Concept Study of a Cislunar Outpost Architecture and Associated Elements That Enable a Path to Mars

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Concept Study of a Cislunar Outpost Architecture and Associated Elements that Enable a Path to Mars

Presented by:

Timothy Cichan Lockheed Martin Space [email protected]

Mike Drever Lockheed Martin Space [email protected]

Franco Fenoglio Thales Alenia Space Italy [email protected]

Willian D. Pratt Lockheed Martin Space [email protected]

Josh Hopkins Lockheed Martin Space [email protected]

September 2016

Abstract

During the course of human space exploration, astronauts have travelled all the way to the Moon on short flights and have logged missions of a year or more of continuous time on board Mir and the International Space Station (ISS), close to Earth. However, if the long term goal of space exploration is to land humans on the surface of Mars, NASA needs precursor missions that combine operating for very long durations and great distances. This will allow astronauts to learn how to work in deep space for months at a time and address many of the risks associated with a Mars mission lasting over 1,000 days in deep space, such as the inability to abort home or resupply in an emergency.

A facility placed in an orbit in the vicinity of the Moon, called a Deep Space Transit Habitat (DSTH), is an ideal place to gain experience operating in deep space. This next generation of in-space habitation will be evolvable, flexible, and modular. It will allow astronauts to demonstrate they can operate for months at a time beyond Low Earth Orbit (LEO). The DSTH can also be an international collaboration, with partnering nations contributing elements and major subsystems, based on their expertise.

In addition to meeting human spaceflight objectives, the DSTH can help meet exploration science objectives. For example, astronauts in the DSTH could operate a robotic rover, in near real-time, to collect geological samples from lunar farside and return them to the outpost using an ascent vehicle. Returning samples from the South Pole–Aitken Basin (SPA) on the far side of the Moon has been identified as a priority in planetary science Decadal Surveys because it would help scientists understand the early dynamics and impact history of the solar system.

Lockheed Martin is currently studying concepts for a DSTH architecture that evolves in capability over time. This work is being conducted both through internally funded work with partners like Thales Alenia Space Italy (TAS-I) and through the NASA-funded NextSTEP Habitat program. The architecture includes elements such as power and propulsion modules, habitation modules, cargo pods, and an Extra-Vehicular Activity (EVA) Module. The outpost’s capabilities increase with each new element, incorporating lessons learned and new technologies that are needed for Mars such as closed loop life support, laser communication, advanced EVA, In-Situ Resource Utilization (ISRU), and robotics.

Acronyms/Abbreviations LPI: Lunar and Planetary Institute ARM: Asteroid Retrieval Mission NASA: National Aeronautics and Space DRO: Distant Retrograde Orbit Administration DSTH: Deep Space Transit Habitat PG: Proving Ground EM: Exploration Mission PGO: Proving Ground Objective EVA: Extra-Vehicular Activity SEP: Solar Electric Propulsion System FTO: Flight Test Objective SPA: South Pole–Aitken Basin ISRU: In-Situ Resource Utilization SLS: Space Launch System ISS: International Space Station TAS-I: Thales Alenia Space Italy LEO: Low Earth Orbit

Introduction mission scenario, the voyage to and from Mars In recent decades, the goal of human could last up to 12 months round-trip. This spaceflight has been to land astronauts on the transit time represents some of the most risky surface of Mars. However, that goal has always parts of the entire mission, due to the lack of seemed to be firmly on the horizon, just out of viable abort options. The challenges associated reach. Several architecture studies have been with Mars transits include: the increased crew conducted to determine the most efficient and autonomy due to long communication delays, safe method for conducting a Mars mission. the need for highly reliable and regenerative One thing they all seem to agree on is that life support systems, the mitigation of deep there are many variables involved and space radiation, spacecraft serviceability,

