Bonnie James

Marshall Space Flight Center

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C. G. Justus

Dynetics (United States)

Michelle Munk

Langley Research Center

Dale L. Johnson

Marshall Space Flight Center

Steve Moon

Joel L. Herr

Glenn Research Center

Rebecca T. Lenzini

Purdue University West Lafayette

Melissa Kummerer

EBSCO Industries (United States)

Les Johnson

Marshall Space Flight Center

George Lewicky

Harvard University Press

Delores Meglio

Harvard University Press

Cooperative Institutions

Marshall Space Flight Center

International Institute of Tropical Agriculture

Harvard University Press

International Institute of Tropical Agriculture

National Aeronautics and Space Administration

Ames Research Center

International Institute of Tropical Agriculture

University of Arizona

Purdue University West Lafayette

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Research Field

Aerocapture Benefits to Future Science Missions

Gwen Artis Bonnie James

NASA's In-Space Propulsion Technology (ISPT) Program is investing in technologies to revolutionize the robotic exploration of deep space. One of these technologies is Aerocapture, the most promising of the techniques used to maneuver a space vehicle within an atmosphere, using aerodynamic forces in lieu of propellant. (Other aeroassist techniques include aeroentry and aerobraking.) Aerocapture relies on drag atmospheric drag to decelerate an incoming spacecraft and capture it into orbit. This technique is very attractive since it permits spacecraft to be launched from Earth at higher velocities, providing shorter trip times and saving mass and overall cost on future missions. Recent aerocapture systems analysis studies quantify the benefits of aerocapture to future exploration. The 2002 Titan aerocapture study showed that using aerocapture at Titan instead of conventional propulsive capture results in over twice as much payload delivered to Titan. Aerocapture at Venus results in almost twice the payload delivered to Venus as with aerobraking, and over six times more mass delivered into orbit than all-propulsive capture. Aerocapture at Mars shows significant benefits as the payload sizes increase and as missions become more complex. Recent Neptune aerocapture studies show that aerocapture opens up entirely new classes of missions at Neptune. Current aerocapture technology development is advancing the maturity of each subsystem technology needed for successful implementation of aerocapture on future missions. Recent development has focused on both rigid aeroshell and inflatable aerocapture systems. Rigid aeroshell systems development includes new ablative and non-ablative thermal protection systems, advanced aeroshell performance sensors, lightweight structures and higher temperature adhesives. Inflatable systems such as trailing tethered and clamped ballutes and inflatable aeroshells are also under development. Computational tools required to support future aerocapture missions are an integral part of aerocapture development. Tools include engineering reference atmosphere models, guidance and navigation algorithms, aerothermodynamic modeling, and flight simulation.

Payload (computing)

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NASA's In-Space Propulsion Technology Program: A Step Toward Interstellar Exploration

Les Johnson Bonnie James Randy Baggett Sandy Montgomery

NASA's In-Space Propulsion Technology Program is investing in technologies that have the potential to revolutionize the robotic exploration of deep space. For robotic exploration and science missions, increased efficiencies of future propulsion systems are critical to reduce overall life-cycle costs and, in some cases, enable missions previously considered impossible. Continued reliance on conventional chemical propulsion alone will not enable the robust exploration of deep space. The maximum theoretical efficiencies have almost been reached and are insufficient to meet needs for many ambitious science missions currently being considered. By developing the capability to support mid-term robotic mission needs, the program is laying the technological foundation for travel to nearby interstellar space. The In-Space Propulsion Technology Program s technology portfolio includes many advanced propulsion systems. From the next-generation ion propulsion systems operating in the 5-10 kW range, to solar sail propulsion, substantial advances in spacecraft propulsion performance are anticipated. Some of the most promising technologies for achieving these goals use the environment of space itself for energy and propulsion and are generically called because they do not require onboard fuel to achieve thrust. Propellantless propulsion technologies include scientific innovations, such as solar sails, electrodynamic and momentum transfer tethers, and aerocapture. This paper will provide an overview of those propellantless and propellant-based advanced propulsion technologies that will most significantly advance our exploration of deep space.

In-space propulsion technologies

Ion thruster

Solar Sail

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Additions to Mars Global Reference Atmospheric Model (MARS-GRAM)

C. G. Justus Bonnie James

Three major additions or modifications were made to the Mars Global Reference Atmospheric Model (Mars-GRAM): (1) in addition to the interactive version, a new batch version is available, which uses NAMELIST input, and is completely modular, so that the main driver program can easily be replaced by any calling program, such as a trajectory simulation program; (2) both the interactive and batch versions now have an option for treating local-scale dust storm effects, rather than just the global-scale dust storms in the original Mars-GRAM; and (3) the Zurek wave perturbation model was added, to simulate the effects of tidal perturbations, in addition to the random (mountain wave) perturbation model of the original Mars-GRAM. A minor modification was also made which allows heights to go 'below' local terrain height and return 'realistic' pressure, density, and temperature, and not the surface values, as returned by the original Mars-GRAM. This feature will allow simulations of Mars rover paths which might go into local 'valley' areas which lie below the average height of the present, rather coarse-resolution, terrain height data used by Mars-GRAM. Sample input and output of both the interactive and batch versions of Mars-GRAM are presented.

