Day 2 :
Keynote Forum
Giancarlo Genta
Politecnico di torino, Italy
Keynote: Solar electric spacecraft for human Mars missions
Time : 09:05-09:40
Biography:
Giancarlo Genta completed his Master Degree in Aeronautical Engineering, he is a Professor of Construction Machines at Polytechnic University of Turin, Italy. He is a Member of the Academy of Sciences of Torino and of International Academy of Astronautics (IAA). In 2013, he received the Yangel Medal for outstanding contributions to “The development of the international space sciences and technologies” and the Engineering Science Award of the International Academy of Astronautics for outstanding achievement in Engineering Science. Starting from 2012 he chaired two study groups of the IAA on human Mars and lunar exploration. He authored 95 papers, published in Italian, American and English journals, 276 papers presented to symposia and 26 books. He is also the Author of two science fiction novels, published in Italian, English and Ukrainian.
Abstract:
Recent progress in the field of thin film photovoltaic cells and large deployable structures may allow to build fast solar electric spacecraft for human Mars exploration. At least in the short term, they may represent an interesting alternative to both chemical propulsion, which implies large initial mass in LEO – and hence large costs – and nuclear electric or nuclear thermal propulsion, which at present require large investments to achieve the required technological readiness. The performance of any electrically propelled spacecraft depends mainly on the mass/power ratio of its power generator, expressed in kg/kW by the parameter α. The value of α, at one astronomical unit (AU) from the sun, approximately doubles at Mars distances, mainly due to the reduction in solar illumination. In a Mars mission, this leads to a decrease of the overall performance of the spacecraft by approximately 15% with respect to a system with constant α i.e. NEP(nuclear electric propulsion). The main advantage of a planetary mission performed using electric propulsion is that the payload ratio increases monotonically with the increase of travel time (contrary to impulsive propulsion in which the payload ratio has a maximum and then decreases again) and thus makes the split-mission concept in which a robotic Mars cargo ship first preposition a habitable infrastructure on the planet before the crew travels there in a faster and lighter ship in a much more convenient manner. SEP is often considered a good choice for a robotic cargo spacecraft, while the crewed ship retains a traditional chemical propulsion. However, new technologies for solar arrays, based on the structures developed for solar sail spacecraft and on thin film PVA allow to maintain quite a low value of α, much lower than what can be realistically predicted in the short and medium term for nuclear generators. Very large, but nevertheless lightweight, solar arrays can thus propel also fast crewed spacecraft, reaching Mars in a time of about 6 or 7 months.
Keynote Forum
Daniele Bortoluzzi
University of Trento, Italy
Keynote: LISA Pathfinder: A technology demonstrator mission for future in-space gravitational wave detection
Biography:
Daniele Bortoluzzi is an Associate Professor of Mechanics in Department of Industrial Engineering at University of Trento. He collaborates with the European Space Agency and several industrial partners in the design of payloads for scientific missions, with particular emphasis on mechanisms. He is responsible for the qualification of the release mechanism for the LISA Pathfinder mission, where tribological, dynamics and control issues are involved.
