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Key Takeaways
- The Space Launch System is NASA’s primary heavy-lift launch vehicle designed for deep space human exploration missions.
- The vehicle utilizes a modular architecture evolving through Block 1, Block 1B, and Block 2 configurations for higher payload.
- Propulsion combines liquid hydrogen and oxygen Core Stage engines with two five-segment solid rocket boosters for ascent.
Introduction
The Space Launch System represents the backbone of the National Aeronautics and Space Administration (NASA) architecture for deep space exploration. This super heavy-lift expendable launch vehicle enables the transport of astronauts and large cargo payloads to the Moon, Mars, and other destinations beyond low Earth orbit. Designed to facilitate the Artemis program, the vehicle integrates proven hardware from previous programs with modern manufacturing techniques and avionics. The system prioritizes high-mass throughput and volume, allowing for the launch of the Orion spacecraft along with co-manifested payloads in a single mission profile.
Development of the launch vehicle centers on a modular approach. This strategy permits the rocket to evolve over time, increasing its capability through incremental upgrades to engines, boosters, and upper stages. The initial configuration, known as Block 1, demonstrated its flight readiness during the Artemis I mission. Subsequent iterations, including Block 1B and Block 2, introduce more powerful upper stages and advanced boosters to meet the demanding requirements of crewed lunar landings and future Martian expeditions.
Core Stage Architecture and Structural Design
The central component of the launch vehicle is the Core Stage. This massive fuselage serves as the structural backbone and carries the cryogenic propellant required for the main engines. Standing approximately 212 feet tall with a diameter of 27.6 feet, the Core Stage is the largest rocket stage ever built by NASA. It creates a unified structure that supports the payload, upper stage, and crew vehicle while absorbing the thrust loads from both the main engines and the attached solid rocket boosters.
Manufacturing and Materials
The Boeing Company manufactures the Core Stage at the Michoud Assembly Facility in New Orleans. The primary structure is composed of aluminum-lithium alloy 2195. This specific alloy offers a significant reduction in weight while maintaining high strength and fracture toughness, a necessity for managing the extreme forces experienced during ascent. The manufacturing process utilizes friction stir welding, a solid-state joining technique that creates stronger and more defect-free bonds compared to traditional fusion welding. This technique is applied to join the large panels and domes that form the propellant tanks.
The stage is covered in a Thermal Protection System (TPS) consisting of spray-on foam insulation. This orange-colored insulation, similar to that used on the Space Shuttle External Tank, serves two primary functions. It isolates the cryogenic propellants from the ambient heat of the atmosphere prior to launch, preventing excessive boil-off. During flight, it protects the aluminum structure from the intense aerodynamic heating generated as the rocket accelerates through the atmosphere.
Forward Skirt
The forward skirt sits at the very top of the Core Stage. It houses the flight computers, cameras, and avionics systems that control the rocket’s flight. This section acts as the logic center for the vehicle, processing data from sensors and issuing commands to the engines and boosters. The forward skirt is constructed from aluminum and connects the Core Stage to the upper stage components. It also manages the structural loads transferred from the upper sections of the rocket down to the rest of the Core Stage.
Liquid Oxygen Tank
Located immediately below the forward skirt is the liquid oxygen (LOX) tank. This vessel holds approximately 196,000 gallons of oxidizer cooled to minus 297 degrees Fahrenheit. The tank design includes slosh baffles to dampen the movement of the liquid during flight, ensuring vehicle stability. A sump assembly at the bottom of the tank feeds the oxidizer into the feedlines. These large feedlines run externally down the side of the intertank and liquid hydrogen tank to reach the engine section at the base of the rocket.
Intertank
The intertank is the rigid structural connector positioned between the liquid oxygen and liquid hydrogen tanks. It is the only dry bay in the Core Stage sections that does not hold propellant. The intertank is heavily reinforced because it serves as the attachment point for the forward tips of the twin Solid Rocket Boosters. The thrust generated by the boosters is transferred into the Core Stage structure through a thrust beam located within the intertank. This section also houses avionics and electronics that require a non-cryogenic environment.
Liquid Hydrogen Tank
The liquid hydrogen (LH2) tank is the largest section of the Core Stage. It holds 537,000 gallons of fuel chilled to minus 423 degrees Fahrenheit. Due to the low density of liquid hydrogen, this tank occupies the majority of the stage’s volume. Like the oxygen tank, it features internal baffles and a sump system. The extreme cold of the hydrogen requires stringent insulation application to prevent the formation of ice on the exterior of the vehicle, which could become a debris hazard during launch.