Figure 1. Astronauts will need to learn to operate at much greater distances and durations than before in order to prepare for a mission to Mars. potential ways to get there. supplies and logistics, and the increased risks to crew health due to long stays in micro While there are many paths one could take to gravity. get to Mars, they all must deal the same core set of challenges. In general, the challenges of Astronauts have pushed the bounds of a Mars mission can be broken down into three human endurance in space. main categories, the long duration transits to Figure 1 depicts some of those achievements. and from the vicinity of Mars, the descent and A typical expedition on board the International ascent from the surface of Mars, and the actual Space Station (ISS) lasts around 180 days and stay on the surface of Mars. Depending on the in 2015-2016 Scott Kelly and Mikhail

Korniyenko spent 340 days at the ISS. The currently near completion, the Orion record for the longest stay in space goes to spacecraft and the Space Launch System (SLS) Valeri Polyakov, who spent 437 consecutive launch vehicle. Additional required elements days on Mir. Analysis of the long term effects and a mission architecture developed by of such extended stays in space is still Lockheed Martin and Thales Alenia Space Italy ongoing—and even Polyakov’s record is still both privately and as a part of the NASA about one half the duration of an entire Mars NextSTEP Habitation program are discussed in mission. this paper.

While a stay on the ISS doesn’t come without Cislunar Proving Ground Architecture some risks, astronauts always have the ability To undertake a human mission to Mars, to abort their mission in the case of an extreme humans will need to develop the technology, emergency. Such scenarios can have a crew systems and capabilities necessary to live in back on the ground within hours of initiating deep space for extended durations. As a key the abort. On trips to Mars, that will not be the part of this preparation, NASA has established case. The orbits of Earth and Mars mean that a set of proving ground objectives (PGO) and mission opportunities only occur roughly every flight test objections (FTO) to identify what 2 years, and the propulsive requirements are needs to be accomplished in cislunar space [1]. too great to allow astronauts to return home NASA envisions three exploration phases that early in the case of an emergency. incrementally build toward Mars travel [2].

Humans have experienced this challenge to a The ISS is being used to begin the first phase, certain degree. During the Apollo missions, with ongoing research on the ISS aimed at astronauts traveled all the way to the Moon. developing techniques, protocols, and Their abort options to safely return to Earth technology needed for deep space travel. were measured in days not the minutes to Examples include maturation of highly hours of an ISS abort. For Mars there is no regenerative life support systems, tele- practical abort option. Even though the Apollo operation of rovers on Earth, and simulated program was a great achievement in human communications delays. NASA refers to this as spaceflight, those missions lasted only one to Phase 0. The next phase, Phase 1, pushes two weeks. A mission to Mars will take further out into deep space beyond the Van astronauts 1,000 times further away from Allen belts. The focus of Phase 1 is to gain Earth, and will last up to 3 years. confidence and understanding of the transportation systems used to access deep To address the challenges of a Mars mission, space, learning how to work in deep space and it’s clear that what is needed is a test program to make sure the crew stays healthy in the that allows engineers and astronauts to gain process. experience working in deep space for long durations, at long distances from Earth. Such a Pursuit of these objectives requires the program would increase both mission distance establishment of a Deep Space Transit Habitat and duration, addressing strategic objectives (DSTH). Astronauts will demonstrate crewed with increasingly complex missions. Such a flight operations in deep space and begin to program will also require a core set of deep increase crew autonomy. Once the majority of space elements. Two of these elements are the PGOs are achieved, NASA expects to use

the lessons learned to meet objectives for perform science missions that are directly Phase 2, which provides the final development applicable to exploring Mars with astronauts, that will enable travel to Mars. such as processing regolith into useful materials via In Situ Resource Utilization Phase 2 will include the addition of advanced (ISRU). Other objectives are met by operating elements that will serve as precursors to the at a greater distance from the Earth with time Mars transit elements. These new elements delays between the crew and Earth reaching will contain Mars-class systems such as closed- around twenty minutes. Crew health on loop life support and radiation protection. missions outside the protection of Earth’s They will also provide more habitable volume magnetic field or without an easy means to and greater power and propulsion capability. return to Earth quickly is a concern. The The validation of Mars-class elements and Proving Ground missions help broaden our vehicles will be accomplished with missions of understanding of and provide solutions for increasing duration and distance from Earth. these and other crew health issues. As the The final mission in Phase 2 might be a year- flight test objectives are met, astronauts gain long mission to an asteroid in its native confidence and experience in operating more location. autonomously in deep space, (Table 1).

