Ankara, Turkey
Ankara, Turkey

Roketsan is a major Turkish weapons manufacturer and defense contractor based in the central Anatolian province of Ankara. Incorporated in 1988 by Turkey's Defense Industry Executive Committee in order to establish the nation's industrial base on rocket technology, the company has quickly risen to become one of Turkey's top 500 industrial establishments. Roketsan's current share holders include TSKGV , Aselsan , MKEK , Kalekalıp , Vakıflar Bankası , Kutlutaş and Havelsan . Roketsan is best known for its vast range of unguided rockets as well as laser and infrared guided missiles such as Cirit and UMTAS. The company also produces subsystems for Stinger and Rapier missiles and provides technology and engineering solutions for other integrated civilian and military platforms.In 2013 Turkey approved the construction by Roketsan of its first satellite launching center, initially for low earth orbit satellites.Roketsan is the only Turkish company to have obtained CMMI/ DEV 3 approval for all its design and development processes. Wikipedia.


Time filter

Source Type

Grant
Agency: European Commission | Branch: H2020 | Program: RIA | Phase: NMP-19-2015 | Award Amount: 7.99M | Year: 2016

In the wind power generation, aerospace and other industry sectors there is an emerging need to operate in the low temperature and highly erosive environments of extreme weather conditions. Such conditions mean current materials either have a very short operational lifetime or demand such significant maintenance as to render many applications either very expensive to operate or in some cases non-viable. EIROS will develop self-renewing, erosion resistant and anti-icing materials for composite aerofoils and composite structures that can be adapted by different industrial applications: wind turbine blades and aerospace wing leading edges, cryogenic tanks and automotive facia. The addition of novel multi-functional additives to the bulk resin of fibre reinforced composites will allow the achievement of these advanced functionalities. Multi-scale numerical modelling methods will be adopted to enable a materials by design approach to the development of materials with novel structural hierarchies. These are capable of operating in severe operating environments. The technologies developed in this project will provide the partners with a significant competitive advantage. The modification of thermosets resins for use in fibre composite resins represents both a chemically appropriate and highly flexible route to the development of related materials with different applications. It also builds onto existing supply chains which are represented within the partnership and provides for European materials and technological leadership and which can assess and demonstrate scalability. The partnership provides for an industry led project with four specific end users providing both market pull and commercial drive to further progress the materials technology beyond the lifetime of the project.


