OHB Sweden AB

Solna, Sweden

OHB Sweden AB

Solna, Sweden
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Agency: European Commission | Branch: H2020 | Program: ECSEL-RIA | Phase: ECSEL-07-2015 | Award Amount: 20.53M | Year: 2016

Embedded systems have significantly increased in technical complexity towards open, interconnected systems. This has exacerbated the problem of ensuring dependability in the presence of human, environmental and technological risks. The rise of complex Cyber-Physical Systems (CPS) has led to many initiatives to promote reuse and automation of labor-intensive activities. Two large-scale projects are OPENCOSS and SafeCer, which dealt with assurance and certification of software-intensive critical systems using incremental and model-based approaches. OPENCOSS defined a Common Certification Language (CCL), unifying concepts from different industries to build a harmonized approach to reduce time and cost overheads, via facilitating the reuse of certification assets. SafeCer developed safety-oriented process lines, a component model, contract-based verification techniques, and process/product-based model-driven safety certification for compositional development and certification of CPSs. AMASS will create and consolidate a de-facto European-wide assurance and certification open tool platform, ecosystem and self-sustainable community spanning the largest CPS vertical markets. We will start by combining and evolving the OPENCOSS and SafeCer technological solutions towards end-user validated tools, and will enhance and perform further research into new areas not covered by those projects. The ultimate aim is to lower certification costs in face of rapidly changing product features and market needs. This will be achieved by establishing a novel holistic and reuse-oriented approach for architecture-driven assurance (fully compatible with standards e.g. AUTOSAR and IMA), multi-concern assurance (compliance demonstration, impact analyses, and compositional assurance of security and safety aspects), and for seamless interoperability between assurance/certification and engineering activities along with third-party activities (external assessments, supplier assurance).

Kleimark J.,KTH Royal Institute of Technology | Delanoe R.,OHB Sweden AB | Demaire A.,OHB Sweden AB | Brinck T.,KTH Royal Institute of Technology
Theoretical Chemistry Accounts | Year: 2013

The decomposition pathways of ionized ammonium dinitramide (ADN) have been analyzed using the B3LYP and the M06-2X density functional theory methods, coupled cluster theory and the composite CBS-QB3 method. Ionization and subsequent decomposition of the major decomposition products have also been studied. The ADN+ ion dissociates into the stable DN radical and NH4+ with a dissociation enthalpy of 50 kJ/mol. The subsequently formed DN+ ion has an activation enthalpy of 102 kJ/mol for decomposition into N2O, O2 and NO+. A competing pathway for ionization and decomposition of ADN involves the HDN+ ion, which dissociates into NO2 and HNNO2 with a barrier of only 17 kJ/mol. The ionization product HNNO2 is stable toward further decomposition, and the barrier for isomerization to HONNO+ is 167 kJ/mol. The computed adibatic ionization potentials of ADN, HDN, DN and HNNO2 are 9.4, 11.5, 10.2 and 10.9 eV, respectively. The results of the study have implications for the future use of ADN in propellants for electromagnetic space propulsion. © Springer-Verlag Berlin Heidelberg 2013.

Bodin P.,OHB Sweden AB | Noteborn R.,OHB Sweden AB | Larsson R.,OHB Sweden AB | Karlsson T.,OHB Sweden AB | And 4 more authors.
Advances in the Astronautical Sciences | Year: 2012

The PRISMA in-orbit testbed was launched on June 15, 2010 to demonstrate strategies and technologies for formation flying and rendezvous. OHB Sweden (OHB-SE) is the prime contractor for the project which is funded by the Swedish National Space Board with additional support from the German Aerospace Center (DLR), the French National Space Center (CNES), and the Technical University of Denmark (DTU). In August 2011, PRISMA completed its nominal mission and during the fall of 2011, several additional activities have been performed under a mission extension program. The mission qualifies a series of sensor and actuator systems including navigation using GPS, Vision Based and RF technology as well as a propulsion system based on environmentally friendly propellant technology. The mission also includes a series of GNC experiments using this equipment in closed loop. Separate experiments are implemented by OHB-SE, DLR, and CNES and the paper provides an overview and conclusions from the nominal mission flight results from these experiments.

Rathsman P.,OHB Sweden | Demaire A.,OHB Sweden AB | Rezugina E.,OHB Sweden AB | Lubberstedt H.,OHB System AG | De Tata M.,OHB System AG
Proceedings of the International Astronautical Congress, IAC | Year: 2013

In September 2003, ESA launched the lunar probe SMART-1. Using a single electric thruster providing only 70 mN of thrust, SMART-1 traversed the radiation belts under the worst solar storm conditions ever recorded to successfully reach the Moon in November 2004. Ten years later, the legacy of SMART-1 has been an important contributor to the implementation of the Electra programme, aimed at developing Europe's first all-EP telecommunications satellite. Thanks to the significant mass saving offered by electric propulsion, Electra will be able to host the same payload capability as traditional mid-sized telecom satellites, whilst achieving a much lower launch mass. The paper discusses the challenges associated with the implementation of all-electric propulsion on telecom satellites, and explains how the experiences of SMART-1 and other relevant missions have contributed to Electra. The first Electra mission is planned to be launched in the 2018-2019 timeframe.

