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NASA’s nuclear thermal propulsion project

NASA’s nuclear thermal propulsion project

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AIAA SPACE Conference and Exposition, 2015

作者： Houts, Michael G. Mitchell, Doyce P. Kim, Tony Emrich, William J. Hickman, Robert R. Gerrish, Harold P. Doughty, Glen Belvin, Anthony Clement, Steven Borowski, Stanley K. Scott, John Power, Kevin P. NASA Marshall Space Flight Center MSFC AL35812 United States US Department of Energy WashingtonDC20585 United States US Department of Energy National Nuclear Security Adminstration Las VegasNV89193 United States NASA Glenn Research Center ClevelandOH44135 United States NASA Johnson Space Center HoustonTX77058 United States NASA Stennis Space Center MS39529 United States Technology Development and Transfer Office/ZP30 United States Propulsion Research and Technology Branch/ER24 United States Metal Joining and Processes Branch/EM32 United States Propulsion Systems Design and Integration Division/ER20 United States Propulsion and Research Technology Branch /ER24 United States Space and Defense Power Systems Department of Energy/NE75 United States /NNSA United States Propulsion and Controls Systems Analysis/86:124 United States Direct Energy Conversion /EP311 United States Engineering Test Directorate/EA61 United States

ISBN: (纸本)9781624103346

The fundamental capability of Nuclear Thermal propulsion (NTP) is game changing for space exploration. A first generation NTP systemcould provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance. The role of a first generation NTP in the development of advanced nuclear propulsion systems could be analogous to the role of the DC- 3 in the development of advanced aviation. Nuclear propulsion can be affordable and viable compared to other propulsion systems and must overcome a biased public fear due to hyperenvironmentalism and a false perception of radiation and explosion risk. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.

关键词： Nuclear propulsion

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A crewed mission to apophis using a hybrid Bimodal Nuclear Thermal Electric propulsion (BNTEP) system 50

A crewed mission to apophis using a hybrid Bimodal Nuclear T...

引用

50th AIAA/ASME/SAE/ASEE Joint propulsion Conference and exhibit 2014

作者： McCurdy, David R. Borowski, Stanley K. Burke, Laura M. Packard, Thomas W. NASA Glenn Research Center ClevelandOH44135 United States NASA Glenn Research Center ClevelandOH44135 United States NASA Glenn Research Center NASA/GRC Trajectory and Mission Analysis ClevelandOH44135 United States NASA Glenn Research Center LLC Trajectory and Mission Analysis ClevelandOH44135 United States LLC Glenn Research Center Propulsion and Controls Systems Analysis 3000 Aerospace Parkway Brook ParkOH44142 United States LTR Branch NTP Systems 21000 Brookpark Road MS 86-4 United States

ISBN: (数字)9781624103032

ISBN: (纸本)9781624103032

A BNTEP system is a dual propellant, hybrid propulsion concept that utilizes Bimodal Nuclear Thermal Rocket (BNTR) propulsion during high thrust operations, providing 10’s of kilo-Newtons of thrust per engine at a high specific impulse (Isp) of 900 s, and an Electric propulsion (EP) system during low thrust operations at even higher Isp of around 3000 s. Electrical power for the EP system is provided by the BNTR engines in combination with a Brayton Power Conversion (BPC) closed loop system, which can provide electrical power on the order of 100’s of kWe. High thrust BNTR operation uses liquid hydrogen (LH2) as reactor coolant propellant expelled out a nozzle, while low thrust EP uses high pressure xenon expelled by an electric grid. By utilizing an optimized combination of low and high thrust propulsion, significant mass savings over a conventional NTR vehicle can be realized. Low thrust mission events, such as midcourse corrections (MCC), tank settling burns, some reaction control system (RCS) burns, and even a small portion at the end of the departure burn can be performed with EP. Crewed and robotic deep space missions to a near Earth asteroid (NEA) are best suited for this hybrid propulsion approach. For these mission scenarios, the Earth return ΔV is typically small enough that EP alone is sufficient. A crewed mission to the NEA Apophis in the year 2028 with an expendable BNTEP transfer vehicle is presented. Assembly operations, launch element masses, and other key characteristics of the vehicle are described. A comparison with a conventional NTR vehicle performing the same mission is also provided. Finally, reusability of the BNTEP transfer vehicle is explored. © 2014, by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Propellants

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The nuclear cryogenic propulsion stage

The nuclear cryogenic propulsion stage

引用

AIAA SPACE 2014 Conference and Exposition

作者： Houts, Michael G. Kim, Tony Emrich, William J. Hickman, Robert R. Broadway, Jeramie W. Gerrish, Harold P. Doughty, Glen Belvin, Anthony Borowski, Stanley K. Scott, John Technology Development and Transfer Office/ZP30 United States Nuclear Cryogenic Propulsion Stage Technology Development and Transfer Office/ZP30 United States Propulsion Research and Technology Branch/ER24 United States Metal Joining and Processes Branch/EM32 United States Propulsion Systems Design and Integration Division/ER20 United States Space and Defense Power Systems Department of Energy/NE75 United States Propulsion and Controls Systems Analysis/86:12 United States NASA Marshall Space Flight Center MSFC AL 35812 United States US Department of Energy Washington DC 20585 United States NASA Glenn Research Center Cleveland OH 44135 United States NASA Johnson Space Center Houston TX 77058 United States