This report studies Ground Based Ballistic Missile Defence Systems in Global market, especially in North America, Europe, China, Japan, Southeast Asia and India, focuses on top manufacturers in global market, with production, price, revenue and market share for each manufacturer, covering  Almaz Antey  ASELSAN AS  BAE Systems  Bharat Dynamics Limited  Bharat Electronics Limited  The Boeing Company  Eurosam GIE  Israel Aerospace Industries (IAI)  Kongsberg Gruppen ASA  Lockheed Martin Corporation  MBDA  Northrop Grumman Corporation  Orbital ATK Inc  Rafael Advanced Defense Systems  Raytheon Company  Roketsan  Saab Group Market Segment by Regions, this report splits Global into several key Regions, with production, consumption, revenue, market share and growth rate of Ground Based Ballistic Missile Defence Systems in these regions, from 2011 to 2021 (forecast), like  North America  Europe  China  Japan  Southeast Asia  India Split by product type, with production, revenue, price, market share and growth rate of each type, can be divided into  Type I  Type II  Type III Split by application, this report focuses on consumption, market share and growth rate of Ground Based Ballistic Missile Defence Systems in each application, can be divided into  Application 1  Application 2  Application 3 Global Ground Based Ballistic Missile Defence Systems Market Research Report 2016  1 Ground Based Ballistic Missile Defence Systems Market Overview  1.1 Product Overview and Scope of Ground Based Ballistic Missile Defence Systems  1.2 Ground Based Ballistic Missile Defence Systems Segment by Type  1.2.1 Global Production Market Share of Ground Based Ballistic Missile Defence Systems by Type in 2015  1.2.2 Type I  1.2.3 Type II  1.2.4 Type III  1.3 Ground Based Ballistic Missile Defence Systems Segment by Application  1.3.1 Ground Based Ballistic Missile Defence Systems Consumption Market Share by Application in 2015  1.3.2 Application 1  1.3.3 Application 2  1.3.4 Application 3  1.4 Ground Based Ballistic Missile Defence Systems Market by Region  1.4.1 North America Status and Prospect (2011-2021)  1.4.2 Europe Status and Prospect (2011-2021)  1.4.3 China Status and Prospect (2011-2021)  1.4.4 Japan Status and Prospect (2011-2021)  1.4.5 Southeast Asia Status and Prospect (2011-2021)  1.4.6 India Status and Prospect (2011-2021)  1.5 Global Market Size (Value) of Ground Based Ballistic Missile Defence Systems (2011-2021) 7 Global Ground Based Ballistic Missile Defence Systems Manufacturers Profiles/Analysis  7.1 Almaz Antey  7.1.1 Company Basic Information, Manufacturing Base and Its Competitors  7.1.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.1.2.1 Type I  7.1.2.2 Type II  7.1.3 Almaz Antey Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.1.4 Main Business/Business Overview  7.2 ASELSAN AS  7.2.1 Company Basic Information, Manufacturing Base and Its Competitors  7.2.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.2.2.1 Type I  7.2.2.2 Type II  7.2.3 ASELSAN AS Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.2.4 Main Business/Business Overview  7.3 BAE Systems  7.3.1 Company Basic Information, Manufacturing Base and Its Competitors  7.3.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.3.2.1 Type I  7.3.2.2 Type II  7.3.3 BAE Systems Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.3.4 Main Business/Business Overview  7.4 Bharat Dynamics Limited  7.4.1 Company Basic Information, Manufacturing Base and Its Competitors  7.4.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.4.2.1 Type I  7.4.2.2 Type II  7.4.3 Bharat Dynamics Limited Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.4.4 Main Business/Business Overview  7.5 Bharat Electronics Limited  7.5.1 Company Basic Information, Manufacturing Base and Its Competitors  7.5.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.5.2.1 Type I  7.5.2.2 Type II  7.5.3 Bharat Electronics Limited Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.5.4 Main Business/Business Overview  7.6 The Boeing Company  7.6.1 Company Basic Information, Manufacturing Base and Its Competitors  7.6.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.6.2.1 Type I  7.6.2.2 Type II  7.6.3 The Boeing Company Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.6.4 Main Business/Business Overview  7.7 Eurosam GIE  7.7.1 Company Basic Information, Manufacturing Base and Its Competitors  7.7.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.7.2.1 Type I  7.7.2.2 Type II  7.7.3 Eurosam GIE Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.7.4 Main Business/Business Overview  7.8 Israel Aerospace Industries (IAI)  7.8.1 Company Basic Information, Manufacturing Base and Its Competitors  7.8.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.8.2.1 Type I  7.8.2.2 Type II  7.8.3 Israel Aerospace Industries (IAI) Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.8.4 Main Business/Business Overview  7.9 Kongsberg Gruppen ASA  7.9.1 Company Basic Information, Manufacturing Base and Its Competitors  7.9.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.9.2.1 Type I  7.9.2.2 Type II  7.9.3 Kongsberg Gruppen ASA Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.9.4 Main Business/Business Overview  7.10 Lockheed Martin Corporation  7.10.1 Company Basic Information, Manufacturing Base and Its Competitors  7.10.2 Ground Based Ballistic Missile Defence Systems Product Type, Application and Specification  7.10.2.1 Type I  7.10.2.2 Type II  7.10.3 Lockheed Martin Corporation Ground Based Ballistic Missile Defence Systems Production, Revenue, Price and Gross Margin (2015 and 2016)  7.10.4 Main Business/Business Overview  7.11 MBDA  7.12 Northrop Grumman Corporation  7.13 Orbital ATK Inc  7.14 Rafael Advanced Defense Systems  7.15 Raytheon Company  7.16 Roketsan  7.17 Saab Group