Missions in the Proving Ground incrementally Architecture Elements expand our ability to explore space further Lockheed Martin and our partners have been from Earth and for longer durations while developing a set of vehicle modules to be continuing to return valuable science. Many of a1ssembled and used in cis-lunar space for the objectives are satisfied by deploying and crews to meet Proving Ground Objectives over operating a subsystem that enables living in the course of several missions (Figure 2). The deep space, such as closed loop life support. DSTH is evolvable, flexible, and modular so that Other objectives are achieved as crews as we learn, we can grow and change the

Proving ISS EM-1 EM-2 EM-3 EM-4 EM-5 EM-6 EM-7 EM-8 EM-9 Ground Testing Objectives Transportation

Habitation Working In Space Operations Working In Space Exploration Working In Space Staying Healthy Table 1: Each mission in the proving ground meets critical flight test objectives and increases Mars readiness.5

system to meet new needs and objectives. The operational lifetime of at least 1000 days. Proving Ground objectives are separated into Orion specifications are shown in Table 2, and three phases, starting as ISS and ending with a the spacecraft is described in more detail in [3]. deep space excursion far beyond the Earth Moon System. The focus of this paper is on the Phase 1 elements that operate beyond the immediate safety of LEO.

Figure 3. Orion enables astronauts to explore beyond Low Earth Orbit.

Orion Parameter Performance Total spacecraft ΔV 1,340 m/s Figure 2. The Elements of the Proving Ground available Architecture that will broaden our understanding Crew size 4 of and provide solutions for the challenges of Pressurized volume 20 m3 long-term living in space. Habitable volume 8.9 m3 Main engine thrust 27 kN 3.1 Orion Auxiliary engine thrust 8 x 0.5 kN Orion is the next-generation human Electrical power 11.0 kW, 120 Vdc exploration spacecraft being developed by On-orbit mass 25.8 tons NASA. The Orion spacecraft includes a launch Usable propellant mass 8.6 tons abort system, a pressurized capsule with living Typical reentry velocity 11.05 km/s space for four astronauts, and an attached Crew systems Galley, toilet, exercise equipment service module, provided by the European Table 2: The Orion spacecraft is the only vehicle Space Agency, which provides propulsion, designed to take astronauts into deep space. solar power, and thermal management Orion independently provides the capabilities to Orion is a critical component in making the safely carry four astronauts from Earth to DSTH safe and reliable for human occupancy. beyond the Moon (Figure 3). The elements of To minimize the complexity and cost of the the Proving Ground Mission Architecture DSTH, Orion systems such as solar arrays, augment Orion’s capabilities to allow for more communications systems, carbon dioxide ambitious missions. In a mated configuration, scrubbers, and attitude control systems are where consumables are not used or are used to add redundancy to the other elements resupplied from the DSTH, Orion has an while astronauts are present (see Table 3).

