Nova Advanced - MM Nova Advanced Concepts - Martin Marietta Credit: © Mark Wade. 10,905 bytes. 641 x 351 pixels.

Before there was Saturn, when it was still known as the Juno V, there was - NOVA. The US Air Force had begun development of a 1.5 million pound thrust engine, the F-1, in the 1950�s. When NASA was formed, it considered a new launch vehicle beyond the Saturn, using the F-1 engine and capable of sending a manned expedition to the moon. This launch vehicle was identified as Nova in NASA�s first long range plan, delivered to President Eisenhower on January 27, 1959.

NASA, Von Braun�s team at Huntsville, and major aerospace contractors conducted a number of design studies of Nova from January 1959 to June 1960. A common characteristic was the clustering of modular units consisting of an F-1 or J-2 engine and their associated propellant tanks. The first Nova designs used four F-1�s in the first stage and had a translunar payload of only 24 tonnes. Once the three-man, 5 tonne Apollo capsule was settled on, payload for a direct landing on the moon increased quickly - first to 45 tonnes, then finally over 60 tonnes. The number of F-1�s in the first stage correspondingly increased to 8 or 9.

Despite the selection of Saturn in 1961, studies on Nova continued into the middle of 1962. There were those at NASA headquarters who advocated using large solid rocket motors in place of an F-1 liquid fuelled first stage. They were sure these could be developed in time for the deadline, allowing the use of Nova to launch a direct landing mission to the moon. The first Nova did not finally die until the great �mode debate� was settled in June 1962 with the selection of lunar orbit rendezvous for the landing method. This marked the end of consideration of Nova designs dedicated to launch of a direct-landing Apollo spacecraft.

But was not quite the end of Nova. The launch vehicle was now recharacterised as the �next� launch vehicle after the Saturn V. Design objective was a million-pound payload to low earth orbit. Two major rocket companies that did not receive production contracts for Saturn stages - General Dynamics (Convair) and Martin Marietta - were given �consolation� study contracts for Nova in July 1962. Philip Bono of Douglas Aircraft characteristically did his own study without a contract. The contractors were to make preliminary designs of million-pound-payload launch vehicles that explored all possible combinations of:

• one versus two stages
• use of existing (F-1A and M-1) engines versus higher thrust, higher performance engines
• recovery and reuse of either or both stages

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The following table cross tabulates the Nova launch vehicle types versus contractor, indicating lift-off masses, in millions of kg, normalised to a million pound payload:

Another aspect of Nova was how to transport and erect such huge launch vehicles. NASA had already selected and purchased land for Nova launch sites north of the Saturn V�s LC-39. Nova and others of its ilk essentially require transport by water from the factory to the launch site and launch from sea or at least seaside facilities. NASA had the Army Corps of Engineers study some ingenious launch facility designs using barges and water channels under the pad to move the vehicle into position. Because of the enormous sound that would be generated in a Nova launch, remote off shore or towed launch platforms were considered essential. One exotic concept was to launch Nova not from Cape Canaveral, but from launch tubes hollowed into the side of Hawaiian cliffs!

By the end of 1963 NASA no longer foresaw any need for such huge launch vehicles. Saturn V studies had already begun which indicated that, using solid strap-on motors, the Saturn could deliver up to a million pounds to orbit without the need to build new vehicles or facilities. More importantly, most at NASA saw the follow-on to the Saturn V to be a reusable winged shuttle, which would land at air strips and be fully reusable. Nova was cancelled quietly in 1964. However throughout the 1960�s visionaries like Truax and Bono continued to design and advocate very large or single stage to orbit designs like Sea Dragon and Rombus. But in the absence of political support for human colonisation of space or exploration of Mars, the need for such large launch vehicles has not materialised to this day.

Launch Vehicle: Nova 4L. Earliest Nova design, using only 4 F-1's, capability less than later Saturn designs.

Launch Vehicle: Nova NASA. The Nova vehicle most often illustrated in the popular press and histories. As in other early concepts, used F-1 engine in both first and second stages. Resulting performance and total liftoff mass was equivalent to later Saturn V.

Launch Vehicle: Nova 4S. Cluster of 4 240 inch solid motors used as first stage; upper stages as Nova 7S and 8L.

Launch Vehicle: Nova 5S. Nova design using segmented solid motors in first and second stages. Five six segment motors in first stage; four four segment motors in second stage, equivalent to 9 x F-1 first stage and 4 x F-1 second stage.

Launch Vehicle: Nova 7S. Cluster of 7 160 inch solid motors used as first stage; upper stages as Nova 4S and 8L.

Launch Vehicle: Nova 8L. Most capable Nova studied just prior to selection of Saturn for moon landing. Used a three stage configuration of eight F-1 engines in stage 1, two M-1 engines in stage 2, and one J-2 engine in stage 3. Similar to the Saturn C-8 except in the use of M-1 engines. Unlike other modular Nova designs of the time, this one had the unitary stage construction of Saturn.

Launch Vehicle: Nova 8L Mod. First two stages use short Nova building blocks with 2 F-1's in each block. Four used in stage 1, one in stage 2. Typical of early Nova designs with F-1's in both first and second stages.

