Ben Donahue

The Boeing Company · Exploration Launch Systems Division

After the conclusion of the Apollo program in 1972, two fully functional Saturn V launch vehicles and one fully functional Saturn 1B remained. The main reasons for the termination of the Apollo missions to the Moon has been reported to be due to 1) the large cost, 2) a change in the technical direction from exploration of space to exploring low Ear...

This paper explores the capability of the new NASA Space Launch System to deliver an inflatable Zeppelin type spacecraft and science package to the atmosphere of Titan. The Balloon and spacecraft would ride the stratified and dynamic wind currents of Titan. Having the capability to vary its altitude, this system would over many months or potentiall...

To reduce mission complexity, a new Mars Sample Return concept is presented. Specifically, this paper explores the capability of the NASA Space Launch System (SLS) to deliver an "All-in-one" lander system that features a robust Mars Ascent Vehicle (MAV); capable of boosting an Earth Return Capsule from the surface, beyond Mars Escape velocity to a...

Space-based astronomical telescopes are in great demand typically observing objects beyond the solar system. Therefore, synaptic observations of solar system bodies are limited by the availability of telescope time and resolution. The need for a high-resolution, multi-wavelength space telescope for dedicated planetary science is especially acute wi...

For Mars, it is expected that multiple sample return missions will be necessary in support of both science and human exploration missions. The first Mars sample return (MSR) campaign is currently underway with the Mars Perseverance rover creating rock cores to be returned to Earth. NASA's current architecture for MSR is under external review, large...

This paper explores the capability of the NASA Space Launch System (SLS) to deliver a lander with a space telescope to the north pole of Phobos. Space-based astronomical telescopes are in great demand typically observing objects beyond the solar system. Therefore, synaptic observations of solar system bodies are limited by the availability of teles...

This paper explores the capability of the new NASA Space Launch System to deliver an inflatable Zeppelin type spacecraft and science package to the atmosphere of Titan. The Balloon and spacecraft would ride the stratified and dynamic wind currents of Titan. Having the capability to vary its altitude, this system would over many months or potentiall...

The Space Launch System (SLS) is NASA's new heavy lift launch vehicle which successfully flew for the first time in November 2022. The SLS can inject two Flagship class outer-planet spacecraft, and a Deep Space Maneuver stage, together totaling 22.0 metric tons, on a trajectory that reaches Uranus in 16.0 years, and Neptune in 18.0 years. Both spac...

This paper explores the design of Crewed Mars Ascent Vehicles (MAV) utilizing two propellant combinations. The first involves Mars atmospheric In-situ sourced oxygen with Earth supplied methane (CH4) fuel, and the second, Chlorine Pentafluoride and Hydrazine. The latter is a “Mars storable” propellant; it is not subject to boiloff while on the surf...

The NASA Space Launch System (SLS) capabilities for launching heavy payloads with high injection velocities will enable a variety of exploration missions that would not otherwise be considered. Included are overviews of six new missions: Interstellar Probe, missions to Uranus and Neptune, Phobos/Deimos sample return, Europa lander and a dual deep s...

The NASA Space Launch System (SLS) capabilities for launching heavy payloads with high injection velocities will enable a variety of exploration missions that would not otherwise be considered. In this paper, the Interstellar Probe mission is described and an enhanced version of the NASA SLS is presented.

View Video Presentation: https://doi.org/10.2514/6.2022-4375.vid In 2033, a ‘once every 15 years’ Earth Mars alignment occurs, allowing a free return trajectory, i.e. no propulsive maneuver is required at Mars to effect a return to Earth. NASA’s new Space Launch System (SLS), can launch the large propulsive stages and crew habitat necessary to this...

View Video Presentation: https://doi.org/10.2514/6.2022-4371.vid Traveling far beyond the Sun’s sphere of influence, the Interstellar Probe (IP) will be launched to an extreme velocity to reach the interstellar medium within 15 years. Flying the farthest and the fastest, the IP would venture into the space between our Solar system and neighboring s...

A combined Phobos and Deimos sample return mission spacecraft concept is presented as a mission that would fly as a secondary, co-manifested payload on the NASA Space Launch System launcher. The spacecraft separates from the SLS primary payload (the Orion capsule) after the Trans-Lunar injection burn. After transfer to Mars parking orbit the spacec...

