Scientific Program

Conference Series Ltd invites all the participants across the globe to attend 4th International Conference and Exhibition on Satellite & Space Missions Rome, Italy.

Day 2 :

Keynote Forum

Giancarlo Genta

Politecnico di torino, Italy

Keynote: Solar electric spacecraft for human Mars missions

Time : 09:05-09:40

OMICS International Satellite 2018 International Conference Keynote Speaker Giancarlo Genta photo
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.

OMICS International Satellite 2018 International Conference Keynote Speaker Daniele Bortoluzzi photo
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.

Break: Networking & Refreshment Break 10:15-10:30 @ Foyer

Keynote Forum

Ryspek Usubamatov

Kyrgyz State Technical University, Kyrgyzstan

Keynote: P-MMGP: Physics And Mathematical Models for Gyroscope Properties
OMICS International Satellite 2018 International Conference Keynote Speaker Ryspek Usubamatov photo
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.

OMICS International Satellite 2018 International Conference Keynote Speaker Alexander V Nebylov photo
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.