During uncrewed periods the Habitat Support adequate levels of redundancy for robotic Vehicle controls the DSTH, employing operations. Function DSTH Orion

Life Support  Trace contaminant control and  CO2 and humidity removal during pressure control during habitat crewed periods crewed missions  Ventilation and air filtration  O2 and N2 commodity supply for  Fire detection, suppression, and 60 days recovery  Peak humidity removal during  Human waste management enhanced exercise  Trace contaminant control, pressure countermeasures control, O2 and N2 supply during  Ventilation and air filtration transit periods  Fire detection and suppression Power Primary power source in untended Orion power surplus supports outpost mode when occupied EVA Provides full EVA capability when Provides contingency EVA capability EVA module is added to the DSTH Rendezvous Passive docking target Relative navigation capability and and Docking active docking vehicle Crew Systems  Exercise equipment for long Contains galley, toilet, and additional duration missions privacy quarters  4 sleep stations Communicatio High bandwidth communication to Medium bandwidth communication ns lunar surface and to Earth to Earth Radiation Some shielding provided through Built-in solar storm shelter with on- Protection sleep shelters and general board real-time radiation monitoring positioning of supplies capability Propulsion Attitude control and orbit GN&C, attitude control and orbit maintenance during untended maintenance during crew-tended periods periods preserves fuel on habitat Thermal Passive thermal control during Active thermal control during crew- Control both crewed and untended periods tended periods with inter-module ventilation and habitat passive thermal control Table 3: Orion can provide supporting functions which reduce the cost and complexity of a cislunar habitat.

3.2 Habitat Module Halo orbit using the Habitat Support Vehicle’s The initial elements to arrive in cislunar space Solar Electric Propulsion (SEP). The integrated are the Habitat Module (Figure 4) and Habitat Habitat Support Vehicle/Habitat Module form Support Vehicle (Figure 5). They are launched the initial configuration of the DSTH. together into LEO by a dedicated commercial The Habitat Module provides the crew of Orion launch vehicle and then spiral out to an EM-L2 with additional living space for the initial set of

Proving Ground missions. It supports a crew of 4 astronauts for mission durations up to 60 days. There are four collapsible sleeping stations with integrated radiation protection which also provide personal space, critical for crew health during long duration missions. There are volumes for the crew to congregate to plan activities or relax. The exercise equipment in the habitat expands upon the equipment contained within Orion to allow for a wider variety of exercises helping keep the crew fit and healthy. To maximize the habitable volume for the crew, the Habitat Module features a hybrid pallet-based system with accommodations for traditional rack- based interfaces derived from ISS. In addition to enhancing the crew accommodations, the

Habitat Module has several reconfigurable Figure 4. The Habitat Module provides additional work areas and features that can be changed volume for the crew, enabling long duration between missions to meet mission specific missions. needs. 3.3 Habitat Support Vehicle The habitat has science stations that can be The Habitat Support Vehicle provides the reconfigured to meet the need of each Habitat Module with all of the services mission. It also features advanced in-space required to safely operate in cislunar space for manufacturing capabilities that allows new Phase 1 missions. It provides the primary equipment to be made from obsolete source of power during crewed and uncrewed equipment using the additive manufacturing periods through the use of solar arrays. The system and recycler. Habitat Support Vehicle also provides breathable gases (oxygen and nitrogen) to the DSTH throughout the Phase 1 missions and has the capability to have its gases recharged by visiting logistics vehicles. It is the propulsive stage that delivers the DSTH to cislunar space, provides station keeping, and also allows the DSTH to move between various cislunar orbits such as Earth-Moon libration point orbits and Distant Retrograde Orbits (DRO). The Habitat Support Vehicle is designed to operate autonomously for long periods of time when astronauts are not present and to allow Orion to control the DSTH when astronauts are present.

advanced suit port technology for Mars surface missions.

