKET ENGINE
III - Performance of First Stage With Inlet-Feedpipe-Manifold Assembly
By Roy G. Stabe and John F. Kline Lewis Research Center

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106871624;view=1up;seq=1

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Cold-air performance evaluation of scale model oxidizer pump-drive turbine for the M-1 hydrogen-oxygen rocket engine.
 IV, Performance of first stage with modified inlet feedpipe-manifold assembly / Roy G. Stabe, John F. Kline. by Stabe, Roy G.Published 1968

http://babel.hathitrust.org/cgi/pt?id=uiug.30112106871632;view=1up;seq=1

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[Blackstar]

[Blackstar]