Engine Section
The base of the Core Stage is the engine section. This complex assembly houses the four RS-25 engines and the thrust structure that distributes the mechanical loads from the engines to the rest of the rocket. The engine section includes the mounting points for the aft segments of the Solid Rocket Boosters. It also contains the auxiliary power units, hydraulic systems for engine gimbaling, and the boattail fairing that manages airflow around the engines at the base of the rocket.
RS-25 Propulsion System
The main propulsion for the Core Stage is provided by four RS-25 engines. These engines are modified versions of the Space Shuttle Main Engines (SSME) that powered the Space Shuttle orbiters for three decades. The RS-25 is a staged-combustion cycle engine that burns liquid hydrogen and liquid oxygen. It is renowned for its high efficiency and reliability. Aerojet Rocketdyne, now a part of L3Harris, is responsible for the design, manufacture, and testing of these engines.
Engine Modifications for Expendability
While the original SSMEs were designed to be reusable, the engines used on the Space Launch System are flown in an expendable configuration. This shift in operational philosophy necessitated several design changes to reduce complexity and cost while increasing performance. The engines operate at a higher thrust level than they did during the Shuttle era. For the initial flights, the engines run at 109 percent of their original rated power level.
Engineers developed new engine controllers to replace the legacy computers used on the Shuttle. The new controllers possess significantly higher processing power and modern interfaces to communicate with the Core Stage avionics. The nozzle insulation was also upgraded to withstand the higher thermal loads experienced during the ascent profile, which differs from the Shuttle’s flight path.
Performance Characteristics
Each RS-25 engine generates approximately 418,000 pounds of thrust at sea level and 512,000 pounds of thrust in a vacuum. The combined thrust of the four engines provides about 2 million pounds of force at liftoff. The engines are gimbaled, meaning they can swivel to steer the rocket. This vector control is managed by hydraulic actuators powered by the Core Stage auxiliary power units. The specific impulse, a measure of fuel efficiency, is 452 seconds in a vacuum, making the RS-25 one of the most efficient chemical rocket engines in existence.
The propellant flow within the engine is driven by high-pressure turbopumps. The high-pressure fuel turbopump rotates at approximately 37,000 revolutions per minute, delivering hydrogen to the main combustion chamber. The staged-combustion cycle redirects a portion of the fuel and oxidizer to pre-burners, which drive the turbines before the exhaust is fed into the main injector. This closed-loop cycle ensures that all propellant is used for propulsion, maximizing efficiency.
Solid Rocket Boosters
Two five-segment Solid Rocket Boosters (SRBs) provide the majority of the thrust required to lift the vehicle off the launch pad. These boosters are an evolution of the four-segment boosters used on the Space Shuttle. Northrop Grumman manufactures the booster motors and manages their assembly. Together, the two boosters contribute more than 75 percent of the total thrust at liftoff.
Segment Composition and Grain Geometry
Each booster consists of five individual motor segments containing solid propellant. The propellant is a mixture of aluminum powder (fuel), ammonium perchlorate (oxidizer), iron oxide (catalyst), and a polymer binder (PBAN) that holds the mixture together and serves as additional fuel. The segments are stacked vertically and joined at the launch site. The addition of a fifth segment compared to the Shuttle booster increases the total impulse and burn time, allowing the rocket to carry heavier payloads.
The internal shape of the propellant, known as the grain geometry, determines the thrust profile of the booster. By shaping the hollow core of the propellant segment, engineers can tailor the thrust output over time. The Space Launch System boosters are designed to provide maximum thrust at ignition to clear the pad, then throttle down slightly to reduce aerodynamic stress as the vehicle passes through the area of maximum dynamic pressure (Max Q), and then throttle back up for the remainder of the burn.
Booster Avionics and Separation
The boosters are equipped with their own avionics systems located in the forward skirt assembly. These systems communicate with the Core Stage flight computers and manage the ignition and thrust vector control. The nozzles at the base of the boosters can be gimbaled to assist with steering the vehicle during the first two minutes of flight.