Figure 5. HABITAT SUPPORT VEHICLE: The HABITAT SUPPORT VEHICLE provides the Habitat Module with all of the services required to safely Figure 6. EVA Module: The EVA Module allows operate in cislunar space for Phase 1 missions. the crew to collect samples from asteroids, service vehicles or other objects that can visit or 3.4 EVA Module be visited by the DSTH. The EVA Module allows the crew to exit the DSTH to collect samples from an asteroid 3.5 Cargo and Logistics Pod during the Asteroid Redirect Crew Mission (see Each launch of an Orion on a Space Launch description below), service vehicles or other System (SLS) launch vehicle can support the co- objects that can visit or be visited by the DSTH. manifesting of an additional payload. This The EVA Module can also serve as a means to allows for launching a minimum of about 3,000 test future EVA equipment to be used at Mars kg of pressurized cargo to the DSTH to support in the relative safety of Earth’s neighborhood. the mission. A commercial or internationally- Including an EVA Module in the PG provided cargo pod (Figure 7), with a similar architecture satisfies many key objectives structural shell to the Habitat Module, is the needed prior to getting to Mars. co-manifest payload for most Orion flights. The pod is a simple logistics module that relies on The EVA Module consists of an equipment bay Orion to carry it to the DSTH (through a process for storage and maintenance of space suits and called a transposition maneuver, similar to the an airlock that allows astronauts to access the way the Apollo command module extracted outside of the DSTH without depressurizing the the Lunar Module from the Saturn V upper entire habitat (Figure 6). The equipment bay is stage). This means the pod does not require its a pressure vessel with two International own power and propulsion. The pod also Docking System Standard compliant axial provides additional pressurized volume when docking ports. It stores EVA maintenance docked (about 50 m3), as well as a means of equipment, tools and suits, and adds to crew trash disposal. living quarters. The airlock is used for depressurization/repressurization allowing for crew ingress/egress during EVAs. To minimize mass and provide efficient launch packaging, the EVA Module uses an inflatable airlock that is deployed after launch. The EVA Module may be pre-configured to provide the ability to test

The Phase I missions accomplish many of the proving ground objectives while exploring cislunar space. Astronauts will complete one mission per year, lasting 30-60 days. Below is a description of each Phase 1 mission.

EM-1 will be the first flight of the combined SLS/Orion vehicle stack. The uncrewed test will place the Orion spacecraft in a Distant

Figure 7. The Cargo and Logistics Pod carries Retrograde Orbit for about 25 days before provisions and equipment returning to Earth. The mission will build upon the EFT-1 test flight launched in 2014 [4] to Mission Set check out various systems and demonstrate The Space Launch System (SLS) and Orion will the heat shield at lunar return velocity prior to open crewed access to cislunar space in the the first launch of astronauts in Orion during early 2020s. The SLS can deliver the Orion EM-2. vehicle and a co-manifested cargo vehicle to a lunar transfer orbit, and Orion performs the Element Delivery Mission (EDM) - 1 delivers maneuvers to place itself and the co- the Habitat Module and the Habitat Support manifested cargo in the desired destination Vehicle to LEO. The Habitat Support Vehicle orbit near the Moon. The Proving Ground will use its high power SEP propulsion systems missions progressively increase capability and to slowly spiral out from LEO to the destination duration to evolve human exploration cislunar orbit beyond the lunar farside in time capabilities with the objective of being ready to for astronauts to visit on the next flight (Figure leave the Earth-Moon system. The Proving 8). By doing so it will demonstrate the ability to Ground Objectives are grouped into three move massive payloads out of Earth’s gravity general categories: transportation, working in well, a key capability for a human journey to space, and staying healthy. As the missions Mars. progress, additional equipment and modules will be integrated into the DSTH to allow the EM-2 will be the first flight of astronauts on crews to pursue more ambitious objectives. By Orion. They will fly Orion to the DSTH located the end of the test campaign the crew will be in a cislunar orbit over the lunar far side. EM-2 ready to journey to the vicinity of Mars. As the will be the first flight of the upgraded SLS Block Proving Ground Objectives are being 1B, allowing it and subsequent flights to co- accomplished, the crew will also perform manifest a cargo module that will provide the valuable science missions, so each mission’s crew with extra supplies which allow the crew multiple concurrent objectives maximize the to stay 30 days at the habitat. Counting transit value of each mission. The mission architecture time in Orion between Earth and the Moon, is depicted in Figure 12. the total mission duration is 45-50 days, during which the four-person crew will spend almost Phase 1 Cislunar Exploration Missions (EM-1 as many crew-days in deep space as the entire through EM-6) Apollo program did. The astronauts will spend much of their time outfitting the DSTH with additional equipment brought by the cargo