A Mars polar lander, specifically designed to land on the north polar ice cap, is presented. The Mars north pole ice cap is about 1000 km in diameter during the northern summer, and contains about 1.5 km3 of water ice. Mars polar water ice is a resource from which both crew consumables and rocket propellant can be derived. This large, SLS launched,...

A 2033 Mars Flyby mission is described and the characteristics of the trajectory, in-space stages, crew habitat and Earth Entry Capsule are described. An Earth Mars alignment, that allows for a free return trajectory at Mars, occurs every 15 years. This means that no propulsive maneuver is required at Mars to affect a return to Earth. The vehicle s...

A combined Phobos and Deimos sample return mission spacecraft concept is presented as a mission that would fly as a secondary, co-manifested payload on the NASA Space Launch System (SLS) launcher in the late 2020s. The spacecraft separates from the SLS primary payload (the Orion crew capsule) after the Trans-Lunar injection velocity burn. The space...

Traveling far beyond the Sun's sphere of influence, the Interstellar Probe (IP) will be launched to an extreme velocity to reach the interstellar medium within 15 years. Flying the farthest and the fastest, the IP would venture into the space between our Solar system and neighbouring stars, on a 50-year mission of discovery. The IP is to be launche...

Every 15 years, an Earth Mars alignment occurs that allows for a free return trajectory at Mars, which means no propulsive maneuver is required at Mars to effect an return to Earth. The vehicle swings by Mars and is thereafter on a path to intercept the Earth. This greatly reduces the energy requirements for the Earth-Mars in space stages, and allo...

Space architects and mission planners have long managed the compromise of maximizing the capability of a space asset while staying within the lift capability and payload bay size of available launch vehicles. Alternate approaches include breaking up a space asset into multiple smaller elements to be launched separately or keeping the asset as one l...

A Mars Polar Lander, specifically designed to land on the north polar ice cap, is presented. The Mars north pole ice cap is about 1000 km in diameter during the northern summer, and contains about 1.5 km3 of water ice. Mars polar water ice is a resource from which both rocket propellant and crew consumables can be derived. Demonstration of the tech...

The NASA Space Launch System (SLS) Block 1 configuration is presently at NASA KSC preparing for its first launch later this year or early in 2022. Earlier this year the SLS Core Stage finished its Green Run, full duration test at NASA Stennis Space Center. In this report, several beyond Earth orbit exploration missions, enabled by the SLS, are pres...

View Video Presentation: https://doi.org/10.2514/6.2021-3264.vid In 2033, a ‘once every 15 years’ Earth Mars alignment occurs, allowing a free return trajectory, i.e. no propulsive maneuver is required at Mars to effect an return to Earth. NASA’s new Space Launch System (SLS), can launch the large propulsive stages and crew habitat necessary to thi...

View Video Presentation: https://doi.org/10.2514/6.2021-3265.vid A Mars Polar Lander, specifically designed to land on the north polar ice cap, is presented. The Mars north pole ice cap is about 1000 km in diameter during the northern summer, and contains about 1.5 km3 of water ice. Mars polar water ice is a resource from which both rocket propella...

View Video Presentation: https://doi.org/10.2514/6.2021-3266.vid Future Missions for the NASA Space Launch System Conceptual overviews of five new Space Exploration missions, enabled by launch on the NASA Space Launch System (SLS) are given. Descriptions of these new missions will serve to highlight the robust capabilities provided by SLS and show...

In 2033, a ‘once every 15 years’ Earth Mars alignment occurs, allowing a free return trajectory, i.e. no propulsive maneuver is required at Mars to effect an return to Earth. NASA’s new Space Launch System (SLS), can launch the large propulsive stages and crew habitat necessary to this exciting mission. The flyby would serve as a precursor to later...

The NASA Space Launch System (SLS) Core Stage has finished its Green Run, full duration test at NASA Stennis Space Center. In this report, the SLS development status and its launch capabilities are discussed, and the new optimized Exploration Upper Stage, currently in development, which will optimize the SLS Core and Booster Stages, is presented. T...

The NASA Space Launch System (SLS) Core Stage is presently in test at NASA’s Stennis Space Center. The Core Stage “Green Run” test will demonstrate systems readiness for flight, including a full duration engine operation. The SLS Block 1 configuration is progressing toward a 2021 first flight, launching an uncrewed Orion capsule to the Moon. In thi...

A human mission to the moon and Mars is the stated space exploration goal of the United States and the international community. To achieve these goals, NASA is developing the Space Launch System (SLS) and the Orion crew capsule as key elements in the architecture for missions to the moon and Mars. As part of the SLS Booster Obsolescence and Life Ex...

