Mountain aerospace research solutions

fenris mk2 engine has arrived

MARS Fenris series engines represent the first incremental change to rocket motor nozzle design since Goddard.  Since his design, every rocket motor that’s reached orbit has been a derivation of the same converging-diverging nozzle.  While classic C-D rocket motor geometry has done well for a very long time, it has for all practical purposes, been perfected to within fractions of a percent of theoretically attainable efficiencies and thrust levels.  Traditional rocket motors are completely dependent on stored oxidizer and fuel to affect combustion and create thrust. Jet engines typically carry no oxidizer, only fuel, and characteristically attain the majority of their thrust by combusting fuel to accelerate air.

 

The methods used to design Fenris Mk2 were triple verified with test data, CFD of the as-tested article matching verified test data and hand calculations.  Armed with these verifications and confirmations, MARS tackled designing the bigger, better, high power Fenris Mk2 around the clock for nearly a year.  The step from the lower power “verification of function” Mk1 to the “time to go to space” Mk2 consumed >358,640 CPU hours and >5,000 man hours. 

 

MARS Fenris series rocket engines are simple to scale, design and build because they take advantage of natural phenomena to intake ambient fluids as free reaction mass.  For a launch from earth this fluid would be air.  If fluid entering the intake contains a compatible oxidizing constituent, like the oxygen in Earth’s atmosphere, that oxidizer is then used to create additional combustion and delta V in the second stage of the thrust chamber. 

 

Fenris Mk2 Specifications:

 

 

 

 

 

 

 

 

 

 

 

 

 

 

The MARS team is thrilled to create the next chapter in space travel with you.

 

 

Aaron Davis                                               Scott Stegman

 

 

Founder / CEO                                                Co-Founder / VP

UNITED STATES

MARS, INC.

BOOSTER / UPPER / EXTRA-PLANETARY

GAS GENERATOR / STAGED (PLANNED)

>60,000 lbf

< 200 lb

15.5 in

16.7 in

LOX/RP-1 (METHANE COMPATIBLE / HYDROGEN PLANNED)

>3,428 (INCREASING WITH VELOCITY)

15,000 - 100,000 lbf

900 psi

COUNTRY OF ORIGIN: 

MANUFACTURER:    

APPLICATIONS:          

CYCLE:                             

THRUST:              

MASS:                            

DIAMETER:                   

LENGTH:                           

PROPELLANT:             

ISP (STATIC/SL):         

THROTTLE:                 

PCHAMBER