Abstract:
LISA Pathfinder is an ESA mission for the in-flight testing of the concept of gravitational wave detection. Two test masses are set inside the spacecraft in an unprecedented level of free-fall purity under the action of the planetary gravitational field, by reducing any force disturbance at the femto-N order of magnitude. The achievement of this level of free-fall purity constitutes the key requirement for the measurement of gravitational waves in the frequency bandwidth (10-4 up to 10-1 Hz) where the most predictable and powerful sources (galactic binaries and massive black holes) predominantly emits their radiation. This bandwidth is not covered by ground-based detectors (e.g. LIGO) due to the terrestrial Newtonian gravitational field noise and can only be explored by space-based instruments, like LISA (Laser Interferometer Space Antenna). The mission was launched on December 3rd 2015 and successfully concluded the science operations on June 30th 2017, after a nominal and an extended mission phase. In general, the mission provided the demonstration that an extended object can be set into a geodesic trajectory with an acceleration noise level of the fms-2/√Hz (over a bandwidth of 0.1mHz to 0.1Hz), which fulfills the requirements for the full observation program of the LISA observatory for the gravitational waves. The key technologies tested in LISA Pathfinder, ranging from the inertial sensor, the optical metrology, the spacecraft drag free and attitude control system to the micro-propulsion system, combine with several other system challenges: gravitational balancing, thermal stability, control of the magnetic environment. This complex experiment aims at confirming the physical model of the forces acting on the test masses, understanding the dynamics of the spacecraft-test mass system to an exceptional detail. The increase of knowledge about all these topics is the real outcome of the mission. As a technology demonstrator for LISA, it addressed its main criticalities and provided strong support to its formal selection as the 3rd large class mission in the ESA cosmic vision program. In this framework, its heritage becomes part of a long-term planning strategy implemented by ESA to push the frontiers of space exploration to new limits.
Keynote Forum
Ryspek Usubamatov
Kyrgyz State Technical University, Kyrgyzstan
Keynote: P-MMGP: Physics And Mathematical Models for Gyroscope Properties
Biography:
Ryspek Usubamatov, Doctor Engineer graduated from Bauman Moscow State Technical University. Russia. He is a Professional Engineer in Mechanical, Manufacturing and Industrial Engineering, completed PhD in 1972 and Dr Tech Sc in 1993. He worked as an Engineer at a company and Lecturer in universities of Kyrgyzstan and Malaysia. He is a Professor of Razzakov Kyrgyz State Technical University. He has supervised around 100 Professional Engineer 15 MSc and 7 PhD students. His key research are productivity theory for industrial engineering, gyroscope theory and wind turbines represented by 7 books, 30 brochures and more than 300 manuscripts in reputed journals and 60 patents.
Abstract:
The gyroscope property of maintaining the axis of a spinning rotor is used in gyroscopic devices for navigation and control systems in aerospace and other industries. Recent investigations in gyroscope area have demonstrated that the origin of gyroscope effects is more complex than represented in known mathematical models, which do not match the actual forces and motions. It is known that in a gyroscope are acting simultaneously and interdependently eight inertial torques around two axes, which manifest the resistance and precession torques and other properties. These torques are generated by action of centrifugal, common inertial and Coriolis forces of mass elements as well as the change in the angular momentum of the spinning rotor’s center mass. Action of internal torques is a result of action of the external torque applied to a gyroscope. In engineering area, the gyroscopic devices can be loaded by several external torques acting around axes. Each external torque generates the internal inertial torques acting around two axes. The external torque applied to the gyroscope with one side support in direction of precession demonstrates its turn up around axis. Some researchers represent this effect as evidence of “gyroscope’s antigravity property”, which actually is the result of action of the internal torques. The new mathematical models for the gyroscope’s internal torques based on action of the mass elements and center mass of the spinning rotor enable describing all gyroscope effects, properties and motions. Additionally, new analytical approach demonstrates new unknown gyroscope properties, which physics is hard to interpret.
Keynote Forum
Alexander V Nebylov
State University of Aerospace Instrumentation, Russia
Keynote: Performance and technological feasibility of aerospace plane horizontal launch and landing with ekranoplane assistance
Biography:
Alexander V Nebylov has few Degrees to credit including: Title of the Honorary Scientist of the Russian Federation; Decree of the President of Russian Federation of 2006; Academic rank of Full Professor since 1986; Doctor of Science Degree in information processing and control systems since 1985. His scientific field of interest include: motion control theory, control systems and avionics. He the author of 18 books and more than 300 scientific papers and inventions, leader of many Research and Development in aerospace instrumentation. He is a Chairman of Aerospace Devices and Measuring Complexes, State University of Aerospace Instrumentation in Saint Petersburg and Director of the International Institute for Advanced Aerospace Technologies, Russia. He is a Member of the leadership of the IFAC Aerospace Technical Committee since 2002.
