Starship

Starship and Super Heavy launch Stack

Starship is the name of the 2019 version of the second stage of the SpaceX reusable super heavy lift vehicle, resting upon the Super Heavy booster. The term "Starship" may also be used to refer to the complete stack of both stages as well.

Development history

2016 Interplanetary Transportation System

The origins of Starship are rooted in the Interplanetary Transportation System. This architecture was revealed in a 2016 speech by Elon Musk at the International Astronomical Congress. The concept was conceived as a two-stage spacecraft able to be reused a thousand times and to hold crews of over a hundred people with its primary intent to send people to Mars. The concept would depend upon tanker ships and orbital refueling, and it would extensively utilize in-situ resource utilization to produce the methane fuel required for the return voyage to Earth.

The design was immense, with a twelve meter diameter and depended upon forty-two methane Raptor engines on the booster alone, allowing it to produce thrust of thirteen-thousand metric tons. The stacked system would stretch up one-hundred-twenty-two meters into the sky. Upon stage separation, the booster would return to the launch site, landing propulsively on the launch mounts so that it could quickly be refueled and again flown. The second stage, which in some launches would include a habitat, had nine additional Raptor engines to accelerate the ship to Low Earth Orbit. In order to continue a trip to Mars, the second stage would have to be refueled by one or more tankers.

The proposal of the carbon fiber launch vehicle came with an estimated necessary cost of investment of ten billion dollars by Elon Musk, who suggested that a massive public-private partnership might be the best option for the vehicle. The original timeline of the proposal called for structures and propulsion development to be completed in 2019, when ship testing and orbital testing where to begin. Orbital testing was to be completed in late 2022, and shortly thereafter Mars flights were to begin.

Musk acknowledged that this timeline was incredibly ambitious, but he believed that it was not too unreasonable. Musk took pride in announcing that two components of the system had already been built and were undergoing testing: the twelve-meter carbon fiber tank to store oxidizer in the second stage and the first development versions of the Raptor methane full-flow staged combustion engine. Initial tests of the carbon fiber tank proved to be successful, with Musk noting that his company had not "seen any leaks or major issues" when testing the tanks with cryogenic propellent. After heavy testing, the tank was destroyed in February 2017.

2017 Big Falcon Rocket

Over the course of a year, Musk and SpaceX recognized that a smaller, more feasible system was necessary to be pursued. Musk revealed the scaled-back design at the 2017 International Astronomical Congress almost exactly a year after the original unveil of the system. Musk also announced that the working name for the spacecraft was BFR, officially the Big Falcon Rocket. The height of the two-stage craft was reduced to one-hundred-six meters, and the diameter was reduced to nine meters.

2018 Starship-Super Heavy

This version was presented by Elon Musk during the announcement of Yusaku Maezawa' Dear Moon project, as an evolution of the BFR/BFS concept and Interplanetary Transportation System (ITS) concepts.

2019 Starship-Super Heavy

Originally planned to be constructed of carbon fiber composite, it was changed to a Stainless Steel design in January 2019 .

Comparison of various iterations

	2016 ITS	2017 BFR	2018 Super Heavy- Starship	2019 Super Heavy - Starship
Iteration announced	27 Septemer 2016
Stack height	122 m	106 m	xx m - 55 m	118 m
– First stage height		58 m		68 m
– Second stage height		48 m		50 m
Diameter †	12 m	9 m	9 m	9 m
Principle material	Carbon fiber	Carbon fiber	Carbon fiber	301 Stainless steel
First stage thrust	128 MN	48 MN		72 MN
Mass to Low Earth Orbit	300 t	150 t		100 t
Engines	42- 9	47 Raptors	xx- yy	43 Raptors
– First stage engines		31 Raptors		37 Raptors
– Second stage engines		2 Sea-level Raptors 4 Vacuum Raptors	7 Sea-level Raptors	6 Raptors
Propellant capacity		3625* t		4500 t
– First stage capacity		2525* t		3300 t
– Second stage capacity		1100 t		1200 t
Pressurized volume		825 m³
Principle sources
* Indicates that this number is unofficial † Diameter has always been the same for the first and second stages

Characteristics of Starship

85-120 tonnes mass, 9m diameter, 100-150 tonnes of payload to LEO, 100-150 tonnes to Mars. These are target values, the lower the mass of the vehicle, the higher the payload mass will be. Payload volume of 1000 m3.

3 vacuum Raptor engines with 380s ISP and 3 atmospheric Raptor engines with 330s ISP. Nominal thrust of 2000 kN, (200 tonnes of force per engine) These numbers are subject to change as the engine and the vehicle concepts are under development.

120-160 day transportation time to Mars, using aerocapture at Mars.

Fully reusable, rapid turnover and low maintenance vehicle.

Up to 100 passengers to Mars, although this has not been demonstrated yet by SpaceX.

Enabling technologies

The fundamental enabling technology of the Starship is supersonic retro propulsive landing on Mars. The use of supersonic retropropulsion in a critical phase of the Mars entry path allows the vehicle to land heavier payloads that previously thought possible. Although the exact details are not public, the current SpaceX Falcon 9 booster rocket has done flight tests that would confirm the flight path.

A second enabling technology is the capacity of refueling in orbit.

A third enabling technology is the use of methane as fuel, than can be provided by In-situ ressources production systems on Mars, and therefore allow for the re-use of the spaceship.

A fourth technology is a robust heat shield for Mars and Earth entry. This allows for fast re-use and lower costs, but also for faster transit times, reducing the radiation exposure to travellers. The Spaceship is not intended to use low energy Hoffman transfer orbits, but higher velocity orbits. These have lower transit times but leave the vehicle with significant velocity when it reaches Mars or Earth. The Starship must then use direct entry and aerodynamic braking to shed the kinetic energy from the extra velocity.

The NASA Ames research center trajectory browser can be used to explore transit times to Mars and other bodies in the Solar System. Trajectory browser