Karlsson T.,OHB Sweden AB | Ahlgren N.,OHB Sweden AB | Faller R.,German Aerospace Center | Schlepp B.,German Aerospace Center
SpaceOps 2012 Conference | Year: 2012

The PRISMA in-orbit test-bed was launched in June 2010 to demonstrate strategies and technologies for formation flying and rendezvous. OHB Sweden is the prime contractor for the project which is funded by the Swedish National Space Board (SNSB) with support from DLR, CNES, and DTU. Mission operations are carried out from OHB Sweden's purpose built control-room in Solna, Sweden, using the company's own GNC and platform experts to conduct the mission. As an experimental technology demonstrator a large number of in-orbit experiments were initially planned, with desires exceeding the constraints of available funding. In an effort to extend the use of the satellites and enable more experiments DLR/GSOC offered to temporarily operate the satellites from their control center in Oberpfaffenhofen, Germany, for a period of five months. Control of the spacecraft was transferred to GSOC in March, 2011, after a training period of several months. A number of experiments were executed, including GSOC's own formation flying and autonomous orbit keeping, SSC ECAPS's green propulsion and several different OHB Sweden experiments. Handover back to OHB Sweden was then performed in August the same year, from where the mission continues to be run. Transferring control of a satellite project from one organization to another, including new operational personnel and a new control room, posed a great challenge to both parties. This paper describes the mission concept, the background for the transfer, implementation of a mirrored control room and the process of transferring knowledge from the design and operations team of OHB Sweden to the GSOC operations team. © 2012 by OHB-Sweden AB.

Agency: European Commission | Branch: FP7 | Program: CSA-SA | Phase: SPA.2009.2.4.01 | Award Amount: 741.07K | Year: 2010

The general objective of the current project is to create the necessary conditions for utilizing the existing and emerging potential of the consortium partners in Nordic-Baltic dimension for continuous and sustainable contribution in major on-going and planned European space programmes. There is urgent need in emerging space countries for national space programme. For emerging space countries it could be primarily financed by the ESA PECS Charter but also by key governmental agencies. The NordicBaltSat has mission-oriented approach to build a bridge for successful integration into space industry in Europe. As a result of this project and as an overall impact emerging space countries are expected to raise their space capacities in order to access to ESA and to have contribution to European space programmes in future. There are several specific actions contributing to achieve the objectives of the project. The main actions intend to chart space potential and create joint technology programme; to build capacity and develop cooperation between emerging space countries and ESA; and to shape national space governance systems in emerging space countries. The activities include also dissemination and exploitation. These actions will enhance the potential of FP7 States to make a continuous and sustainable contribution to major on-going and planned European space programs. Capacity building and cooperation promotion between emerging space countries and ESA will strengthen the relationship with ESA and it also gives opportunity for future cooperation and adhesion to ESA. The actions will foster dialogue and debate on space science and research with the public beyond the research community, aiming at embracing a new generation of scientists and engineers.

Mateo-Velez J.-C.,ONERA | Theillaumas B.,Airbus | Sevoz M.,Airbus | Andersson B.,OHB Sweden AB | And 7 more authors.
IEEE Transactions on Plasma Science | Year: 2015

Spacecraft charging in GEO particularly concerns dielectric surfaces that may charge to significant voltages relative to spacecraft ground because of the space environment. Testing materials helps to define the level of risk and to maintain confidence in a spacecraft's immunity to damaging effects. Another factor defining the risk involves numerical simulation of spacecraft charging. Several tools aim to calculate surface charging, which is particularly hazardous in harsh environments produced by geomagnetic sub storms, where particles in the energy range of a few to hundreds of kiloelectronvolts are present. The main codes include Nascap-2k, Spacecraft plasma Interaction Software (SPIS), MUSCAT, and Coulomb-2. They use different numerical and sometimes physical models and cross checking their results is a necessary process to achieve better confidence in simulations performed by spacecraft prime manufacturers. The objective of this paper is to simulate different GEO spacecraft configurations with NASA Charging Analyzer Program at geosynchronous orbits (a 1980s to 1990s predecessor to Nascap-2k) and SPIS and to compare the results, both in terms of absolute and differential potentials. The first section concerns the SCATHA spacecraft. The second part of this paper compares efforts to model a modern telecom spacecraft. Finally, we conclude on the reliability of the simulations performed and possible areas for modeling improvement. © 1973-2012 IEEE.