Abstract:
Numerous attempts to reduce the cost of satellites launch into a low orbit that were taken in many countries, characterize the current trend to make space projects economically viable and less costly. Unfortunately, this process has not led to a sharp decrease in the specific launch cost. The promising idea to make the launch cheaper is the transition from the vertical to the horizontal launch, which uses an air breathing engine. A simple method of expanding the velocity range for them was being developed by the use of boosters, gives Aerospace Plane (ASP) the aviation speed at which the main air breathing jet engine begins to operate effectively. Researches in the field of satellites horizontal launch (HTHL) were carried out in different countries. We will consider the project of launch system with ekranoplane as a booster for ASP and a mobile landing strip. This project was offered by N Tomita, Y Ohkami and A Nebylov in 1996 and since that time it has been developed in a view of detailed reasoning and various feasibility studies. Ekranoplane can give ASP the primary speed of Mach 0.6 in needed direction which allows to lower the requirements to ASP wing area and its engines. Some other advantages are connected with possible use of ekranoplane for ASP landing. Heavy ekranoplane is the single vehicle for implementing the innovative idea of docking of the descending ASP in the specific stage allowing to expand opportunities of its landing. The technology of ASP horizontal landing without undercarriage by docking with ekranoplane at the last stage of descent and the requirements of control systems are discussed.
- Space Missions | Remote Sensing Satellites and GIS | Satellite Navigation and Communication | Aerospace and Mechanical Engineering | Mobile Satellite Communication Networks Environmental Science
Location: Olimpica 1
Chair
Giancarlo Genta
Politecnico di torino, Italy
Co-Chair
Ryspek Usubamatov
Kyrgyz State Technical University, Kyrgyzstan
Session Introduction
Pascal Legai,
European Union Satellite Centre, Spain
Title: Earth observation for security and defence: The European Union Satellite Centre experience and future views
Biography:
Pascal Legai is an aeronautical and space engineer and holds a degree in geography engineering, a master's degree in image processing and a doctorate in international relations. Intelligence officer of the French Ministry of Defence, he is a specialist in international space relations and, in particular, is an expert on strategic issues related to satellite imagery. He was the director of the Joint Training and Imagery Interpretation Interpreting (CF3I) of the Military Intelligence Directorate (DRM) and is currently Director of the European Union Satellite Center (SatCen).
Abstract:
The European Union Satellite Centre (SatCen) supports the decision-making and actions of the European Union in the field of Common Foreign and Security Policy (CFSP), in particular Common Security and Defence Policy (CSDP). It thus addresses European Union crisis management missions and operations, by providing products and services resulting from the exploitation of relevant space assets and collateral data, including satellite imagery and aerial imagery, and related services. For fulfilling its tasks, SatCen cooperates with numerous national, European and international institutions in the field of remote sensing from space and works with image providers, public, commercial or governmental ones as well as with open source information. From its unique role and position in the remote sensing operational chain for security and defense, SatCen is following carefully the fast evolution of the remote sensing field: the needs from the end users but also of the techniques as well as the provided services and innovation from industry. In particular, the users ‘requirements, asking from near real time service, imply to have more frequent data acquisition as well as faster data processing and analysis. On the other hand, the increasing volume of available data collides with the limitation of image analyst staffing, imposing to extract the information close by the data generation, at upstream level, as well as to rely on automatic tools to focus analysts work on the most complex and demanding issues. The presentation will thus expose the analysis of SatCen, taking the benefits of its 25 years operational experience, on the fast evolving environment of remote sensing for security and defense, to identify the most important challenges to face at technical, operational and staff levels.
Biography:
Xavier Geneste works for aerospace industry since 1989 as an Electronics Engineer. He has been working on spacecrafts for the three majors in France, Aerospatiale (then Alcatel Space and now Thales Alenia Space), Astrium (now Airbus Defense and Space), CNES (National Center for Space Research) on a wide range of activities from project initiation to launches. He is currently working at European Space Agency since 2009 as a Senior Spacecraft Engineer and is dealing with new technologies developments for the telecommunication platforms (ARTES program).
