GPS based prediction of the instantaneous impact point for sounding rockets |
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| Institution: | 1. German Space Operations Center, Deutsches Zentrum für Luft- und Raumfahrt, DLR 82230 Weßling, Germany;2. NASA, Goddard Space Flight Center, Wallops Flight Facility, Wallops Island, Virginia 23337-5099, USA;3. Kayser-Threde GmbH, Wolfratshauser Staße 48, 81379 München, Germany;1. West Department of IZMIRAN, 41 Av. Pobeda, 23601 Kaliningrad, Russia;2. Institute of Ionosphere NAS and MES of Ukraine, Kharkov, Ukraine;3. Geodynamics Research Laboratory, University of Warmia and Mazury, Olsztyn, Poland;1. German Aerospace Center (DLR), Institute of Communications und Navigation (IKN), Kalkhorstweg 53, D-17235 Neustrelitz, Germany;2. Telespazio VEGA Deutschland GmbH c/o European Space Operations Centre (ESA/ESOC), Robert-Bosch-Straße 5, D-64293 Darmstadt, Germany;3. Center for Atmospheric Research, University of Massachusetts Lowell, Lowell, MA, USA;4. Department of Physics and Astronomy, Dartmouth College, Hanover, NH, USA;5. European Space Operations Centre (ESA/ESOC), Robert-Bosch-Straße 5, D-64293 Darmstadt, Germany;1. School of Information Science and Engineering, Shandong University, Jinan 250100, PR China;2. Key Laboratory of Intelligent Perception and Systems for High-Dimensional Information, Ministry of Education, Nanjing University of Science and Technology, Nanjing 210094, PR China;3. Computer Science Department, Rensselaer Polytechnic Institute, Troy, NY 12180, USA;4. School of Electronics and Information Engineering, Harbin Institute of Technology, Harbin 150080, PR China;1. Institute of Laser, School of Science, Beijing Jiaotong University, Beijing 100044, China;2. Key Laboratory of Luminescence and Optical Information, Ministry of Education, Beijing 100044, China |
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| Abstract: | As part of the range safety operations during a sounding rocket launch, a real-time prediction of the instantaneous impact point (IIP) is performed to monitor the expected touch down point in case of a boost termination. Supplementary to traditional radar tracking, the IIP prediction is nowadays based on GPS navigation data, which offer an inherently higher accuracy and reduced data noise. To comply with the increased tracking performance, a consistent set of equations suitable for real-time computation of the approximate IIP is established. Aside from a consideration of gravitational forces, reference frame rotation and Earth curvature, the model can also account for drag during the ascent trajectory provided that a priori information on the ballistic properties of the launch vehicle is available. The algorithm is tested for a representative set of mission profiles and applied to GPS flight data of an Improved Orion rocket and a Maxus rocket launched at Esrange, Kiruna. |
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