pod, potentially including an externally telescope in the farside quiet zone.[ 6 , 7 ]A mounted robotic arm that can be used to communications relay to the farside is an reposition later elements as they arrive. On the enabling capability to begin to address these first crew stay at the DSTH, simple exploration science priorities. During most of the year the experiments can begin, such as measuring how DSTH would serve as a relay to operators on quickly food and medications break down in Earth. When the DSTH is occupied, astronauts the radiation environment, and how may directly control lunar rovers as practice for populations of microbes evolve on a deep similar operations from Mars orbit [8]. Small space habitat that is occupied intermittently – robotic lunar landers, rovers, and surface an issue important for planetary protection at experiments would be launched separately Mars. from the astronauts and may be provided by international partners or commercial entities.

EM-4 will carry advanced life support equipment including a water recycling system that will reduce the amount of water that needs to be flown from Earth. This makes it possible for astronauts to begin to stay longer durations at the DSTH.

EM-5 is a science opportunity for astronauts to operate sample collection rovers on the lunar surface in near real time from the DSTH. The Figure 8. On EDM-1, the habitat module and crew can guide rovers to collect samples from habitat support vehicle are delivered to LEO and multiple locations and place them into a begin a 2-year journey to an L2 halo orbit near canister on an ascent vehicle, which will launch the Moon using electric propulsion. and delivered the samples to the DSTH for return to Earth. Variations on the human- EM-3 enhances the communications assisted sample return concept have been capabilities of the DSTH with the addition of a studied by JPL9 and by ESA/LPI10 in sufficient laser communications terminal. The advanced detail to identify landing sites and even communications capability allows astronauts individual boulders to sample. to operate lunar rovers on the far side of the Moon in near real time. The L2 Halo orbit is EM-6 adds an airlock to the DSTH to support selected as the initial location for the DSTH the Asteroid Redirect Mission (ARM) (Figure 9, because from this orbit the spacecraft can Figure 10). The EVA module enables astronauts provide continuous communications coverage to perform multiple EVAs on a subsequent to the far side of the Moon, either for direct mission to explore and experiment with a astronaut control or for relay to Earth.[ 5 ] boulder retrieved from an asteroid by a robotic Recent decadal surveys in planetary science spacecraft. The airlock will also be used to test and astrophysics have identified the farside of advanced planetary EVA capabilities such as the Moon as a priority for understanding the new space suits in preparation for future impact history of the inner solar system, and missions to Mars. for probing the early Universe with a radio

EDM-2 is a robotic flight that delivers an advanced habitat and habitat support vehicle to the DRO location of the DSTH. These new elements are classified as advanced because they are an evolution of the earlier Phase 1 elements, incorporating all of the lessons learned from previous missions. The advanced habitat will contain a Mars-class regenerative life support system and incorporate appropriate radiation shielding for months- Figure 10. On EM-6, astronauts use the DSTH to long deep space missions for example. The explore the asteroid boulder brought back to advanced habitat support vehicle will cislunar space by the Asteroid Redirect Robotic Vehicle. incorporate higher power generation and a deep space propulsion system capable of Phase 2 Deep Space Shakedown Missions (EM- bringing astronauts on long transit missions. 7 though EM-9) The addition of these elements will allow for longer duration missions and for the Orion With the Phase 1 objectives complete, DSTH system to leave the Earth-Moon system astronauts will be ready to push further into on 120-day and longer shakedown missions in space, on longer missions. The primary focus of preparation for missions to Mars orbit. the Phase 2 missions is to incorporate all of the

lessons learned from Phase 1 and begin to simulate longer missions with complexity similar to a Mars transit.