Abstract:
Recent discoveries of possible existence of water in the South Pole of the moon, the popularity growth on missions to Mars, the reduction of the launch cost and more affordable technology, are some of the key aspects which have triggered a growing interest in the moon exploration by a number of governmental and private organizations during the latest years. Today, most of the big players are planning activities at the moon for the upcoming ten years in diverse areas (i.e. governmental, tourism, science, imaging and mining). Lunar Communications mission aims at enabling the development of a wide range of missions at the moon by providing a backbone lunar communication and navigation infrastructure. The mission is proposed as a game changer, especially for small-medium size missions by providing data relay communication and localization services, reducing the complexity, weight and costs of the payloads and outsourcing the operations and logistics, thus de-risking lunar missions and attracting new initiatives to the moon. The communications architecture is planned to be fully compatible with the International Communication System Interface Standards Document being finalized within the Interagency Operations Advisory Group (IOAG) standard services and Consultative Committee on Space Data Systems (CCSDS) forums. This intends to simplify, not only the architecture by offering services compatible with internationally agreed frequency and modulation schemes allocations, but the interaction with the future users that would just need to build their systems compatible with the standards.
Serhii Moskalov,
Yuzhnoye State Design Office, Ukraine
Title: Advanced space technologies in interests of scientific researches in the near earth and interplanetary space
Biography:
Serhii Moskalov has his expertise in the field of system designing space hardware. He participated in development of the Earth observation satellite Egyptsat-1 as well as the Earth observation and scientific satellites Sich-1M and Sich-2 that were launched in 2007, 2004 and 2011 respectively. Now Serhii Moskalov is a deputy Chief Designer and Head of Spacecraft and Systems Design Office. Under his leadership modern Earth observation and scientific satellites and buses for satellites of different classes are now being developed.
Abstract:
Development of spacecraft in the context of scientific research of space was from the very start one of the prioritized directions of Yuzhnoye’s activities. Nowadays Yuzhnoye proposes satellite platforms for scientific research as a reasonably priced and available means for scientific and technological experiments implementation. Depending on the payload type, specific orbit parameters, required type and accuracy of orientation there is a possibility to outfit the satellite platforms in terms of the following: increasing data rate; increasing attitude control accuracy; increasing power supply performance. Currently Yuzhnoye ensures technical implementation of Microsat project, the main purpose of which is observation of dynamic processes in the earth’s ionosphere. To perform ionosphere measurements Microsat-M spacecraft, developed on the basis of MS-2 satellite platform, is equipped with scientific instruments including: magnetic-wave complex; particles density analyzer; electric field spectrum analyzer; ionic driftmeter; scientific data collection system. Further phase of the project shall be development of satellite cluster for researching earth ionosphere based on Yuzhsat satellite platform providing simultaneous multi-point measurements of ionosphere parameters. Aerosol-UA project is currently being developed. It is intended for conducting global measurements of the detailed physical characteristics of natural and anthropogenic aerosols in the earth atmosphere as well as assessment of their chemical composition. For this project implementation Yuzhnoye also proposes Yuzhsat satellite platform equipped with a payload including scanning polarimeter (ScanPol) and multi-spectrum image-polarimeter (MSIP). The report also contains the results of “Lunar Industrial and Researching Base” conceptual design (concept of Lunar Industrial and Research Base, its configuration and infrastructure at different phases of operation, duration of the project implementation, main technical characteristics of the Lunar Base). A number of key elements are based on available technologies ( the reliability of some of them was confirmed by flight tests). Technologies and strategy of Lunar Industrial and Research Base creation proposed by Yuzhnoye bring us closer to practical implementation of such a global idea with lower expenses and short time period.