ISBN: (纸本)9781624102578

The fundamental capability of Nuclear Thermal propulsion (NTP) is game changing for space exploration. A first generation Nuclear Cryogenic propulsion Stage (NCPS) based on NTP could provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. Characteristics of fission and NTP indicate that useful first generation systems will provide a foundation for future systems with extremely high performance. The role of the NCPS in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation. Progress made under the NCPS project could help enable both advanced NTP and advanced Nuclear Electric propulsion (NEP). Nuclear propulsion can be affordable and viable compared to other propulsion systems and must overcome a biased public fear due to hyperenvironmentalism and a false perception of radiation and explosion risk.

关键词： Nuclear propulsion

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The nuclear cryogenic propulsion stage 50

The nuclear cryogenic propulsion stage

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50th AIAA/ASME/SAE/ASEE Joint propulsion Conference and exhibit 2014

作者： Houts, Michael G. Kim, Tony Emrich, William J. Hickman, Robert R. Broadway, Jeramie W. Gerrish, Harold P. Doughty, Glen Belvin, Anthony Borowski, Stanley K. Scott, John NASA Marshall Space Flight Center Technology Development and Transfer Office/ZP30 MSFCAL35812 United States NASA Marshall Space Flight Center Nuclear Cryogenic Propulsion Stage Technology Development and Transfer Office/ZP30 MSFCAL35812 United States NASA Marshall Space Flight Center Propulsion Research and Technology Branch/ER24 MSFCAL35812 United States NASA Marshall Space Flight Center Metal Joining and Processes Branch/EM32 MSFCAL35812 United States NASA Marshall Space Flight Center Propulsion Systems Design and Integration Division/ER20 MSFCAL35812 United States US Department of Energy Space and Defense Power Systems Department of Energy/NE75 WashingtonDC20585 United States NASA Glenn Research Center Propulsion and Controls Systems Analysis/86:124 ClevelandOH44135 United States NASA Johnson Space Center Direct Energy Conversion/EP311 HoustonTX77058 United States

ISBN: (数字)9781624103032

ISBN: (纸本)9781624103032

关键词： Space research

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Affordable development of a nuclear cryogenic propulsion stage

Affordable development of a nuclear cryogenic propulsion sta...

引用

AIAA SPACE Conference and Exposition 2012

作者： Houts, Michael G. Kim, Tony Emrich, William J. Hickman, Robert R. Broadway, Jeramie W. Gerrish, Harold P. Adams, Robert B. Bechtel, Ryan D. Borowski, Stanley K. George, Jeffrey A. NASA Marshall Space Flight Center MSFC Game Changing Technology Development Office/ZP31 AL 35812 United States NASA Marshall Space Flight Center MSFC Propulsion Research and Technology Branch/ER24 AL 35812 United States NASA Marshall Space Flight Center MSFC Metal Joining and Processes Branch/EM32 AL 35812 United States NASA Marshall Space Flight Center MSFC Propulsion Systems Design and Integration Division/ER20 AL 35812 United States NASA Marshall Space Flight Center MSFC Advanced Concepts Office/ED04 AL 35812 United States US Department of Energy Space and Defense Power Systems/NE75 Department of Energy Washington DC 20585 United States NASA Glenn Research Center Propulsion and Controls Systems Analysis/86:124 Cleveland OH 44135 United States NASA Johnson Space Center Propulsion and Power Division/AH3 Houston TX 77058 United States

ISBN: (纸本)9781600869402

The fundamental capability of Nuclear Thermal propulsion (NTP) is game changing for space exploration. A first generation Nuclear Cryogenic propulsion Stage (NCPS) based on NTP could provide high thrust at a specific impulse above 900 s, roughly double that of state of the art chemical engines. The foundation provided by development and utilization of a NCPS could enable development of extremely high performance systems. The role of the NCPS in the development of advanced nuclear propulsion systems could be analogous to the role of the DC-3 in the development of advanced aviation. Progress made under the NCPS project could help enable both advanced NTP and advanced Nuclear Electric propulsion (NEP).

关键词： Space research

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HERRO: A science-oriented strategy for crewed missions beyond LEO

HERRO: A science-oriented strategy for crewed missions beyon...