Yumusak M.,Roketsan | Eyi S.,Middle East Technical University
Computers and Fluids | Year: 2012

The objective of this study is to develop a reliable and efficient design tool that can be used in chemically reacting flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. The finite rate chemistry model includes eight species and eleven reaction equations. These coupled equations are solved by using Newton's method. Both the numerical and the analytical methods are used to calculate the Jacobian matrices. Sensitivities are evaluated by using the adjoint method. The performance of the optimization method is demonstrated for rocket motor nozzle design. © 2012 Elsevier Ltd.


A multiple rocket launcher (MRL) or multiple launch rocket system (MLRS) is a type of rocket artillery system. Rockets have different capabilities than artillery, like longer range, and different payloads, for example considerably larger warheads, or multiple warheads. Unguided rocket artillery is notoriously inaccurate and slow to reload, compared to artillery. To overcome this, rockets are combined in systems that can launch multiple rockets simultaneously. Modern rockets can use GPS or inertial guidance, to combine the advantages of rockets with high accuracy. Scope of the Report:  This report focuses on the Multiple Rocket Launchers in Global market, especially in North America, Europe and Asia-Pacific, South America, Middle East and Africa. This report categorizes the market based on manufacturers, regions, type and application. Market Segment by Regions, regional analysis covers  North America (USA, Canada and Mexico)  Europe (Germany, France, UK, Russia and Italy)  Asia-Pacific (China, Japan, Korea, India and Southeast Asia)  South America, Middle East and Africa Market Segment by Applications, can be divided into  Military field  Other Global Multiple Rocket Launchers Market by Manufacturers, Regions, Type and Application, Forecast to 2021 1 Market Overview  1.1 Multiple Rocket Launchers Introduction  1.2 Market Analysis by Type  1.2.1 Tracked Rocket Launchers  1.2.2 Wheeled Rocket Launchers  1.2.3 Towed Rocket Launchers  1.3 Market Analysis by Applications  1.3.1 Military field  1.3.2 Other  1.3.3  1.4 Market Analysis by Regions  1.4.1 North America (USA, Canada and Mexico)  1.4.1.1 USA  1.4.1.2 Canada  1.4.1.3 Mexico  1.4.2 Europe (Germany, France, UK, Russia and Italy)  1.4.2.1 Germany  1.4.2.2 France  1.4.2.3 UK  1.4.2.4 Russia  1.4.2.5 Italy  1.4.3 Asia-Pacific (China, Japan, Korea, India and Southeast Asia)  1.4.3.1 China  1.4.3.2 Japan  1.4.3.3 Korea  1.4.3.4 India  1.4.3.5 Southeast Asia  1.4.4 South America, Middle East and Africa  1.4.4.1 Brazil  1.4.4.2 Egypt  1.4.4.3 Saudi Arabia  1.4.4.4 South Africa  1.4.4.5 Nigeria  1.5 Market Dynamics  1.5.1 Market Opportunities  1.5.2 Market Risk  1.5.3 Market Driving Force 2 Manufacturers Profiles  2.1 Lockheed Martin  2.1.1 Business Overview  2.1.2 Multiple Rocket Launchers Type and Applications  2.1.2.1 Type 1  2.1.2.2 Type 2  2.1.3 Lockheed Martin Multiple Rocket Launchers Sales, Price, Revenue, Gross Margin and Market Share  2.2 NORINCO GROUP  2.2.1 Business Overview  2.2.2 Multiple Rocket Launchers Type and Applications  2.2.2.1 Type 1  2.2.2.2 Type 2  2.2.3 NORINCO GROUP Multiple Rocket Launchers Sales, Price, Revenue, Gross Margin and Market Share  2.3 Splav  2.3.1 Business Overview  2.3.2 Multiple Rocket Launchers Type and Applications  2.3.2.1 Type 1  2.3.2.2 Type 2  2.3.3 Splav Multiple Rocket Launchers