- WorkShop
Location: Olimpica 1
Session Introduction
Paul S Szymanski
Space Strategies Center, USA
Title: Outer space warfare challenges: Theory, doctrine, strategies and tactics
Biography:
Paul S Szymanski has 41 years of continuous experience studying outer space warfare theory, doctrine, strategies and tactics. This includes advanced concept development, space courses of action (COA’s) design, and space battle management command and control (BMC2) support.
Abstract:
The importance of outer space satellites and their supporting systems cannot be overstated. Their use in the civil and commercial world to provide communications, weather, navigation, timing and earth resources monitoring provides major advantages to those who employ the information generated by these systems. However, due to the global reach of these space systems, advantages are provided to both friendly and adversary militaries. Beginning with the use of space systems to support military operations during the Arab-Israeli conflicts, and in Desert Storm, both major and minor players are considering how denial of space capabilities to their adversaries will be a force multiplier on terrestrial battlefields. Based on the author’s extensive experience in this theoretical area, he has developed essential theory, rules, doctrine, strategies and tactics by which he feels the next space war will be conducted. These are based on his unclassified analyses of past military history, and of classical Military Principles of War and Sun Tzu's Art of War applicability to Space Warfare. Since a full-up space war has not yet occurred, all of these concepts are notional and unproven, much like air warfare doctrine was only theoretically understood prior to World War 2. Nonetheless, it is very important to better understand how a future space war might be conducted to ensure favorable outcomes for the more prepared country, and for better outcomes for the world, in general, post space conflict.
- Session Continuous
Location: Olimpica 1
Session Introduction
Alaa A Saeed Al Rubaie
Ministry of Higher Education and Scientific Research, Iraq
Title: Turbo code based physical layer network coding for free space optical channel
Biography:
Alaa A Saeed Al Rubaie has completed his PhD in Communications from Communications, Sensors, Signal and Information Processing (ComS2IP) Group, School of Electrical and Electronic Engineering, Newcastle University, Newcastle Upon Tyne, UK He has MSc in Computer Network from University of Technology, Baghdad, Iraq. He is currently working as the Director in the Department of Information Technology in the Ministry of Higher Education and Scientific Research, Baghdad, Iraq. He has his expertise in wireless communication networks with a focus on an advanced modulation, coding technique, equalization, radio frequency and free-space optical channels.
Abstract:
Physical layer network coding (PNC) for a two-way relay (TWR) channel has been utilized for increasing the system throughput in a TWR, where the two users exchange their information via a relay node. PNC with a TWR channel is adopted free space optical (FSO) communication link (TWR-FSO) to enhance the link availability under the atmospheric turbulence condition. FSO has attracted significant attention in a range of application, where the radio frequency (RF) based wireless technologies may not be used or be suitable. In fact, the use of FSO in certain applications releases the pressure on already highly congested RF spectrum, which can be used in areas where the demand for RF is very high. In this research, we introduce the turbo code in the TWR-FSO PNC system and evaluate the end-to-end (E2E) in terms of the bit error rate (BER) for weak and strong regimes. The performance of E2E turbo code in terms of iterative manner combined with TWR-FSO PNC is presented to improve the system performance and then compared with both non-iterative convolutional code and uncoded systems under the different influences turbulence. The simulation results shows that the proposed scheme can achieve a significant BER performance improvement through the introduction of an iterative process between turbo decoders. Furthermore, we investigate the decoding process of the system by using a graphical description, this involved implementing the extrinsic information transfer (ExIT) charts. The ExIT chart was implemented as a tool to analyze the convergence properties of iterative receivers. We review the ExIT chart, the simulation setup and the construction to analyze the major features of system architecture. The ExIT functions of the two decoders are thoroughly analyzed for a range of parameters under the influence of a turbulence-induced channel fading to demonstrate the convergence behavior.