The NASA Space Launch Systems (SLS) outstanding capabilities for launching heavy, large diameter payloads will enable robust lunar architectures where the Near Rectilinear Halo Orbit (NRHO) is used as an aggregation node for lander and Orion elements. SLS capabilities and production status is discussed, as is the new large Exploration Upper Stage,...

The NASA Space Launch System (SLS) will provide a game-changing capability for the exploration of other worlds. The Initial Block 1 configuration is scheduled for launch in 2020; by 2024 the SLS will evolve into the more powerful Block 1B configuration that will use the new Exploration Upper Stage (EUS). The EUS optimizes the SLS Core and Booster S...

The NASA Space Launch System (SLS) will provide a game-changing capability for the exploration of other worlds, beginning with the Block 1 configuration that utilizes the Interim Cryogenic Propulsion Stage (ICPS). In 2023, the new NASA Exploration Upper Stage (EUS) will evolve the SLS to a significantly higher performance level. The EUS optimizes t...

Presented at the NASA Marshall Space Flight Center In-Space chemical Propulsion Technical Interchange Meeting, 29-30 August 2018 Huntsville, Alabama, USA, this presentation present NASA Space Launch System (SLS) launched, Large Crewed Lunar Lander Design concepts. A brief review is give on the 1969 Grumman Apollo Lunar Excursion Module (LEM) and th...

The SLS Launch Vehicle with Orion will provide the capability of achieving human exploration, operations and science objectives for a variety of Beyond Earth Orbit (BEO) missions, including Crewed Cis-lunar missions in the 2020s and Crewed Mars missions in the 2030s. The SLS program is in the production and test phase. There are three SLS configura...

A brief graphical overview is given of technology opportunities and applicability to Mars Crew Landers, Mars Transfer Vehicles and In-situ propellant derived Mars Ascent Vehicles (MAV). A large Mars surface propellant supplied Crewed MAV is presented and relevant technologies associated with the vehicle and its mission are outlined.

In this report a summary is given of the capabilities of the SLS, strategies for exploration missions are presented, and descriptions of SLS based payload elements are given. The SLS program is making progress toward delivering a new capability for Beyond Earth Orbit exploration, with a first flight scheduled for late 2018.

Presented at the ESA/ESTEC International Symposium on the Moon, 15 December 2015, Noordwijk, the Netherlands

The Space Launch System (SLS) Program is making progress toward delivering a new capability for Beyond Earth Orbit (BEO) exploration. Developed with the goals of safety, affordability and sustainability in mind, SLS will start with 10% more thrust than the Saturn V that launched astronauts to the Moon 40 years ago. From there it will evolve into th...

The Space Launch System (SLS) is the most powerful rocket ever built and provides a critical heavy-lift launch capability enabling diverse deep space missions.

Conceptual design of an 18 Kilowatt Solar Electric Propulsion (SEP) spacecraft for a Phobos sample return mission. Done by the Boeing Advanced Concept Teams at Huntington Beach, CA and Huntsville, AL. Presented at the Lunar Planetary Institute, June 12, 2012 during the 'Concepts and Approaches for Mars Exploration' Workshop, Houston TX

Presenting a 20kW Solar Electric Propulsion (SEP) transfer system/Mars spacecraft for a Phobos sample return mission. A E-M trajectory is described and the benefits of SEP for Mars is presented; reductions in cost and reuse of systems are benefits.

Based from one of the Earth Moon Libration Points (EMLP), a Mars exploration campaign is described that features reusable Solar Electric Propulsion (SEP) stages. SEP Earth-Mars transfer stages using advanced array and high specific impulse (Isp) (1500-5000) electric thruster technology would be a viable option for exploration missions, especially t...

Lunar, Near Earth Object (NEO) and Mars missions in 2020-2040 are presented. An Earth Moon Lagrange Point (L Point) station serves as a transfer stage return and refueling node. An initial reusable lander lunar mission forms the first "beyond LEO" mission for the SLS launcher. With this approach a "one SLS per crew sortie" lunar campain is possible...

This paper contains an investigation of an Earth Moon Libration Point 1 (EML1) base station as a staging node for Human exploration of the Moon, Near Earth Objects (NEO), Phobos and Mars. Based from EML1, an early 2020s Lunar exploration campaign that features a reusable lander for sorties between EML1 and the Lunar Surface is described. The strate...