Separation of the boosters occurs approximately two minutes after liftoff. When the solid propellant is exhausted, pyrotechnic fasteners sever the structural connections to the Core Stage. Small solid rocket motors located at the top and bottom of the boosters fire simultaneously to push the empty casings away from the main vehicle, ensuring they do not collide with the Core Stage as it continues its ascent. Unlike the Shuttle boosters, the Space Launch System boosters are not recovered; they impact the ocean and sink.
Upper Stage Configurations
The upper stage of the rocket is responsible for the final acceleration to orbit and the trans-lunar injection maneuver that sends the spacecraft toward the Moon. The specific hardware used for the upper stage varies depending on the block configuration of the vehicle.
Interim Cryogenic Propulsion Stage (ICPS)
For the Block 1 configuration, the vehicle utilizes the Interim Cryogenic Propulsion Stage. This stage is a modified version of the Delta Cryogenic Second Stage used on the United Launch Alliance Delta IV rocket. It is powered by a single RL10 engine, which burns liquid hydrogen and liquid oxygen. The ICPS provides the necessary thrust to circularize the parking orbit around Earth and then performs the critical burn to break Earth’s gravity and set the Orion spacecraft on a trajectory to the Moon.
The ICPS includes an attitude control system powered by hydrazine thrusters to maintain orientation during coast phases. It is housed within the Launch Vehicle Stage Adapter, which connects the wider Core Stage to the narrower upper stage. The ICPS is a temporary solution designed to enable early Artemis missions while the more powerful Exploration Upper Stage is developed.
Exploration Upper Stage (EUS)
The Block 1B and Block 2 configurations will employ the Exploration Upper Stage. This larger, more powerful stage is designed specifically for the Space Launch System. It features four RL10 engines, providing four times the thrust of the ICPS. The EUS has significantly larger propellant tanks, allowing for greater payload capacity.
With the EUS, the rocket can carry the Orion spacecraft along with a large co-manifested payload, such as a lunar lander module or a gateway habitation module. The EUS enables the vehicle to lift 40 percent more mass to the Moon compared to the Block 1 configuration. This stage is critical for sustainable lunar exploration operations where infrastructure delivery is required alongside crew transport.
Payload Integration and Spacecraft Adapters
Connecting the various stages and the payload requires specialized adapters. These structural elements ensure aerodynamic smoothness and structural integrity while protecting sensitive equipment.
Launch Vehicle Stage Adapter (LVSA)
In the Block 1 configuration, the Launch Vehicle Stage Adapter is a cone-shaped structure that connects the top of the 27.6-foot diameter Core Stage to the 16.7-foot diameter Interim Cryogenic Propulsion Stage. The LVSA protects the ICPS engine and avionics during the ascent through the atmosphere. It is constructed from aluminum-lithium alloy and covered with thermal protection system material. Pneumatic actuators separate the LVSA from the Core Stage once the main engine cutoff occurs.
Orion Stage Adapter (OSA)
The Orion Stage Adapter sits on top of the ICPS (or EUS in future blocks) and connects the rocket to the Orion spacecraft. It houses the separation mechanism that releases Orion once the trans-lunar injection burn is complete. Additionally, the OSA has space to carry small secondary payloads, such as CubeSats. These small satellites are deployed after Orion separates, providing opportunities for scientific research and technology demonstration missions deep in space.
Universal Stage Adapter (USA)
For Block 1B and beyond, the Universal Stage Adapter will replace the LVSA. This adapter connects the Core Stage to the Exploration Upper Stage and extends upward to encapsulate the co-manifested payload. It provides a large volume for cargo, protecting it during launch. The USA is designed to separate cleanly, exposing the payload for extraction or deployment once in orbit.
Operational Launch Infrastructure
Launching a vehicle of this magnitude requires extensive ground support infrastructure. The primary launch site is Launch Complex 39B at the Kennedy Space Center in Florida. The facilities at KSC were extensively modernized to support the specific requirements of the Space Launch System.
Vehicle Assembly Building (VAB)
The stacking and integration of the rocket components take place inside the Vehicle Assembly Building. This iconic structure, originally built for the Saturn V, has been outfitted with new platforms designed to wrap around the SLS vehicle at various levels. These platforms allow engineers and technicians to access the different sections of the rocket for testing, assembly, and closeout procedures. The High Bay 3 integration cell is the dedicated area for SLS assembly.