Sales, Price, Revenue, Gross Margin and Market Share  2.4 Roketsan  2.4.1 Business Overview  2.4.2 Multiple Rocket Launchers Type and Applications  2.4.2.1 Type 1  2.4.2.2 Type 2  2.4.3 Roketsan Multiple Rocket Launchers Sales, Price, Revenue, Gross Margin and Market Share  2.5 Avibras  2.5.1 Business Overview  2.5.2 Multiple Rocket Launchers Type and Applications  2.5.2.1 Type 1  2.5.2.2 Type 2 3 Global Multiple Rocket Launchers Market Competition, by Manufacturer  3.1 Global Multiple Rocket Launchers Sales and Market Share by Manufacturer  3.2 Global Multiple Rocket Launchers Revenue and Market Share by Manufacturer  3.3 Market Concentration Rate  3.3.1 Top 3 Multiple Rocket Launchers Manufacturer Market Share  3.3.2 Top 6 Multiple Rocket Launchers Manufacturer Market Share  3.4 Market Competition Trend 4 Global Multiple Rocket Launchers Market Analysis by Regions  4.1 Global Multiple Rocket Launchers Sales, Revenue and Market Share by Regions  4.1.1 Global Multiple Rocket Launchers Sales by Regions (2011-2016)  4.1.2 Global Multiple Rocket Launchers Revenue by Regions (2011-2016)  4.2 North America Multiple Rocket Launchers Sales and Growth (2011-2016)  4.3 Europe Multiple Rocket Launchers Sales and Growth (2011-2016)  4.4 Asia-Pacific Multiple Rocket Launchers Sales and Growth (2011-2016)  4.5 South America Multiple Rocket Launchers Sales and Growth (2011-2016)  4.6 Middle East and Africa Multiple Rocket Launchers Sales and Growth (2011-2016) 5 North America Multiple Rocket Launchers by Countries  5.1 North America Multiple Rocket Launchers Sales, Revenue and Market Share by Countries  5.1.1 North America Multiple Rocket Launchers Sales by Countries (2011-2016)  5.1.2 North America Multiple Rocket Launchers Revenue by Countries (2011-2016)  5.2 USA Multiple Rocket Launchers Sales and Growth (2011-2016)  5.3 Canada Multiple Rocket Launchers Sales and Growth (2011-2016)  5.4 Mexico Multiple Rocket Launchers Sales and Growth (2011-2016) 6 Europe Multiple Rocket Launchers by Countries  6.1 Europe Multiple Rocket Launchers Sales, Revenue and Market Share by Countries  6.1.1 Europe Multiple Rocket Launchers Sales by Countries (2011-2016)  6.1.2 Europe Multiple Rocket Launchers Revenue by Countries (2011-2016)  6.2 Germany Multiple Rocket Launchers Sales and Growth (2011-2016)  6.3 UK Multiple Rocket Launchers Sales and Growth (2011-2016)  6.4 France Multiple Rocket Launchers Sales and Growth (2011-2016)  6.5 Russia Multiple Rocket Launchers Sales and Growth (2011-2016)  6.6 Italy Multiple Rocket Launchers Sales and Growth (2011-2016)


Yumusak M.,Roketsan
Computers and Fluids | Year: 2013

The objective of this study is to develop a design tool that can be used in viscous flows. The flow analysis is based on the axisymmetric Navier-Stokes and k-e{open} turbulence equations. These coupled equations are solved using an explicit finite difference method. The accuracy of the analysis code is validated for viscous flows in solid rocket motor combustion chamber and nozzle. The gradient-based numerical optimization model is used to maximize the thrust of solid rocket motor under a constraint of propellant weight. The sensitivity analysis that measures the response of the flow with respect to a geometry perturbation is calculated by finite differencing. The optimization of design study employs a commercial optimization package. The performance of design optimization method is tested in solid rocket motor combustion chamber and nozzle design. © 2013 Elsevier Ltd.


