A Revolutionary Lunar Space Transportation System Architecture Using Extraterrestrial LOX-Augmented NTR Propulsion

Borowski, Stanley K.; Corban, Robert R.; Culver, Donald W.; Bulman, Melvin; Mcilwain, Mel C.

doi:10.2514/6.1994-3343

Cited by 27 publications

(11 citation statements)

References 5 publications

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“…The LOx provides an augmentation factor of up to 4:1 (3:1 in this example, from Ref. [18][19][20] and a mission average Isp of 821 seconds, but reactor and structural mass lower payload fractions to negative margin with the selected 120 klb GLOW and take-off T/W of 1.3. Scale favors rocketry, so a positive margin solution may exist but this study was restricted to a known reactor architecture.…”

Section: A Earth To Orbitmentioning

confidence: 99%

The Nuclear Thermal Turbo Rocket - A Conceptual High-Performance Earth-to-Orbit Propulsion System

Bucknell¹

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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A new propulsion concept called the Nuclear Thermal Turbo Rocket (NTTR) is proposed for Earth to Orbit applications. The NTTR utilizes a nuclear fission reactor to thermally heat hydrogen propellant into a rocket plenum. The rocket nozzles are located at the tips of a variable pitch thrust fan connected to the plenum by passages in the fan blades, and each nozzle is a linear aerospike on the trailing edge of the blade.The thrust fan is located in a duct such that the heated hydrogen propellant is combusted with ambientsourced oxygen to augment the rocket thrust. The fan is of variable pitch to provide maximum thrust for varying inlet velocity. The duct has a variable geometry inlet, able to provide appropriate mass flow and compression to the combustor throughout the trajectory, and a variable geometry outlet to provide appropriate nozzle area for maximum thrust. The rocket nozzles act as propellant injectors during the airbreathing portion and pure rockets during low atmospheric density portions, with the NTTR utilizing a single gas path from launch to orbital velocity. The propulsion concept is of high performance and is able to transport more than 50% mass fraction in a Single Stage to Orbit (SSTO) via an air-breathing rocket trajectory with intended complete reusability. Payload fractions of up to 19% are predicted (inert mass includes reactor radiation shielding) due to a mission average Specific Impulse (Isp) of 1,662 seconds. Nomenclature m = mass flow η c = compressor isentropic efficiency c p = constant pressure specific heat γ = ratio of specific heats T = absolute temperature P = absolute pressure M = Mach number MW th = Megawatt, thermal M f = Final Mass PR = Pressure Ratio (Outlet/Inlet) ΔV = change in velocity Φ = equivalence ratio k = reactivity coefficient Ψ = absolute temperature ratio β = oblique shock angle  = flow deflection angle

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Section: A Earth To Orbitmentioning

confidence: 99%

The Nuclear Thermal Turbo Rocket - A Conceptual High-Performance Earth-to-Orbit Propulsion System

Bucknell¹

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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“…There it would be lowered to a "flat-bed" surface vehicle (see Figure 11) and transported to the lunar base air lock for docking and passenger unloading. Besides high energy lunar missions, the LANTR can also dramatically improve space transportation system performance wherever extraterrestrial sources of LOX and L~ can be acquired such as the Martian system, main-belt asteroids and the Galilean satellites Europa, Ganymede, and Callisto (Borowski et al 1994). This paper describes operational characteristics and performance benefits of a versatile new engine concept-the LOX-augmented NTR.…”

Section: Ton Passenger Module Both Ways Resuablementioning

confidence: 99%

“…concept described here leverages the high Isp capability of the N1R and the availability of LUNOX and provides the basis for a revolutionary LTS architecture (Borowski et al, 1994) possessing a variety of engine, vehicle and mission benefits. The implementation strategy for this architecture uses expendable "all LH2 .. NTR systems initially to maximize the smface landed payload per mission while minimizing IMLEO requirements.…”

Section: Introductionmentioning

confidence: 99%

“…Downstream nozzle injection isolates the reactor core from oxygen damage provided the throat retains choked flow. This condition is satisfied using a "cascade" scramjet injector concept developed by Aerojet which controls oxygen addition and heat release proflles (via staged injection) to keep the flow supersonic (Borowski et al 1994). It also increases penetration, mixing and combustion of the oxygen injectant in the supersonic hydrogen flow while minimizing shock losses and high heat flux regions (hot spots), thereby maximizing engine performance and life.…”

Section: Introductionmentioning

confidence: 99%

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Human exploration and settlement of the moon using lunox-augmented NTR propulsion