Ahmed Radi
University of Calgary, Canada
Title: Modelling of stochastic errors for low-cost inertial/GNSS fully integrated architecture systems
Biography:
Ahmed Radi, PhD candidate in the Mobile Multi-Sensor Systems Research Group in the Department of Geomatics Engineering, University of Calgary (UofC), Canada. He got his B.Sc. (2007) and M.Sc. (2014) degrees in Electrical Engineering at Military Technical Collage, Egypt. Prior to joining the UofC, Ahmed held the position of senior researcher at the Technical Researches Center, Egypt. He published 8 papers in academic journals and conference proceedings. Ahmed received Faculty of Graduate Studies scholarship award, UofC, 2018. His research area is related to the non-linear error modeling of low-cost MEMS inertial sensors, multi-sensors integration, IMU calibration, wavelet analysis, estimation techniques, Kalman filter, adaptive integrated navigation algorithms.
Abstract:
The integration of Global Navigation Satellite System (GNSS) with Inertial Navigation Systems (INS) has become a standard approach, for the last two decades, for accurate navigation and, hence, has been implemented widely in various applications. Such a complementary integrated architecture has been used for providing navigational information in many different fields such as mapping/surveying applications, autonomous driving, unmanned ground vehicles (UGVs), and unmanned aerial vehicles (UAVs), where accurate position and orientation information is required. In order to achieve high positioning accuracy, a precise analysis of both GNSS positioning solutions and inertial sensors error, and their quantitative models, is highly needed. This paper investigates the Generalized Method of Wavelet Moments (GMWM) method for stochastic modelling of 1) low-cost GNSS receiver signal and 2) low-cost MEMS-based inertial sensors. Different datasets (including GNSS and raw inertial data) were collected using an all-in-one sensor system, namely MTi-G-710, where GNSS data was obtained and then processed in single point positioning (SPP) mode where position errors are expressed in the local-level frame (LLF) of reference. GMWM were used in identifying and characterizing the different latent stochastic process and their related coefficients for both GNSS position residual signals and inertial sensors ones as well where precise stochastic models have been built. The test results showed that for low-cost GNSS receivers, a white noise process alone is not sufficient for accurate position residual signals’ modeling. The results also stressed out that the GNSS error signal models are complicated where the corresponding error model structures were represented as a sum of random walk and more than one 1st order Gauss-Markov (GM) processes, as an indication of correlated noise existence between consecutive observations. Moreover, results emphasize that a 1st order GM process, which is usually considered, is not always well fitted with the behaviour of low-cost inertial sensor errors where a more complicated model structure need to be considered to improve the overall navigation results. In addition, the results showed that the GMWM is an efficient framework for estimating the parameters of composite stochastic processes with the advantage of correlated noise identification and characterization.
Davide Vignotto
University of Trento, Italy
Title: Object release into free-fall: A technological challenge for in-space gravity wave detection
Biography:
Davide Vignotto is a PhD student at the University of Trento, Italy, where he graduated in Mechatronics Engineering. His master’s thesis focuses on the test mass release dynamics of the space mission LISA Pathfinder. He is interested in systems modelling and identification in the aerospace field. His research interest include: data analysis and systems identification.
Abstract:
LISA Pathfinder (LPF) is an ESA (European Space Agency) mission aimed at testing new technologies in the field of gravitational waves detection. The LPF scientific payload, the LISA Technology Package (LTP), contains two test masses (TMs) that must be set into free-fall inside their Gravitational Reference Sensors (GRS) with a minimum acceleration noise level, in order to provide the sensing bodies for the detection of gravitational waves. Driven by this requirement, the GRS design minimizes noisy forces by means of a strict control of the force budget and the adoption of large gaps between the TM and its electrode housing (EH). This however calls for a mechanism to secure the TM during the spacecraft launch and to release it to free fall for the science phase. The release maneuver is mission-critical and is performed by the grabbing positioning and release mechanism (GPRM), composed of two identical and opposed units which engage the TM by means of two plungers and release-dedicated tips. After a successful nominal and extended mission (2016-2017), due to its criticality for future missions (e.g. LISA), the GPRM release function has been intensively tested. The release performance of the GPRM can be estimated by the TM residual velocity after the disengagement, which should be minimal in order to allow the subsequent capture on behalf of the electrostatic actuation system. However, significant deviations occurred with respect to such a baseline, produced by unexpected configurations of the GPRM-TM system. The dedicated in-flight test campaign made it possible to understand some phenomena which produced such a behavior and formulate some risk-reduction strategies. In this work, the releases performed by the GPRM have been analyzed, focusing mainly on two aspects: i) studying the mechanical configuration of the system in pre-release phases and ii) evaluating the residual velocity of the TM after each release.