The objective of this analysis is to leverage the unique capabilities of advanced Solar Electric Propulsion (SEP) technology and configure a flight strategy for a crewed Mars Phobos mission that plays to the strengths of this vehicle type while minimizing its weaknesses. SEP Earth-Mars (E-M) transfer stages using advanced array technology and high...

This paper describes a sample return mission to Titan, the largest moon of Saturn, and the only moon known to have a dense atmosphere and the only object, other than Earth, for evidence of stable bodies of surface liquid have been found. A 6 year direct trajectory is described that features aerocapture at Titan. Titan's nitrogen atmosphere is 4 tim...

This paper describes Heavy Lift Launch Vehicle concepts that are based on existing propulsion systems. Both In-Line and Side mount configurations for Crew, Crew plus cargo and Cargo only missions are illustrated. Payload data includes launches to due East LEO, ISS, Trans-Lunar Injection (TLI) and the Earth-Sun L2 point. Engine options include SSME...

Future Planetary outposts may require significant amounts of electrical power to support exploration science and life support. Particularly high levels of power would be required for: - Lunar and Mars bases, - Adjacent or stand alone surface in-situ propel production & storage facilities - Locations where Solar Flux is very low A variety of NASA Lu...

This paper describes two space science missions that could take advantage of the proposed Ares-V heavy lift launch vehicle; the first, a Titan sample return mission, would leverage the Ares-V’s injected mass capability and the second, a new large space telescope mission, would leverage its 8-10 meter shroud diameter. A direct trajectory sample retu...

In 2008 the Boeing company conducted a six month design study for the NASA Johnson Space Center as part of the of the Altair Lunar lander concept desi gn effort. Information presented here is taken from Boeings final report presented to NASA in October 2008 in Houston to the Altair program office. This report contains a summary of one aspect of tha...

The NASA Ares V Heavy Lift booster, now in conceptual development, has a primary mission to launch the 45 metric ton NASA Altair Lander to Low Earth Orbit. The Ares V provides the robust payload-to-orbit capabilities necessary for Constellation missions to enable exploration of the Lunar surface. The Ares V's large payload bay will accommodate the...

A new generation of lunar lander is to be the reference payload for the NASA Ares-V heavy-lift launch vehicle, still in conceptual development. The surface-payload capability of the lander is primarily a function of propulsion choice, staging method, and configuration choice. A variety of staging methodologies are investigated, and the benefits and...

Future NASA and commercial Lunar missions will require innovative spacecraft configurations incorporating reliable, sustainable propulsion, propellant storage, power and crew life support technologies that can evolve into long duration, partially autonomous systems that can be used to emplace and sustain the massive supplies required for a permanen...

The development of nuclear and advanced propulsion technologies to be used in atmospheric mining of the outer planets is discussed. The design of the Nuclear Thermal Rocket (NTR) Element Enviroment Simulator, or NTREES has been developed at NASA Marshall to evaluate the characteristics of NTR engine fuel element materials and geometries in represen...

Systems analyses were performed for a Titan Explorer Mission characterized by Earth-Saturn transfer stages using solar electric power generation and propulsion systems for primary interplanetary propulsion, as well as chemical propulsion for capture at Titan. An examination of a range of system factors was performed to determine their effect on the...

The objective of this study is to generate a set of cargo and crew vehicles that together would satisfy Human Mars exploration goals, and serve as an evaluation yardstick for further comparisons. A Mars architecture is defined, a 8 year cycle of missions covering the years 2031-2038 is laid out, payloads are selected, primary operational and perfor...

Conceptual in-space transfer stages, including those using solar electric propulsion and chemical propulsion with aerobraking or aerocapture assist at Mars, were evaluated. Roundtrip Mars sample return mission vehicles were analyzed to determine how technology selections influence payload delivery capability. Results show how specific engine, thrus...

Performance figures are presented for reusable, winged rocket stages launched from several large transport aircraft, including the Boeing 747, the Russian Anotonov An-226, a large supersonic aircraft comparable to the XB-70 aircraft, which achieved Mach 3.1 flight with conventional turbojet propulsion in 1964, and a Mach 6 conceptual aircraft based...

Contents include the following: Review of analysis goal. Analysis introduction: summary approach and goal assumptions. System analysis: propulsion technologies investigated. Analysis results: mission and performance analysis. Cost analysis. Comparison of propulsion technologies. Conclusion.

A high Mach number, high altitude aircraft, utilized as a launch platform for a reusable air-launched rocket, ca