Mobile Launcher
The Mobile Launcher is a massive steel tower that supports the rocket during assembly in the VAB and transport to the pad. It stands approximately 380 feet tall and includes the umbilical arms that provide power, data, and propellant to the rocket and spacecraft. The Mobile Launcher rests on the Crawler-Transporter, which carries the entire stack to the launch pad. The launcher features a sound suppression system that dumps thousands of gallons of water onto the deck during liftoff to dampen the acoustic energy and protect the hardware.
Crawler-Transporter
The Crawler-Transporter 2 (CT-2) is the specialized vehicle used to move the Mobile Launcher and the rocket. It has been upgraded to handle the increased weight of the SLS stack. The crawler moves at a top speed of roughly 1 mile per hour when loaded. It utilizes a hydraulic leveling system to keep the rocket perfectly vertical as it ascends the incline to the launch pad surface.
Flight Profile and Ascent Timeline
The flight profile of the Space Launch System is a carefully choreographed sequence of events designed to maximize performance and ensure crew safety. The timeline varies slightly depending on the specific mission and block configuration, but the general phases remain consistent.
Liftoff and Ascent
At T-0, the four RS-25 engines and the two Solid Rocket Boosters ignite. Hold-down posts on the Mobile Launcher release the vehicle, and it begins to rise vertically. The rocket executes a roll maneuver to align itself with the required launch azimuth. As the vehicle accelerates, it passes through Max Q, the point of maximum dynamic pressure, where mechanical stress on the structure is highest. The engines throttle down during this phase to keep loads within safety limits.
Booster Separation
Approximately two minutes and 12 seconds into the flight, the solid rocket boosters burn out. At this point, the vehicle is traveling at roughly Mach 4.5 and is at an altitude of about 28 miles. The separation motors fire, pushing the boosters away from the Core Stage. The Core Stage engines continue to fire, accelerating the vehicle toward orbit.
Core Stage Main Engine Cutoff (MECO)
The Core Stage burns for approximately eight minutes. During this time, the launch abort system tower (if present) and the service module fairings are jettisoned to reduce weight. At roughly eight minutes and 30 seconds, the RS-25 engines shut down. The vehicle has reached an altitude of roughly 100 miles and is traveling at orbital velocity, approximately 17,500 miles per hour.
Stage Separation and Parking Orbit
Following MECO, the Core Stage separates from the upper stage. The Core Stage follows a ballistic trajectory and breaks up upon re-entry over a designated area in the Pacific Ocean. The upper stage (ICPS or EUS) then performs a brief burn to raise the perigee and circularize the orbit. The vehicle coasts in this parking orbit while systems checks are performed and the trajectory for the lunar transfer is calculated.
Trans-Lunar Injection (TLI)
The final major maneuver of the launch vehicle is the Trans-Lunar Injection burn. The upper stage engine reignites to accelerate the spacecraft out of Earth orbit. This burn increases the velocity to approximately 24,500 miles per hour, sufficient to intercept the Moon. Once the burn is complete, the Orion spacecraft separates from the upper stage and continues its journey. The upper stage then performs a disposal maneuver, either entering a solar orbit or impacting the Moon, depending on the mission plan.
Block Evolution and Future Capabilities
The evolutionary path of the Space Launch System ensures that the vehicle remains relevant for decades of exploration. Each block upgrade addresses specific limitations of the previous version and incorporates new technologies.
Block 1
The initial variant, Block 1, is capable of lifting at least 27 metric tons (59,500 pounds) to trans-lunar injection. This configuration is sufficient for testing the Orion spacecraft and sending it on circumlunar trajectories. It relies on the ICPS and the standard five-segment boosters. This is the configuration used for the first few Artemis missions.
Block 1B
The transition to Block 1B involves replacing the ICPS with the Exploration Upper Stage. This single change drastically increases the payload capability to 38 metric tons (83,700 pounds) to trans-lunar injection. Block 1B can fly in two configurations: Crew and Cargo. The Crew configuration carries Orion and a co-manifested payload. The Cargo configuration replaces Orion with a large aerodynamic fairing, allowing for the launch of massive infrastructure components or science probes.
Block 2
The ultimate iteration, Block 2, replaces the steel-cased solid rocket boosters with advanced boosters that use composite casings and improved propellant formulations. These evolved boosters provide greater thrust and weight savings. Block 2 will be capable of lifting 46 metric tons (101,400 pounds) to trans-lunar injection. This heavy-lift capability is essential for long-term Mars mission planning, where reducing the number of launches and on-orbit assembly steps minimizes mission risk.