Launch Vehicle: Nova 9L. Nova design using clustered small diameter tanks; 9 x F-1 first stage and 4 x F-1 second stage; compared with solid Nova using five six segment solid motors in first stage and four four segment motors in second stage.

Launch Vehicle: Nova A. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 4 F-1 engine/modules in first stage, 4 J-2 engine/modules in second stage.

Launch Vehicle: Nova B. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 6 F-1 engine/modules in first stage, 6 J-2 engine/modules in second stage.

Launch Vehicle: Nova C. Vehicle using Nova A as first two stages, nuclear spacecraft with jettisonable tanks as upper stage.

Launch Vehicle: Nova D. Vehicle using Nova B as first two stages, nuclear spacecraft with jettisonable tanks as upper stage.

Launch Vehicle: Nova GD-B. Nova design using existing engines. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Launch Vehicle: Nova GD-E. Nova design using 325 inch solid motors as first stage, M-1 engines in second stage. Recoverable solid motors, separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange. Recovery of solid motors forshadowed same approach on shuttle 15 years later. Masses estimated based on tank volumes, total thrust, and first stage burnout conditions.

Launch Vehicle: Nova GD-F. Nova design using new 3.5 million kgf Lox/Kerosene engines in first stage. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Launch Vehicle: Nova GD-H. Nova design using 1 1/2 stage arrangement and new 2.4 million kgf Lox/LH2 engines. Recoverable booster 4 engine package would separate at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Launch Vehicle: Nova GD-J. Nova design using recoverable Lox/RP-1 stage of ballistic shape with 3 million kgf engines; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Launch Vehicle: Nova MM 14A. Nova design using 4 300 inch solids as first stage, 5 M-1 in second stage. Operational date would have been April 1973

Launch Vehicle: Nova MM 14B. Nova design using 4 280 inch solids as first stage, 4 M-1 in second stage. Operational date would have been February 1973

Launch Vehicle: Nova MM 1B. Nova design using existing engines; 14 F-1A in the first stage, 2 M-1 in the second. Operational date would have been December 1972

Launch Vehicle: Nova MM 1C. Nova design using existing engines; 18 F-1A in the first stage, 3 M-1 in the second. Operational date would have been February 1973

Launch Vehicle: Nova MM 24G. Nova design using new high pressure LH2/Lox engines; 18 in the first stage in a plug nozzle arrangement, 2 in the second. Operational date would have been December 1974.

Launch Vehicle: Nova MM 33. Nova single stage to orbit design with 24 new high pressure LH2/Lox engines in the first stage in a plug nozzle arrangement. Operational date would have been April 1975.

Launch Vehicle: Nova MM 34. Nova 1 1/2 stage design with 4 new 3 million kgf LH2/Lox engines in the jettisonable booster section and a single 3 million kgf sustainer. Operational date would have been June 1976.

Launch Vehicle: Nova MM R10E-2. Expendable version of most exotic Martin Nova vairant; single stage to orbit, 30 cd module air augmented engines in annular shroud. Operational date would have been October 1980.

Launch Vehicle: Nova MM R10R-2. Reusable version of most exotic Martin Nova vairant; single stage to orbit, 30 cd module air augmented engines in annular shroud. Operational date would have been October 1980.

Launch Vehicle: Nova MM S10E-1. Expendable single stage to orbit Nova using cylindrical shape, 24 CD module engines in zero-length plug nozzle. Operational date would have been October 1977.

Launch Vehicle: Nova MM S10E-2. Expendable single stage to orbit Nova using conical shape, 30 CD module engines in zero-length plug nozzle. Operational date would have been November 1977.

Launch Vehicle: Nova MM S10R-1. Reusable single stage to orbit Nova using cylindrical shape, 24 CD module engines in zero-length plug nozzle. Operational date would have been June 1978.

Launch Vehicle: Nova MM S10R-2. Reusable single stage to orbit Nova using conical shape, 30 CD module engines in zero-length plug nozzle. Operational date would have been July 1978.

Launch Vehicle: Nova MM T10EE-1. Two stage Nova using CD modules; expendable first stage with 18 modules exhausting to a 10% length plug nozzle; expendable second stage with 2 CD module engines. Operational date would have been November 1976.

Launch Vehicle: Nova MM T10RE-1. Two stage Nova using CD modules; reusable first stage with 18 modules exhausting to a 10% length plug nozzle; expendable second stage with 2 CD module engines. Operational date would have been January 1977.

Launch Vehicle: Nova MM T10RR-2. Two stage Nova using CD modules; reusable first stage with 24 modules exhausting to a zero length plug nozzle; reusable second stage with a toroidal plug nozzle engine. Operational date would have been December 1976.

Launch Vehicle: Nova MM T10RR-3. Two stage Nova using CD modules; reusable first stage with 18 modules exhausting to a 10% length plug nozzle; reusable second stage with 2 CD module engines. Operational date would have been July 1977.

Launch Vehicle: Nova-1 DAC. Douglas/Bono design for Nova using Lox/RP-1 in first stage, existing engines.

Launch Vehicle: Nova-2 DAC. Douglas/Bono design for Nova using LH2/Lox in both stages.