Tekin R.,Roketsan
2010 8th IEEE International Conference on Control and Automation, ICCA 2010 | Year: 2010

This paper presents usage of to software programs, MATLAB and LabVIEW, for designing a motion control system and provides a brief look on the issue from the control system designer's level. Firstly, mathematical moedeling and controller for a motion control system including permanent magnet brush type direct current motor and gear head is given with MATLAB and then suitable hardware for specific purposes is mentioned. Afterwards, real time control of the system is presented with LabVIEW FPGA and LabVIEW RT (real time). © 2010 IEEE.


Erer K.S.,Roketsan | Merttopcuoglu O.,Roketsan
Journal of Guidance, Control, and Dynamics | Year: 2012

Nonlinear equations representing the BPPN (Biased Pure Proportional Navigation) kinematics with a stationary target were solved in closed form. The solution indicates that capture does not occur for high bias values due to the rapidly diverging look angle. As implied by the integrated form of the guidance law, it can be used to control the impact angle by adjusting the integral of bias. The two-phase guidance scheme uses bias action to postpone the rotating of the pursuer's velocity vector to target until the required bias integral value is reached. Simulation studies indicate the robustness of the method against seeker noise. Furthermore, adverse effects of velocity change can be avoided with the proposed velocity weighting.


Cimen T.,Roketsan
Journal of Guidance, Control, and Dynamics | Year: 2012

Survey of state-dependent Riccati equation (SDRE) in Nonlinear optimal feedback control synthesis is presented. The aim is to reflect the rapid growth and strong interest in the field of SDRE paradigm by providing control theoreticians and practitioners with a balance between the theoretical developments, systematic design tools, and real-time implementation prospects of SDRE control methodology. In dealing with internal parameter variations, the ability of SDRE design methods to adapt controller gains in real time based on the SDC pair can be viewed as an equivalent approach to the adaptive control design paradigm. The SDRE method avoids cancellations due to the suboptimality property of the method. Extensive simulation results also show that SDRE controllers exhibit robustness against parametric uncertainties/variations and unmodeled dynamics, and they attenuate disturbances.


