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Found 5 entries in the Bibliography.
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Case study of the parker solar probe thermal protection system: Development of a system level process for high temperature technology achievement
Successful development of high temperature systems is complex and difficult. Limitations in testing, manufacturing and materials means that design and testing of such systems is challenging. NASA s Parker Solar Probe (PSP) Spacecraft built by the Johns Hopkins Applied Physics Laboratory was launched in August 2018 and is measuring the Sun s atmosphere in situ. A critical technology development which made this mission possible is the 4.5 inch-thick Thermal Protection System (TPS) that has to withstand 2500°F and protect t ...
Congdon, Elizabeth; Mehoke, Douglas; Conkey, Shelly; Schaefer, Ed; Abel, Elisabeth;
Published by: Proceedings of the International Astronautical Congress, IAC Published on:
Heat shielding; High temperature effects; High temperature engineering; Manufacture; NASA; Probes; Thermal insulating materials; Parker Engineering
Full scale thermal simulator development for the solar probe plus thermal protection system
Solar Probe Plus (SPP) is a NASA mission that will go within ten Solar Radii of the sun. One of the crucial technologies in this system is the Thermal Protection System (TPS), which shields the spacecraft from the sun. The TPS is made up of carbon-foam sandwiched between two carbon-carbon panels, and is approximately eight feet in diameter and 4.5 inches thick. At its closest approach, the front surface of the TPS is expected to reach 1200°C, but the foam will dissipate the heat so the back surface will only be about 300 ...
Heisler, Elizabeth; Abel, Elisabeth; Congdon, Elizabeth; Eby, Daniel;
Published by: IEEE Aerospace Conference Proceedings Published on:
Aluminum coated steel; Carbon; Foams; Heat shielding; NASA; Probes; Simulators; Space flight; Stainless steel; Thermal insulating materials; Thermoanalysis; Vacuum technology; Parker Engineering
Development of the solar probe plus spacecraft thermal protection system (TPS) thermal simulator-subscale testing
The NASA’s Solar Probe Plus spacecraft must endure extreme heat loads while passing near the Sun. Due to its high incident heatload and temperature, the spacecraft Thermal Protection System (TPS) must be simulated using a custom thermal simulator during spacecraft thermal vacuum testing. As part of the development of the TPS thermal simulator, subscale testing was performed. The design, testing, results and lessons learned are described in this paper. Especially useful are the design aspects needed to achieve the high ...
Congdon, Elizabeth; Abel, Elisabeth; Heisler, Elizabeth;
Published by: 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference Published on:
Aerodynamics; Heat shielding; NASA; Probes; Simulators; Spacecraft; Thermal insulating materials; Parker Engineering
Solar Probe Plus mission overview
Solar Probe Plus will be the first mission to pass into the solar corona to study how the corona is heated and the solar wind is accelerated. Solving these two fundamental mysteries has been a top-priority science goal for over five decades. The Johns Hopkins University Applied Physics Laboratory in Laurel, Maryland, is managing the mission for NASA s Living with a Star Program, including the development, build, and operation of the spacecraft. SPP will launch in 2018, performing 24 orbits of the Sun over a 7-year duration. ...
Reynolds, Edward; Driesman, Andrew; Kinnison, James; Lockwood, Mary; Hill, Patrick;
Published by: AIAA Guidance, Navigation, and Control (GNC) Conference Published on:
Carbon; Foams; Heat shielding; Interplanetary flight; NASA; Probes; Solar cell arrays; Solar energy; Spacecraft; Temperature; Thermal insulating materials; Parker Engineering
Development of a high-temperature optical coating for thermal management on solar probe plus
NASA s Solar Probe Plus (SPP) is approaching within 9.5 solar radii from the center of the sun. The SPP thermal protection system (TPS) is a 2.7 meter heat shield. The heat shield reaches temperatures of 1400°C on its front surface, its worst thermal case, and is subjected to launch loads, its worst mechanical case. The front surface of the thermal protection system is coated with an optically white coating in order to reduce the front surface temperature of the TPS and reduce the resulting heat flow into the spacecraft. ...
Congdon, Elizabeth; Mehoke, Douglas; Buchta, Mark; Nagle, Dennis; Zhang, Dajie; Spicer, James;
Published by: 10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference Published on:
Heat shielding; Heat transfer; NASA; Optical coatings; Probes; Thermal insulating materials; Thermal variables control; Parker Engineering