EM-7 is the first crewed mission to the expanded DSTH. All of the advanced elements have arrived and astronauts will spend 120 days onboard, checking out systems and proving the long duration reliability of the life support system. EM-7 will address critical science objectives that will help us understand when and how the first galaxies came into Figure 9. The DSTH, Orion, and all Phase 1 existence. We can best observe the epoch elements. between the end of the Big Bang and the ignition of the first stars nearly a billion years later in radio waves produced or absorbed by neutral hydrogen at a 21-cm wavelength. However, this ancient signal has been deeply redshifted to very low frequencies below 100 MHz. Faint signals at these frequencies can only be observed on the far side of the Moon, where they are shielded from terrestrial radio noise created by artificial sources and the

Earth’s ionosphere. Astronauts will tele- light time delays (communications) of up to operate a rover to unroll a radio telescope 200 seconds. Asteroid SG344 is a potential consisting of receivers imprinted on polyimide asteroid for this mission. It is roughly 20-100 m film over hundreds of meters on the lunar in diameter and the transfer to it will take 131 surface [11]. days. Once there, astronauts will spend 90 days exploring and studying the object. Figure EM-8 is the second Phase 2 mission where 11 is an illustration of the asteroid visit. Unlike astronauts will spend 210 days on a low energy the Asteroid Redirect Mission where only a transfer from a DRO back to an EM-L2 Halo small sample of an asteroid is returned, orbit. A conventional transfer between these astronauts will have access to an entire two orbits would normally take a matter of asteroid, allowing them to take multiple days, but would require a substantial use of samples of heterogeneous locations. The crew propellant. A low energy transfer is possible will also practice excursions to and working on between the two orbits. This transfer requires low gravity bodies. These lessons learned can only a delta-v of about 40 m/sec and takes be applied to a mission to the moons of Mars nearly 120 days to accomplish. With crew on [12]. EM-9 will require astronauts to use all of board, this mission will be the furthest from the deep space operations, technology, and Earth astronauts have ever traveled, nearly 4 protocols developed during Phase 1 and 2 in an times further than the previous Phase 1 environment analogous to a Mars transit. missions. Astronauts will now have to truly operate under Mars transit like conditions. During the 120 days in transit, few abort opportunities exist, requiring the crew to operate more autonomously.

EM-9 is the culmination of the proving ground campaign. It is the final shakedown mission that will prove out all remaining flight test objectives and once completed, astronauts will be ready for a round trip to Mars (Figure 11). Figure 11. A year-long mission to an asteroid in This mission is a year-long mission to visit a its native orbit, called the shakedown cruise, near Earth asteroid in its native orbit. It will allow astronauts to test Mars class systems and operations in a simulated Mars transit. take a crew of four nearly 30,000,000 km from

Earth where they will experience round trip

Figure 12. The Lockheed Martin proving ground architecture builds upon increasingly more challenging missions, meets NASA’s flight test objectives for Mars missions, and addresses key science goals.

Conclusions Orion and SLS will enable the exploration of To prepare for a human mission to Mars, NASA cislunar space, deep space, and Mars. Along has defined a set of flight test objectives to with Orion and SLS, the elements of the complete in the next Proving Ground phase of Lockheed Martin Deep Space Transit Habitat human space exploration. These objectives allow NASA to meet the flight test objectives, address the different challenges of the deep and are prototype Mars mission systems. The space environment, including development of proposed set of proving ground missions start required technologies, the ability of humans to with simple, shorter duration objectives and work in space, and the limits of human then expand the envelope in duration and performance. The objectives are areas that complexity as the missions proceed. The must be understood and proven before Proving Ground will demonstrate living and venturing to Mars. The ideal location for a working in deep space, completing the Mars proving ground is the space in the vicinity knowledge required to design and execute a of Earth’s moon, cislunar space. It provides human mission to Mars. many of the hazards found in deep space and near Mars, while still being days, not months, from the safety of Earth.

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