Comparison with Historical and Contemporary Systems
Understanding the scale of the Space Launch System requires comparison with other heavy-lift vehicles. The most direct historical antecedent is the Saturn V, the rocket that took Apollo astronauts to the Moon.
SLS vs. Saturn V
The Saturn V stood 363 feet tall and could lift 48.6 metric tons to trans-lunar injection. While the initial Block 1 SLS is shorter and lifts less payload than the Saturn V, it produces greater thrust at liftoff (8.8 million pounds versus 7.6 million pounds). The Block 2 SLS will surpass the Saturn V in lift capability, approaching the theoretical limits of what is possible with chemical propulsion. The Saturn V used kerosene and liquid oxygen for its first stage, whereas the SLS uses hydrogen and solid propellant, reflecting the shift in propulsion philosophy post-Apollo.
SLS vs. Starship
A contemporary comparison is the SpaceX Starship system. Starship is a fully reusable super heavy-lift launch vehicle. The design philosophies differ fundamentally: SLS is an expendable vehicle optimized for maximum performance on a single specific mission profile, utilizing high-efficiency hydrogen engines. Starship relies on methane propulsion and rapid reusability, aiming for lower costs through flight frequency. The SLS architecture is integrated deeply with the specific requirements of the Orion spacecraft and NASA’s safety standards for deep space crewed flight, whereas Starship is a broader commercial platform that also serves as the Human Landing System for the Artemis program.
Avionics and Software Systems
The brain of the rocket is a distributed avionics system that manages navigation, communication, and vehicle health. The flight software is based on the ARINC 653 standard, which allows for time and space partitioning. This ensures that critical flight control processes are isolated from less critical monitoring tasks, preventing a software error in one system from crashing the entire computer.
The flight computers are physically redundant, with three computers voting on every command. If one computer disagrees with the other two, it is voted out of the loop. This triple-modular redundancy is a standard safety feature in human spaceflight. The software handles the complex guidance algorithms required to steer the rocket through the changing atmospheric conditions, adjusting the engine gimbal angles in milliseconds to maintain the correct trajectory.
The Role of SLS in the Artemis Program
The Artemis program is structured around the unique capabilities of this launch vehicle. While commercial rockets can launch cargo and smaller components to lunar orbit, the Space Launch System is currently the only vehicle certified to launch the crewed Orion spacecraft. The mass and volume requirements of Orion, combined with the need for a high-energy injection to the Moon, necessitate a super heavy-lift class vehicle.
The co-manifested payload capability of Block 1B is particularly significant for the Gateway, a space station in lunar orbit. SLS allows NASA to transport modules of the Gateway attached to the Orion spacecraft, reducing the complexity of autonomous docking operations. This simplifies the logistics of building a permanent presence in lunar orbit.
Further reading on the history and context of these missions can be found in The Artemis Project or comparable technical literature.
Summary
The Space Launch System stands as a testament to modern aerospace engineering, blending heritage hardware with advanced manufacturing and avionics. Its modular design offers a pathway to increasingly ambitious missions, from lunar flybys to surface landings and eventual Martian exploration. By providing the raw power necessary to escape Earth’s gravity with massive payloads, it enables the scientific and human exploration goals of the 21st century. The successful operation of the Core Stage, boosters, and upper stages demonstrates the viability of this architecture for heavy-lift requirements. As the vehicle evolves through its block configurations, it will remain the primary heavy-lift asset for the United States’ deep space ambitions.
Appendix: Top 10 Questions Answered in This Article
What is the primary purpose of the Space Launch System?
The Space Launch System serves as NASA’s primary super heavy-lift launch vehicle designed to transport astronauts and large cargo payloads to deep space destinations. It is the only rocket currently capable of sending the Orion spacecraft, astronauts, and supplies to the Moon in a single mission.
How does the Space Launch System evolve over time?
The vehicle uses a modular block architecture starting with Block 1, followed by Block 1B and Block 2. Each subsequent block introduces upgrades such as a more powerful upper stage (Exploration Upper Stage) and advanced solid rocket boosters to increase payload capacity.
What engines power the Core Stage of the rocket?
The Core Stage is powered by four RS-25 engines, which are modified versions of the Space Shuttle Main Engines. These engines burn liquid hydrogen and liquid oxygen and are configured for expendable use rather than reuse.
What is the function of the Solid Rocket Boosters?