Zhang Rong Zhi
Xi’An Satellite Control Center, China
Title: Selection of optimum time for spacecraft collision avoidance operation
Biography:
Zhang Rong Zhi has her expertise in evaluation and passion in the spacecraft collision avoidance warning and operation. He leads a team for spacecraft collision warning and avoidance operation is Xi’an satellite control center about two decade. He is mainly interested in space missions.
Abstract:
More than 23,000 space objects around the earth orbits in total are regularly tracked by the space surveillance network and maintained in the catalogue, which cover objects whose size are larger than approximately 5 to 10 cm in low earth orbit (LEO). Most of these space objects, especially the size of only several centimeters, are called space debris which are very dangers for in-orbit operational spacecraft because of potential collision. Space debris collision avoidance has almost been a routine activity for incapable space powers for the purpose to ensure the security of their spacecraft operation. In view of the current engineering and technological basics, the confidence level of collision warning is still to be further improved. In engineering, both the ability of tracking space objects of surveillance network and the integrality of measuring data limit the accuracy of orbit determination of space objects. But according to current technologies, the prediction accuracy of orbit dynamics model, especially low orbit atmospheric model, seriously decreases the accuracy of precise orbit prediction with time prolongs. On one hand, the shorter the time duration between the prediction and potential and potential collision is, the higher confidence level of the collision avoidance warning will be. On the other hand, the preparation procedure of spacecraft maneuver and the power consumption budget require collision avoidance to be made earlier. This paper focuses on the selection of the optimum time for spacecraft collision avoidance operation.
Eman Fouad El-Said El-Nobi
South Valley University, Egypt
Title: Erythemal UV dose rate spatial distribution using ozone monitoring instrument satellite data over Egypt
Biography:
Eman Fouad El-Nobi is a Lecturer in Physics Department, Faculty of Science, South Valley University-Qena-Egypt, and has her expertise in Solar Radiation especially on Ultraviolet Radiation. She completed PhD in Atmospheric Physics at Faculty of Science, South Valley University, and her thesis is entitled as “Distribution of UV-index in some upper Egypt regions”.
Abstract:
The spatial distribution of Erythemal Ultraviolet Dose Rate (EUV) at noon in mW/m2 observations derived from the Ozone Monitoring Instrument (OMI) are presented over Egypt covering the geographical domain (22.5°–31.5°N, 25.5°–35.5°E) during twelve year from 2005 to 2015. In the frame of the variability, Egypt was considered as an average area (one pixel); the box-whisker plots were created for average monthly and annual values of EUV. The monthly mean of EUV values are lower in the winter months (December to February) 116.17±2.30 mW/m2 compared to those in the summer months (June to August) 282.36±2.87 mW/m2. The annual mean of EUV values are lower in 2015 (204.15±60.41 mW/m2) and higher in 2013 (213.13±60.34 mW/m2). For the purpose of mapping contour, with a spatial resolution of 1°×1°, 104 pixels, the results illustrated by monthly, seasonally and all period contour maps indicate high similarity of EUV in all years. Finally comparisons of ground-based measurement of Erythemal Ultraviolet Dose Rate (EUVpyr) using a UVB-1 pyranometer with Ultraviolet Dose Rate (EUVomi) from OMI satellite data have been examined in Qena, Upper Egypt (26° 16` N, 32° 75` E, 96 m asl) at noontime in mW/m2. The examination revealed an overestimation of EUVomi, on deviation average by 13.37±11%, within the period of study from 2006 to 2015 (except 2011-2012).