ConcurrentEngineering is a specialised work methodology based on the parallelization of tasks. The complete design team, composed of the various technical domain specialists, work on the different aspects of the project at the beginning of the design process. The methodology relies on identifying and parameterising dependencies between team members. Rapid gain of design consistency and overall project convergence is obtained with constant direct communication and data interchange. Results are achieved in a dramatically shorter time compared with a classical design approaches. This technique has been put to very good effect in Europe to assess the technical and financial feasibility of future space missions and new spacecraft concepts, space system trade-offs and options evaluation, new technology validation at system & mission level, requirements definition and consolidation. For example, the ESA Concurrent Design Facility (CDF) is routinely used for Phase 0 (pre-phase A studies); Large system integrators (LSI) also have established similar infrastructure for their own mission engineering tasks. Concurrent Design may be conducted as a manual process, which can be aided by the use of simple tools and techniques such linked spreadsheets. But it is most effective and efficient when supported by modern tools, such as J-CDS Concurrent Design Platform (CDP) and ESA's Open Concurrent Design Server (OCDS, under development), which not only support the process but are increasingly integrated with other external tools such as simulation frameworks, requirements management tools, and other system modelling environments. At this point, the artefacts of a concurrent design session become a design model; a set of integrated data products which can be reused in later phases of the project. These artefacts will eventually specify or influence the design of the mission components, spacecraft, payload and ground segment, which traditionally follow parallel (but independent) traditional development lifecycles. Concurrent design sessions at facilities such as CDF feature the strong interactions of a physically collocated team. The ESA CDF organises the studies in bi-weekly half day sessions with the participation of all disciplines needed. For a typical ESA study the ESA CDF holds between 6 to 10 sessions (i.e. 3 to 6 weeks). This paper explores the potential use of Concurrent Engineering techniques and tools throughout the whole lifecycle, supporting physically distributed teams. Phase 0 to B could effectively be classed as a single "design phase", which continues from initial concept to the finished design using the same specialists, tools and communication techniques. There is still a need for reviews and acceptance at different phases of the design which can be achieved by taking "snapshots" of the ongoing process and measuring the maturity of the desired products.The concurrent design tools are increasingly connected with system models for supporting the satellite, payload and simulator designs, which themselves manifest themse...

J-CDS and IHC Merwede have set up a programme to perform a hands-on introductory Concurrent Design (CD) Lite™ activity on a relevant subject. The goal of this CD Lite™ activity is to convey a first idea of the CD methodology to a selected team of IHC engineers. This activity will be evaluated to assess the potential and applicability of the full Concurrent Design methodology at IHC Merwede. Concurrent Design is a methodology for the early design phases. With a multidisciplinary team of stakeholders the design work is done in collocated sessions. The strong points of Concurrent Design are creating an integrated design in the form of parameters and enabling good communication and exchange of information between team members, including the customer. An activity consists of several clear phases: preparation, the collocated design sessions, followed by a reporting phase. The CD Lite™ activity consists of a preparation and two full days of sessions. The central questions for the sessions is to assess the scalability of two current trencher systems, a plough and a mechanical trencher, to cope with higher demands and requirements, most notably an increased target depth of the trench. The design is driven by reliability, availability and performance. In the sessions, the design team worked out two design options in three iterations and made comparisons between these to see in how far they are able to meet the requirements. The goal was achieved to provide some answers related to the trencher system questions for 2 options by performing 3 iterations per option. The main goal was achieved, i.e. in the short time of preparation and 2 days of sessions the CDLite™ experience has given the first insight to the design team and part of the management of IHC Merwede of the potential of Concurrent Design. The team members were positive about the CD methodology and the process. Positive remarks were given on the structured and transparent way of cooperation and the fast interaction that is possible with CD. The face to face communication was found very valuable. Having a team of experts in the room was perceived to be beneficial for the decision process. These experts can give a direct response to issues or problems, giving an insight on the impact of their decisions. Through working on a central database, it becomes clear what the relevant parameters in a design are in a design cycle. This approach is expected to improve the design process at IHC Merwede, especially in the field of innovative product developments that continue to push back the technical limitations in the maritime sector.

The Manufacturing Operations and Information System (MOIS) is the industry leading "Real World" software suite dedicated to Preparation, Management and Execution of Spacecraft Test and Flight Operations Procedures. It is well established as the standard system used within European Space Operations Centre (ESA/ESOC) and a range of other European operators. In addition, MOIS is widely used by Satellite and Instrument Primes for testing spacecraft and preparation of space segment deliverables. MOIS reached the milestones of 100 spacecraft and 50 independent missions in 2015 and the year also marked the release of MOIS-7 which provides major increases in functionality, capability and technology development as a comprehensive solution for all types of mission control configuration data. This paper focuses on ongoing further development which achieves a step-change increase in efficiency in the validation process of procedures by tackling a number of key areas where costs and inefficiencies remain across the space system development lifecycle. It adopts a holistic approach supported by a modern "model based" paradigm and the provision of a new generation of extremely flexible, model based support tools to support in the preparation, execution and management of Functional Verification at Subsystem and System level and Flight Operation Manuals.The tight coupling between Flight Operations Manual (FOM) and Functional Validation is also emphasised, supporting an overall validation process that covers both enabling efficient transfer to the operational team.