Borowski¹,

Culver²,

Bulman³

1995

AIP Conference Proceedings

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An innovative trimodal nuclear thennal rocket (NTR) concept is described which combines conventional liquid hydrogen (LHJ-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOX)-augmented NTR (LANTR), this concept utilizes the large divergent section of the N1R nozzle as an "afterburner" into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LAN1R's choked sonic throat-"scramjet propulsion in reverse." By varying the oxygen-to-bydrogen mixture ratio (MR), the LANfR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (ldbf) NTR increases by -440%-from 3 to 13-while the lsp decreases by only -45%-from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that "big engine" perfonnance can be obtained using smaller, more affordable, easier to test NTR engines. "Reoxidizing" the bipropellant LAN1R system in low lunar orbit (ILO) with high density "lunar-derived" LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class SbuttIe-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable "all LH 2 " NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid "commuter" shuttle capable of 36 to 24 hour "one way" trips to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

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“…Over the next five years, with its industry partner Aerojet, GRC quantified the operational characteristics and performance potential of an enhanced NTR -known as the LOX-Augmented NTR (LANTR) -in an evolutionary LTS architecture [10]. The LANTR concept adds an oxygen (O 2 ) "afterburner" nozzle and feed system to the basic NTR allowing O 2 injection and supersonic combustion in the engine's hot H 2 exhaust downstream of the nozzle throat.…”

Section: Introductionmentioning

confidence: 99%

The Nuclear Thermal Propulsion Stage (NTPS): A Key Space Asset for Human Exploration and Commercial Missions to the Moon

Borowski

McCurdy²,

Burke

2013

AIAA SPACE 2013 Conference and Exposition

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The nuclear thermal rocket (NTR) has frequently been discussed as a key space asset that can bridge the gap between a sustained human presence on the Moon and the eventual human exploration of Mars. Recently, a human mission to a near Earth asteroid (NEA) has also been included as a "deep space precursor" to an orbital mission of Mars before a landing is attempted. In his "post-Apollo" Integrated Space Program Plan (1970 -1990), Wernher von Braun, proposed a reusable NTPS to deliver cargo and crew to the Moon to establish a lunar base initially before sending human missions to Mars. The NTR was selected because it was a proven technology capable of generating both high thrust and high specific impulse (I sp ~900 s) -twice that of today's best chemical rockets. During the Rover and NERVA programs, twenty rocket reactors were designed, built and successfully ground tested. These tests demonstrated the (1) thrust levels; (2) high fuel temperatures; (3) sustained operation; (4) accumulated lifetime; and (5) restart capability needed for an affordable in-space transportation system. In NASA's Mars Design Reference Architecture (DRA) 5.0 study, the "Copernicus" crewed NTR Mars transfer vehicle used three 25 klb f "Pewee" engines -the smallest and highest performing engine tested in the Rover program. Smaller lunar transfer vehicles -consisting of a NTPS with three ~16.7 klb f "SNRE-class" engines, an in-line propellant tank, plus the payload -can be delivered to LEO using a 70 t to LEO upgraded SLS, and can support reusable cargo delivery and crewed lunar landing missions. The NTPS can play an important role in returning humans to the Moon to stay by providing an affordable in-space transportation system that can allow initial lunar outposts to evolve into settlements capable of supporting commercial activities. Over the next decade collaborative efforts between NASA and private industry could open up new exploration and commercial opportunities for both organizations. With efficient NTP, commercial habitation and crew delivery systems, a "mobile cislunar research station" can transport crews to small NEAs delivered to the E-ML2 point. Also possible are week-long "lunar tourism" missions that can carry passengers into lunar orbit for sightseeing (and plenty of picture taking), then return them to Earth orbit where they would re-enter and land using a small reusable lifting body based on NASA's HL-20 design. Mission descriptions, key vehicle features and operational characteristics are described and presented. NomenclatureE-ML2 = Earth-Moon L2 Lagrange point K = temperature (degrees Kelvin) klb f = thrust (1000's of pounds force) LEO = Low Earth Orbit (= 407 km circular) LOX / LH 2 = Liquid Oxygen / Liquid Hydrogen propellant NERVA = Nuclear Engine for Rocket Vehicle Applications SLS / HLV = Space Launch System / Heavy Lift Vehicle SNRE = Small Nuclear Rocket Engine t = metric ton (1 t = 1000 kg) ΔV = velocity change increment (km/s) ---

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A Revolutionary Lunar Space Transportation System Architecture Using Extraterrestrial LOX-Augmented NTR Propulsion

Cited by 27 publications

References 5 publications

The Nuclear Thermal Turbo Rocket - A Conceptual High-Performance Earth-to-Orbit Propulsion System

The Nuclear Thermal Turbo Rocket - A Conceptual High-Performance Earth-to-Orbit Propulsion System

Human exploration and settlement of the moon using lunox-augmented NTR propulsion

The Nuclear Thermal Propulsion Stage (NTPS): A Key Space Asset for Human Exploration and Commercial Missions to the Moon

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