Chasset C.,OHB Sweden AB | Noteborn R.,OHB Sweden AB | Bodin P.,OHB Sweden AB | Larsson R.,OHB Sweden AB | Jakobsson B.,OHB Sweden AB
CEAS Space Journal | Year: 2013

PRISMA implements guidance, navigation and control strategies for advanced formation flying and rendezvous experiments. The project is funded by the Swedish National Space Board and run by OHB-Sweden in close cooperation with DLR, CNES and the Danish Technical University. The PRISMA test bed consists of a fully manoeuvrable MANGO satellite as well as a 3-axis controlled TANGO satellite without any ΔV capability. PRISMA was launched on the 15th of June 2010 on board DNEPR. The TANGO spacecraft is the reference satellite for the experiments performed by MANGO, either with a "cooperative" or "non-cooperative" behaviour. Small, light and low-cost were the keywords for the TANGO design. The attitude determination is based on Sun sensors and magnetometers, and the active attitude control uses magnetic torque rods only. In order to perform the attitude manoeuvres required to fulfil the mission objectives, using any additional gravity gradient boom to passively stabilize the spacecraft was not allowed. After a two-month commissioning phase, TANGO separated from MANGO on the 11th of August 2010. All operational modes have been successfully tested, and the pointing performance in flight is in accordance with expectations. The robust Sun Acquisition mode reduced the initial tip-off rate and placed TANGO into a safe attitude in <30 min. The Manual Pointing mode was commissioned, and the spacecraft demonstrated the capability to follow or maintain different sets of attitudes. In Sun/Zenith Pointing mode, TANGO points its GPS antenna towards zenith with sufficient accuracy to track as many GPS satellites as MANGO. At the same time, it points its solar panel towards the Sun, and all payload equipments can be switched on without any restriction. This paper gives an overview of the TANGO Attitude Control System design. It then presents the flight results in the different operating modes. Finally, it highlights the key elements at the origin of the successful 3-axis magnetic control strategy on the TANGO satellite. © 2013 CEAS.

Ahlgren N.,OHB Sweden AB | Karlsson T.,OHB Sweden AB | Larsson R.,OHB Sweden AB | Noteborn R.,OHB Sweden AB
SpaceOps 2012 Conference | Year: 2012

The PRISMA in-orbit test-bed was launched in June 2010 to demonstrate strategies and technologies for formation flying and rendezvous. OHB Sweden is the prime contractor for the project which is funded by the Swedish National Space Board (SNSB) with support from DLR, CNES, and DTU. In early September of 2011, 15 months after launch, all primary mission objectives of the PRISMA formation flying satellites had been achieved and mission success was declared. Since a significant amount of delta-V capability still remained an open call for new experiments was issued, inviting both old and new experimenters to use the capabilities of the formation. Several interested parties took the opportunity to perform their own experiments with an existing platform, each coming with new mission objectives not previously planned to be flown on the PRISMA satellites. Some of these experiments were close to what had already been achieved within the nominal mission, but some included new ways of using the formation not envisioned by the spacecraft designers. The new experiments span from data collection in specific relative orbits, with a separation from a few meters to several kilometers, to entirely new modules within the on-board software. Changing from a pre-planned technology demonstration mission to operating a commercial resource required adaptation of the original operational concept, taking into account the different levels of experience of the customers and managing the satellites between experiments. This paper describes how these new mission objectives were integrated in operations and how a sometimes very short turn-around between initial concept and experiment execution was implemented with the aid of well established validation processes, high degrees of on-board autonomy and a flexible operations team. © 2012 by OHB-Sweden AB.

Battelino M.,OHB Sweden AB | Svard C.,OHB Sweden AB
SpaceOps 2012 Conference | Year: 2012

RAMSES (Rocket and Multi Satellite EMCS Software) was developed in-house at OHB Sweden (former Space Systems Division at SSC) and has during the past years served a number of different space related projects; e.g. the PRISMA satellite formation flying project at OHB Sweden and DLR GSOC in Germany, the Russian scientific satellite project FOTON-M3 and the sounding rocket programs MASER and MAXUS. Common to all projects is that the RAMSES ground system is used throughout the whole project from development and test up to and including its mission phase. RAMSES is especially suited for projects with short timelines and where cost efficiency is an important driver. The system is deployed within minutes and executes on standard PC hardware. The adaptation of the system to new missions is generally only a matter of populating the system database with mission specific telemetry and telecommand definitions. The functionality within RAMSES is distributed between a number of standalone application nodes executing on one or several PC machines connected to the network. This paper will focus on the design, functionality and advantages of RAMSES compared with other systems on the market. Newly developed functionality concerning archiving and extraction of large amount of data is described. The role of RAMSES through the different phases of the small satellite project PRISMA is also presented. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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