Gram

Dust storm

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NASA's In-Space Propulsion Technology Program: A Step Toward Interstellar Exploration

Journal of the British Interplanetary Society (2005)

Lee Johnson Bonnie James Rune Baggett Erin Montgomery

In-space propulsion technologies

Ion thruster

Solar Sail

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Operating in the space plasma environment - A spacecraft charging study of the Solar X-ray Imager

Space Programs and Technologies Conference and Exhibit (1994)

Joel L. Herr Matthew McCollum Bonnie James

This study presents the results of a spacecraft charging effects protection study conducted on the Solar X-ray Imager (SXI). The SXI is being developed by NASA Marshall Space Flight Center for NOAA's Space Environment Laboratory, and will be used to aid in forecasting energetic particle events and geomagnetic storms. Images will provide information on the intensity and location of solar flares, coronal mass ejections, and high speed solar streams. The SXI will be flown on a next-generation GOES sometime in the mid to late 1990's. Charging due to the encounter with a worst-case magnetic substorm environment is modeled using the NASCAP/GEO computer code. Charging levels of exterior surfaces and the floating potential of the spacecraft relative to plasma are determined as a function of spacecraft design, operational configuration, and orbital conditions. Areas where large surface voltage gradients exist on or near the SXI are identified as possible arc-discharge sites. Results of the charging analysis are then used to develop design recommendations that will limit the effects of spacecraft charging on the SXI operation.

Spacecraft charging

Space environment

Astrophysical plasma

10.2514/6.1994-4472

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Citations (2)

Project B: developing plant health management options

K. Agboka Mafimidiwo Bamidele Ayodele Ranajit Bandyopadhyay Fen D. Beed P. Boons

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Simple Thermal Environment Model (Stem) User's Guide

C. G. Justus G. W. Batts B. J. Anderson Bonnie James

This report presents a Simple Thermal Environment Model (STEM) for determining appropriate engineering values to specify the thermal environment of Earth-orbiting satellites. The thermal environment of a satellite, consists of three components: (1) direct solar radiation, (2) Earth-atmosphere reflected shortwave radiation, as characterized by Earth's albedo, and (3) Earth-atmosphere-emitted outgoing longwave radiation (OLR). This report, together with a companion report provides methodology and guidelines for selecting design points for thermal environment parameters for satellites and spacecraft systems. The methods and models reported here are outgrowths of Earth Radiation Budget Experiment (ERBE) satellite data analysis and thermal environment specifications discussed by Anderson and Smith (1994). In large part, this report is intended to update (and supersede) those results.

Albedo (alchemy)

Shortwave

Longwave

Earth observation satellite

Thermal Radiation

Shortwave radiation

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Citations (12)

Operating in the space environment - A spacecraft charging study of the Advanced X-ray Astrophysics Facility-Spectroscopy

Space Programs and Technologies Conference and Exhibit (1994)

M. McCollum Bonnie James Joel L. Herr

space technology

10.2514/6.1994-4471

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Citations (2)

Mars Global Reference Atmospheric Model 2000 Version (Mars-GRAM 2000): Users Guide

C. G. Justus Bonnie James

This report presents Mars Global Reference Atmospheric Model 2000 Version (Mars-GRAM 2000) and its new features. All parameterizations for temperature, pressure, density, and winds versus height, latitude, longitude, time of day, and L(sub s) have been replaced by input data tables from NASA Ames Mars General Circulation Model (MGCM) for the surface through 80-km altitude and the University of Arizona Mars Thermospheric General Circulation Model (MTGCM) for 80 to 170 km. A modified Stewart thermospheric model is still used for higher altitudes and for dependence on solar activity. Climate factors to tune for agreement with GCM data are no longer needed. Adjustment of exospheric temperature is still an option. Consistent with observations from Mars Global Surveyor, a new longitude-dependent wave model is included with user input to specify waves having 1 to 3 wavelengths around the planet. A simplified perturbation model has been substituted for the earlier one. An input switch allows users to select either East or West longitude positive. This memorandum includes instructions on obtaining Mars-GRAM source code and data files and for running the program. It also provides sample input and output and an example for incorporating Mars-GRAM as an atmospheric subroutine in a trajectory code.

Longitude

Atmosphere of Mars

Atmospheric models

Atmospheric Circulation

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Citations (24)

Mars Global Reference Atmospheric Model (Mars-GRAM): Release No. 2 -Overview and applications

21st Aerospace Sciences Meeting (1993)

Bonnie James Dale L. Johnson L. TYREE

The Mars Global Reference Atmospheric Model (Mars-GRAM), a science and engineering model for empirically parameterizing the temperature, pressure, density, and wind structure of the Martian atmosphere, is described with particular attention to the model's newest version, Mars-GRAM, Release No. 2 and to the improvements incorporated into the Release No. 2 model as compared with the Release No. 1 version. These improvements include (1) an addition of a new capability to simulate local-scale Martian dust storms and the growth and decay of these storms; (2) an addition of the Zurek and Haberle (1988) wave perturbation model, for simulating tidal perturbation effects; and (3) a new modular version of Mars-GRAM, for incorporation as a subroutine into other codes.

Atmospheric models

Atmosphere of Mars

10.2514/6.1993-849

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