引用

作者： Schmidt, George R. Landis, Geoffrey A. Oleson, Steven R. Borowski, Stanley K. Krasowski, Michael J. NASA Glenn Research Center Cleveland OH 44135 United States Research and Technology MS 3-5 United States Photovoltaics and Power Technologies Branch MS 302-1 United States Systems Analysis Branch MS 105-3 United States Propulsion and Controls Systems Branch MS 86-4 United States Optical Instrumentation and NDE Branch MS 77 United States

ISBN: (纸本)9781600867392

This paper presents an exploration strategy for human missions beyond Low Earth Orbit (LEO) and the Moon that combines the best features of human and robotic spaceflight. This "Human Exploration using Real-time Robotic Operations" (HERRO) strategy refrains from placing humans on the surfaces of the Moon and Mars in the near-term. Rather, it focuses on sending piloted spacecraft and crews into orbit around exploration targets of interest, such as Mars, and conducting astronaut exploration of the surfaces using telerobots and remotely controlled systems. By eliminating the significant communications delay with Earth due to the speed of light limit, teleoperation provides scientists real-time control of rovers and other sophisticated instruments, in effect giving them a "virtual presence" on planetary surfaces, and thus expanding the scientific return at these destinations. It also eliminates development of the numerous man-rated landers, ascent vehicles and surface systems that are required to land humans on planetary surfaces. The propulsive requirements to travel from LEO to many destinations with shallow gravity-wells in the inner solar system are quite similar. Thus, a single spacecraft design could perform a variety of missions, including orbit-based surface exploration of the Moon, Mars and Venus, and rendezvous with Near Earth Asteroids (NEAs), as well as Phobos and Deimos. Although HERRO bypasses many of the initial steps that have been historically associated with human space exploration, it opens the door to many new destinations that are candidates for future resource utilization and settlement. HERRO is a first step that takes humans to exciting destinations beyond LEO, while expanding the ability to conduct science within the inner solar system.

关键词： Orbits

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Design and implementation of a characterization test rig for evaluating high bandwidth liquid fuel flow modulators

Design and implementation of a characterization test rig for...

引用

45th AIAA/ASME/SAE/ASEE Joint propulsion Conference and Exhibit

作者： Saus, Joseph R. Chang, Clarence T. DeLaat, John C. Vrnak, Daniel R. NASA Glenn Research Center Cleveland OH 44135 United States Controls and Dynamics Branch MS77-1 21000 Brookpark Rd. United States Combustion Branch MS77-1 21000 Brookpark Rd. United States Propulsion and Control Systems Analysis Branch MS86-1 21000 Brookpark Rd. United States

ISBN: (纸本)9781563479762

A test rig was designed and developed at the NASA Glenn Research Center for the purpose of characterizing high bandwidth liquid fuel flow modulator candidates to determine their suitability for combustion instability control research. The test rig is capable of testing flow modulators at up to 600 psia supply pressure and flows of up to 2 gpm. The rig is designed to provide a quiescent flow into the test section in order to isolate the dynamic flow modulations produced by the test article. Both the fuel injector orifice downstream of the test article and the combustor are emulated. The effect of fuel delivery line lengths on modulator dynamic performance can be observed and modified to replicate actual fuel delivery systems. For simplicity, water is currently used as the working fluid, although future plans are to use jet fuel. The rig is instrumented for dynamic pressures and flows and a high-speed data system is used for dynamic data acquisition. Preliminary results have been obtained for one candidate flow modulator.

关键词： Modulators

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Yaw-steered payload pointing and orbital control for a highly inclined elliptical orbit spacecraft

Yaw-steered payload pointing and orbital control for a highl...

引用

作者： Munir, Saghir Allison, Darcy L. MacHlis, Matthew Price, Xen Kemper, Brian Bruno, Michael Space Systems Loral Palo Alto CA 94303 United States Dynamics and Controls Analysis 3825 Fabian Way M/S G.76 United States Propulsion Products 3825 Fabian Way M/S G.86 United States Orbit Dynamics 3825 Fabian Way M/S G.76 United States Systems Engineering 3825 Fabian Way M/S G.80 United States

ISBN: (纸本)9781563479786

This article outlines a novel thruster use for orbital control and momentum management on a current Space systems/Loral 1300 series spacecraft. The strategy employed for steering a large unfurlable transmit antenna (9 meters in diameter) mounted on a satellite operating in a highly inclined elliptical orbit (HIEO) towards the continental U.S. (CONUS) is outlined. The onboard EIRP-Steering strategy ensures that the Equivalent Isotropic Radiated Power (EIRP) from the satellite to the intended CONUS is maximized during the service delivery period. The EIRP-steering algorithm is driven by the on-board control system and is fully autonomous, even in the event of orbital perturbations. Electrical power considerations require that the satellite be yaw steered about the electrical boresight of the transmit antenna. Given the 9-meter reflector and tight pointing requirements, the use of bipropellant thrusters for orbital control is minimized. Instead, the method chosen for orbital control are the north, south, and west-mounted stationary plasma thrusters (SPTs). Whenever possible, momentum management is also performed by the SPTs due to their significantly higher specific impulse (Isp). For attitude control, the satellite uses a star tracker, with a high fidelity onboard orbit propagator that models all significant disturbances, including SPT and bi-propellant thruster actuations. Orbital perturbations and effects on momentum management from SPT plume impingement on the spacecraft surfaces are accounted for. Summary plots showing various aspects of the missions profile and relavant momentum management results are also included. Copyright © 2009 by Space systems Loral.

关键词： Attitude control

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