Sea Dragon internal and external views. Both show the ballast tank attached to the first-stage engine bell. An Apollo CSM-like spacecraft is mounted on top.
The Sea Dragon was a 1962 conceptualized design study for a two-stage sea-launched orbital super heavy-lift launch vehicle. The project was led by Robert Truax while working at Aerojet,one of a number of designs he created that were to be launched by floating the rocket in the ocean. Although there was some interest at both NASA and Todd Shipyards,the project was not implemented.
With dimensions of 150m (490ft) long and 23m (75ft) in diameter,Sea Dragon would have been the largest rocket ever built. As of 2024[update],among rockets that have been fully conceived but not built,it is by far the largest ever and,in terms of payload into low Earth orbit (LEO),equaled only by the Interplanetary Transport System concept (the predecessor to SpaceX Starship) in the latter's expendable configuration with both designed for 550 tonnes.
Design
Truax's basic idea was to produce a low-cost heavy launcher,a concept now called "big dumb booster." To lower the cost of operation,the rocket itself was launched from the ocean,requiring little in the way of support systems. A large ballast tank system attached to the bottom of the first-stage engine bell was used to "hoist" the rocket vertical for launch. In this orientation the payload at the top of the second stage was just above the waterline,making it easy to access. Truax had already experimented with this basic system in the Sea Bee[1][NB 1] and Sea Horse.[2][NB 2] To lower the cost of the rocket,he intended it to be built of inexpensive materials,specifically 8mm (0.31in)steel sheeting. The rocket would be built at a sea-side shipbuilder and towed to sea for launch. It would use wide engineering margins with strong simple materials to further enhance reliability and reduce cost and complexity. The system would be at least partially reusable with passive reentry and recovery of rocket sections for refurbishment and relaunch.[3][4]
The first stage was to be powered by a single 36,000,000kgf (350MN;79,000,000lbf) thrust engine burning RP-1 and LOX (liquid oxygen). The tank pressure was 32atm (3,200kPa;470psi) for the RP-1 and 17atm (1,700kPa;250psi) for the LOX,providing a chamber pressure of 20atm (2,000kPa;290psi) at liftoff. As the vehicle climbed the pressures dropped off,eventually burning out after 81 seconds. By this point the vehicle was 25 miles (40km) up and 20mi (32km) downrange,traveling at a speed of 4,000mph (6,400km/h;1.8km/s). The normal mission profile expended the stage in a high-speed splashdown some 180 miles (290km) downrange,though the potential for recovering the stage was studied as well. The noise of the engine was so powerful it was the reason the rocket was to be sea launched;On land it would have torn itself apart from the vibrations,and crushed the launch pad.
The second stage was also equipped with a single very large engine,in this case a 6,000,000kgf (59MN;13,000,000lbf) thrust engine burning liquid hydrogen and LOX. It was also pressure-fed,at a constant lower pressure of 7atm (710kPa;100psi) throughout the entire 260second burn,at which point it was 142mi (229km) up and 584mi (940km) downrange. To improve performance,the engine featured an expanding engine bell,changing from 7:1 to 27:1 expansion as it climbed. The overall height of the rocket was shortened somewhat by making the "nose" of the first stage pointed,lying inside the second-stage engine bell.
A typical launch sequence would start with the rocket being refurbished and mated to its cargo and ballast tanks on shore. The RP-1 would also be loaded at this point. The rocket would then be towed to a launch site,where the LOX and LH2 would be generated on-site using electrolysis;Truax suggested using a nuclear-powered aircraft carrier as a power supply during this phase. The ballast tanks,which also served as a cap and protection for the first-stage engine bell,would then be filled with water,sinking the rocket to vertical with the second stage above the waterline. Last minute checks could then be carried out and the rocket launched.
The rocket would have been able to carry a payload of up to 550 tonnes (540 long tons;610 short tons) or 550,000kg (1,210,000lb) into LEO. This is enough to comfortably launch the ISS in a single launch (which weighs a "mere" 450 tons). Payload costs,in 1963,were estimated to be between $59 and $600 per kg (roughly $500 to $5,060 per kg in 2020 dollars[5]). TRW (Space Technology Laboratories,Inc.) conducted a program review and validated the design and its expected costs.[6] However,budget pressures led to the closing of the Future Projects Branch,ending work on the super-heavy launchers they had proposed for a crewed mission to Mars.
Principle of the Sea DragonComposite of two NASA technical drawings,of the Saturn V rocket and the proposed Sea Dragon rocket,to the same scale. The second stage of Saturn V would fit inside the first-stage engine and nozzle of the Sea Dragon.A composite visualization of the Sea Dragon standing in front of the NASA Vehicle Assembly Building for scale.
Sea Dragon in fiction
The Sea Dragon appears in the first-season finale of the 2019 Apple TV+ series For All Mankind. The series is set in an alternate history timeline in which the 1960s-era space race did not end. In the post-credits scene,which takes place in 1983,a Sea Dragon is depicted launching from the Pacific Ocean to resupply the US lunar colony. An astronaut says in a voice-over that the ocean launch is being used as a safety measure because the payload includes plutonium.[7] The Sea Dragon continues to play a role in season 2;its high payload capacity is used to resupply an expansive lunar base and is the subject of a lunar blockade by the Soviet Union.[8] There are some small changes from the original concept compared to the version in the series,namely a lack of Launch Abort System for the Apollo capsule at the top of the rocket,and the lack of expanding second stage nozzle,instead using a large,more standard rocket engine,with four additional engines surrounding.
↑ Sea Bee was a proof of principle program to validate the sea-launch concept. A surplus Aerobee rocket was modified so that it could be fired underwater. The rocket worked properly the first time in restrained mode. Later tests of repeat firings proved so simple that the cost of turn-around was about 7% that of a new unit.
↑ Sea Horse demonstrated sea-launch at a larger scale and on a rocket with a complex set of guidance and control systems. It used a surplus 9,000kgf (20,000lbf; 88,000N) pressure fed, acid/aniline Corporal missile on a barge in San Francisco Bay. This was first fired several metres above the water, then lowered and fired in successive steps until reaching a considerable depth. Firing from underwater posed no problems and there was substantial noise attenuation.
↑ "Study of Large Sea-Launch Space Vehicle," Contract NAS8-2599, Space Technology Laboratories, Inc./Aerojet General Corporation Report #8659-6058-RU-000, Vol. 1 – Design, January 1963
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