Since the 1990s, state-dependent Riccati equation (SDRE) strategies have emerged as general design methods that provide a systematic and effective means of designing nonlinear controllers, observers and filters. These methods overcome many of the difficulties and shortcomings of existing methodologies, and deliver computationally simple algorithms that have been highly effective in a variety of practical and meaningful applications in very diverse fields of study. These include missiles, aircraft, unmanned aerial vehicles, satellites and spacecraft, ships, autonomous underwater vehicles, automotive systems, biomedical systems, process control, and robotics, along with various benchmark problems, as well as nonlinear systems exhibiting several interesting phenomena such as parasitic effects of friction and backlash, unstable nonminimum-phase dynamics, time-delay, vibration and chaotic behavior. SDRE controllers, in particular, have become very popular within the control community, providing attractive stability, optimality, robustness and computational properties, making real-time implementation in feedback form feasible. However, despite a documented history of SDRE control in the literature, there is a significant lack of theoretical justification for logical choices of the design matrices, which havedepended on intuitive rules of thumb and extensive simulation for evaluation and performance. In this paper, the capabilities and design flexibility of SDRE control are emphasized, addressing the issues onsystematic selection of the design matrices and going into detail concerning the art of systematicallycarrying out an effective SDRE design for systems that both do and do not conformto the basic structureand conditions required by the method. Several situations that prevent the direct application of the SDRE technique, such as the presence of control and state constraints, are addressed, demonstrating how these situations can be readily handled using the method. In order to provide a clear understanding of the proposed methods, systematic and effective design tools of SDRE control are illustrated on a singleinverted pendulum nonlinear benchmark problem and a practical application problem of optimally administering chemotherapy in cancer treatment. Lastly, real-time implementation aspects are discussed with relevance to practical applicability. © Since the 1990s, state-dependent Riccati equation (SDRE) strategies have emerged as general design methods that provide a systematic and effective means of designing nonlinear controllers, observers and filters. These methods overcome many of the difficulties and shortcomings of existing methodologies, and deliver computationally simple algorithms that have been highly effective in a variety of practical and meaningful applications in very diverse fields of study. These include missiles, aircraft, unmanned aerial vehicles, satellites and spacecraft, ships, autonomous underwater vehicles, automotive systems, biomedical systems, process control, and robotics, along with various benchmark problems, as well as nonlinear systems exhibiting several interesting phenomena such as parasitic effects of friction and backlash, unstable nonminimum-phase dynamics, time-delay, vibration and chaotic behavior. SDRE controllers, in particular, have become very popular within the control community, providing attractive stability, optimality, robustness and computational properties, making real-time implementation in feedback form feasible. However, despite a documented history of SDRE control in the literature, there is a significant lack of theoretical justification for logical choices of the design matrices, which have depended on intuitive rules of thumb and extensive simulation for evaluation and performance. In this paper, the capabilities and design flexibility of SDRE control are emphasized, addressing the issues on systematic selection of the design matrices and going into detail concerning the art of systematically carrying out an effective SDRE design for systems that both do and do not conformto the basic structure and conditions required by the method. Several situations that prevent the direct application of the SDRE technique, such as the presence of control and state constraints, are addressed, demonstrating how these situations can be readily handled using the method. In order to provide a clear understanding of the proposed methods, systematic and effective design tools of SDRE control are illustrated on a singleinverted pendulum nonlinear benchmark problem and a practical application problem of optimally administering chemotherapy in cancer treatment. Lastly, real-time implementation aspects are discussed with relevance to practical applicability. © 2010 Elsevier Ltd.


Cimen T.,Roketsan
IFAC Proceedings Volumes (IFAC-PapersOnline) | Year: 2011

The fundamental objective of autopilot design for missile systems is to provide stability with satisfactory performance and robustness over the whole range of flight conditions throughout the entire flight envelope that missiles are required to operate in, during all probable engagements. Depending on the control mode (skid-to-turn or bank-to-turn), intercept scenario (such as surface to surface, surface to air, air to air) and mission phase (launch, midcourse, terminal), missile autopilots can command accelerations, body rates, incidence angles, or flight path angles. To this end, classical and modern multivariable techniques from linear control theory combined with gain scheduling have dominated missile autopilot design over the past several decades. In this paper, the concept of extended linearization (also known as state-dependent coefficient parameterization) is examined for state-dependent nonlinear formulation of the vehicle dynamics in a novel and very general form for the development of a generic and practical autopilot design approach for missile flight control systems. Any extended linearization control method, such as the currently popular State-Dependent Riccati Equation (SDRE) methods, can then be applied to this state-dependent formulation for missile flight control system design. The unique contribution of this paper is the novel use of a very general and realistic nonlinear aerodynamic model that captures all major aerodynamic nonlinearities attributed to missiles, together with the fully nonlinear and coupled 6-DOF equations of motion of rigid-body missile dynamics for full-envelope, 3-axes nonlinear autopilot design, without invoking any of the usual simplifying assumptions of the traditional linear design philosophy, and independent of any flight or trim conditions. Moreover, in the development of the generic approach, all the autopilot command structures mentioned above are incorporated in one compact topology. Practical considerations such as actuator dynamics and actuator position and rate saturation are also included in the development of the nonlinear autopilot. The proposed approach has been implemented and its performance and robustness validated in detailed 6-DOF simulations in three dimensional environments, using various missile configurations with stable, unstable and nonminimum-phase characteristics. © 2011 IFAC.

Loading Roketsan collaborators
Loading Roketsan collaborators