Two five-segment Solid Rocket Boosters provide more than 75 percent of the total thrust at liftoff. They burn solid propellant to lift the vehicle off the pad and accelerate it through the dense lower atmosphere before separating approximately two minutes into flight.
How does the Block 1 upper stage differ from future versions?
The Block 1 configuration uses the Interim Cryogenic Propulsion Stage (ICPS), a single-engine stage derived from the Delta IV rocket. Future versions like Block 1B will use the Exploration Upper Stage (EUS), which has four engines and significantly larger propellant tanks for heavier payloads.
Where is the Space Launch System manufactured?
The Core Stage is manufactured by Boeing at the Michoud Assembly Facility in New Orleans. The Solid Rocket Booster motors are manufactured by Northrop Grumman in Utah, and the engines are built by Aerojet Rocketdyne (L3Harris).
What is the Launch Vehicle Stage Adapter?
The Launch Vehicle Stage Adapter is a cone-shaped structural connector used in the Block 1 configuration. It connects the Core Stage to the Interim Cryogenic Propulsion Stage and protects the upper stage avionics and engine during ascent.
How does the Space Launch System compare to the Saturn V?
The initial SLS Block 1 produces more thrust at liftoff (8.8 million pounds) than the Saturn V (7.6 million pounds) but has a slightly lower payload capacity. However, the future Block 2 configuration is designed to surpass the Saturn V in lift capability.
What fuel does the rocket use?
The Core Stage and upper stages use cryogenic liquid hydrogen as fuel and liquid oxygen as an oxidizer. The Solid Rocket Boosters use a solid propellant mixture containing aluminum powder, ammonium perchlorate, iron oxide, and a polymer binder.
What is the role of the Mobile Launcher?
The Mobile Launcher is a large tower structure that supports the rocket during assembly and transport to the launch pad. It provides power, data, and propellant connections to the vehicle and includes the crew access arm for astronauts to board the spacecraft.
Appendix: Top 10 Frequently Searched Questions Answered in This Article
How tall is the Space Launch System?
The height of the rocket depends on the configuration, but the Block 1 version stands approximately 322 feet (98 meters) tall. Future configurations like Block 1B and Block 2 will vary in height due to different upper stages and payload fairings.
How much thrust does the Space Launch System produce?
At liftoff, the vehicle generates approximately 8.8 million pounds of thrust. This power comes from the combined output of the four RS-25 liquid engines and the two solid rocket boosters.
Is the Space Launch System reusable?
No, the Space Launch System is an expendable launch vehicle. The Core Stage, boosters, and upper stage are not recovered after launch, although the RS-25 engines are highly efficient and were originally designed for reuse on the Shuttle.
What is the cost of a Space Launch System launch?
While specific per-launch costs vary based on mission parameters and accounting methods, the system is designed as a high-performance government asset rather than a commercial commodity. It prioritizes capability and reliability for deep space missions over the low-cost frequency models of commercial providers.
How fast does the rocket go?
The rocket accelerates to orbital velocity, which is approximately 17,500 miles per hour (28,000 kilometers per hour), to reach low Earth orbit. During the trans-lunar injection burn, the speed increases to roughly 24,500 miles per hour to travel to the Moon.
What is the difference between SLS and Starship?
SLS is an expendable rocket using hydrogen fuel, optimized for deep space crewed missions with the Orion spacecraft. Starship is a fully reusable commercial vehicle using methane fuel, designed for a wide range of applications including Earth-to-Earth transport, satellite deployment, and lunar landing.
When was the first launch of the Space Launch System?
The first flight of the Space Launch System occurred during the Artemis I mission. This uncrewed test flight successfully demonstrated the performance of the rocket and the Orion spacecraft in late 2022.
What is the Exploration Upper Stage?
The Exploration Upper Stage is a powerful new second stage being developed for the Block 1B configuration. It features four engines instead of one, allowing the rocket to carry 40 percent more payload to the Moon compared to the initial version.
How many stages does the rocket have?
The rocket effectively operates as a two-stage vehicle. The first stage consists of the Core Stage and the two Solid Rocket Boosters firing together, and the second stage is the upper stage (ICPS or EUS) that pushes the payload from Earth orbit to the Moon.
Can the Space Launch System go to Mars?
Yes, the Space Launch System is designed to support missions to Mars. Its high payload capacity allows it to launch the heavy habitats and transfer vehicles required for a human mission to the Red Planet, likely using the Block 2 configuration.
