06-17-2015, 01:08 PM

Here's a study summary and pics from May of 1962 discussing the options for a solid-propellant NOVA launch vehicle for a direct-ascent flight to the Moon with direct landing on the Moon by the Apollo spacecraft. This is another study made around the same time as the JPL study on this same topic published at roughly the same time period, alongside numerous other industry studies on large solid propellant rocket concepts.

This one would have produced a 35 million pound vehicle with 40 million pounds of liftoff thrust, built around clustered solid rocket motors in four stages. The first stage would have been 75 feet in diameter, and it would have stood about 282 feet high (less payload). It would have been capable of delivering 500,000 lbs to LEO, or inject 130,000 lbs to the Moon.

It also makes some basic comparisons to the "C-8" Saturn NOVA proposal, which would have had 8 F-1 engines in the first stage.

Enjoy! OL JR

[attachment=73]

First, the solid NOVA system...

[attachment=74]

Second, A model of the NOVA injection vehicle...

[attachment=75]

Third, liquid and solid NOVA vehicles in scale with the Washington Monument...

[attachment=76]

Fourth, estimated vehicle parameters...

[attachment=77]

Fifth, propulsion characteristics...

[attachment=78]

More to come! OL JR

First, rocket motor production facility concepts...

[attachment=79]

Second, propellant processing facility proposal at the Cape...

[attachment=80]

Third, physical description of the facilities...

[attachment=81]

Fourth, launch operations schedule...

[attachment=82]

Fifth, final assembly and launch site (offshore launch pads).

[attachment=83]

More to come! OL JR

First, cost summary...

[attachment=84]

Second, comparison of various solid NOVA studies by industry and critiques...

[attachment=85]

Third, relative occurrence of malfunctions in rocket flight (as it pertains to flight reliability)...

[attachment=86]

Fourth, Solid Nova and C-8 schedule comparisons...

[attachment=87]

Fifth, Solid Nova and C-8 cost comparisons...

[attachment=88]

More to come! OL JR

First, comparison of solid and liquid stage system complexities (solid motor vs. Agena)...

[attachment=89]

Second, Agena hydraulic system complexity...

[attachment=90]

Third, static test of Aerojet 100 inch solid August 1961...

[attachment=91]

Fourth, clustered solid rockets for Explorer upper stages...

[attachment=92]

Fifth, conceptual NOVA designs...

[attachment=93]

More to come! OL JR

First, summary of stage weights...

[attachment=94]

Second, truss type interstage concept...

[attachment=95]

Third, longeron type interstage concept...

[attachment=96]

Fourth, pressurized vs. turbopump TVC thruster systems...

[attachment=97]

Fifth, continuation of previous slide...

[attachment=98]

More to come! OL JR

First, secondary injection TVC system configuration study...

[attachment=99]

Second, drag coefficient vs. Mach number, faired vs. unfaired solid NOVA vehicle (with or without aerodynamic fairings over exposed SRM head-ends, interstages...)

[attachment=100]

Third, CG/CP locations over time...

[attachment=101]

Fourth, Vehicle performance parameters...

[attachment=102]

Fifth, stage inert weights (also referred to as "steps" in this study).

[attachment=103]

More to come! OL JR

First, comparison of computed and assumed stage weights for solid NOVA...

[attachment=104]

Second, sensitivity of gross vehicle weight to vehicle dry weight to propellant load ratios...

[attachment=105]

Third, physical description of the facilities...

[attachment=106]

Fourth, various propellant components and 1961 production capabilities...

[attachment=107]

Fifth, spacecraft mass projections breakdown...

[attachment=108]

More to come! OL JR

First, spacecraft design study for liquid vehicles (would work with the solid NOVA)...

[attachment=109]

Second, spacecraft design using hybrid rocket engines... (Convair designs, as previous)...

[attachment=110]

Third, lunar landing velocity increments and weights for liquid propellant lunar lander...

[attachment=111]

Finally, lunar landing velocity increments and weights, for hybrid or solid motor lunar lander vehicle...

[attachment=112]

That's all... Later! OL JR

This one would have produced a 35 million pound vehicle with 40 million pounds of liftoff thrust, built around clustered solid rocket motors in four stages. The first stage would have been 75 feet in diameter, and it would have stood about 282 feet high (less payload). It would have been capable of delivering 500,000 lbs to LEO, or inject 130,000 lbs to the Moon.

It also makes some basic comparisons to the "C-8" Saturn NOVA proposal, which would have had 8 F-1 engines in the first stage.

Enjoy! OL JR

[attachment=73]

First, the solid NOVA system...

[attachment=74]

Second, A model of the NOVA injection vehicle...

[attachment=75]

Third, liquid and solid NOVA vehicles in scale with the Washington Monument...

[attachment=76]

Fourth, estimated vehicle parameters...

[attachment=77]

Fifth, propulsion characteristics...

[attachment=78]

More to come! OL JR

First, rocket motor production facility concepts...

[attachment=79]

Second, propellant processing facility proposal at the Cape...

[attachment=80]

Third, physical description of the facilities...

[attachment=81]

Fourth, launch operations schedule...

[attachment=82]

Fifth, final assembly and launch site (offshore launch pads).

[attachment=83]

More to come! OL JR

First, cost summary...

[attachment=84]

Second, comparison of various solid NOVA studies by industry and critiques...

[attachment=85]

Third, relative occurrence of malfunctions in rocket flight (as it pertains to flight reliability)...

[attachment=86]

Fourth, Solid Nova and C-8 schedule comparisons...

[attachment=87]

Fifth, Solid Nova and C-8 cost comparisons...

[attachment=88]

More to come! OL JR

First, comparison of solid and liquid stage system complexities (solid motor vs. Agena)...

[attachment=89]

Second, Agena hydraulic system complexity...

[attachment=90]

Third, static test of Aerojet 100 inch solid August 1961...

[attachment=91]

Fourth, clustered solid rockets for Explorer upper stages...

[attachment=92]

Fifth, conceptual NOVA designs...

[attachment=93]

More to come! OL JR

First, summary of stage weights...

[attachment=94]

Second, truss type interstage concept...

[attachment=95]

Third, longeron type interstage concept...

[attachment=96]

Fourth, pressurized vs. turbopump TVC thruster systems...

[attachment=97]

Fifth, continuation of previous slide...

[attachment=98]

More to come! OL JR

First, secondary injection TVC system configuration study...

[attachment=99]

Second, drag coefficient vs. Mach number, faired vs. unfaired solid NOVA vehicle (with or without aerodynamic fairings over exposed SRM head-ends, interstages...)

[attachment=100]

Third, CG/CP locations over time...

[attachment=101]

Fourth, Vehicle performance parameters...

[attachment=102]

Fifth, stage inert weights (also referred to as "steps" in this study).

[attachment=103]

More to come! OL JR

First, comparison of computed and assumed stage weights for solid NOVA...

[attachment=104]

Second, sensitivity of gross vehicle weight to vehicle dry weight to propellant load ratios...

[attachment=105]

Third, physical description of the facilities...

[attachment=106]

Fourth, various propellant components and 1961 production capabilities...

[attachment=107]

Fifth, spacecraft mass projections breakdown...

[attachment=108]

More to come! OL JR

First, spacecraft design study for liquid vehicles (would work with the solid NOVA)...

[attachment=109]

Second, spacecraft design using hybrid rocket engines... (Convair designs, as previous)...

[attachment=110]

Third, lunar landing velocity increments and weights for liquid propellant lunar lander...

[attachment=111]

Finally, lunar landing velocity increments and weights, for hybrid or solid motor lunar lander vehicle...

[attachment=112]

That's all... Later! OL JR