Conceptual data model: A foundation for successful concurrent engineering

Fischer, Philipp M.; Deshmukh, Meenakshi; Maiwald, Volker; Quantius, Dominik; Gomez, Antonio Martelo; Gerndt, Andreas

doi:10.1177/1063293x17734592

Cited by 19 publications

(13 citation statements)

References 14 publications

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“…This approach allows a rapid and easy evaluation about the suitability of the proposed option for each subsystem and its influence on the designs of the rest of subsystems. Various works have applied this concept for the design of space systems in different projects (Avnet and Weigel, 2010;Bacchetti et al, 2001;Fischer et al, 2018;Imhof, 2007;Kempf et al, 2016;Raab et al, 2016).…”

Section: Concurrent Designmentioning

confidence: 99%

Optimum preliminary design of ion thrusters in concurrent design facility

García-Pérez

2020

Concurrent Engineering

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In recent years, the development of new satellites has accelerated, especially for small satellites like university-class Cubesats, due to low design and manufacturing costs. The preliminary design of these spacecraft requires the utilization of new tools that improve the interrelation among the different subsystems and optimize the design. One of the most suitable approaches is the concurrent design facility, which connects specialists of each subsystem in the same room to facilitate the communication among them. This method provides different preliminary designs for the complete system by an iterative process in a reduced time, taking into account the simultaneity with the designs of the subsystems. One of the main subsystems of a spacecraft is the propulsion system, which plays a key role in the success of a mission by allowing the spacecraft to reach the final destination. Electric propulsion has become an interesting option due to the high value of the specific impulse, which provides the necessary velocity increment with a lower propellant mass compared to the traditional chemical rockets. The purpose of this paper is to present the equations implemented in the propulsion module of the concurrent design facility to obtain optimum designs of ion thrusters, which supposes a novelty compared to the traditional design approach of these systems, where there is no interaction with the design of the rest of subsystems. The objective is to help the designer to select the best options in a fast and easy way and improve the efficiency of the iterative work of the concurrent design facility.

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Section: Concurrent Designmentioning

confidence: 99%

Optimum preliminary design of ion thrusters in concurrent design facility

García-Pérez

2020

Concurrent Engineering

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“…Which information has to be gathered at which time? [6] At DLR such a study is supported by a Model Based Systems Engineering (MBSE) process. It requires inviting around twelve engineers from design critical domains.…”

Section: Related Work To Ce Process and Data Modelingmentioning

confidence: 99%

“…This rights management helps keeping the system model consistent. [6] Virtual Satellite constantly analyzes the system model and provides instant feedback to the engineers [2].…”

Section: Related Work To Ce Process and Data Modelingmentioning

confidence: 99%

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Spacecraft Interface Management in Concurrent Engineering Sessions

Fischer

Lange

Maiwald

et al. 2019

Lecture Notes in Computer Science

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This paper contributes to the topic of spacecraft interface and data rate management in Concurrent Engineering (CE) sessions. At DLR, CE is used together with a CE process for designing new spacecraft. The software Virtual Satellite supports this process. It provides a shared system model to the engineers to exchange design information. Until today, it supports the structural decomposition of the system and the analysis of design drivers such as the mass or power consumption of the spacecraft. During one of the S2TEP studies for a multi-mission platform it was required to have a closer look to power and data interfaces. This paper discusses the state of the art to this topic and derives a generic approach to it. This approach is customized and nally implemented in Virtual Satellite and directly applied in the S2TEP study.

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“…A detailed description of the CE process as applied by DLR in Bremen can be found in [7] and [8]. More information on the data model used by DLR for these studies is presented in [9].…”

Section: Concurrent Engineering: From Concept To Designmentioning

confidence: 99%

Orbital Hub: a concept for human spaceflight beyond ISS operations

et al. 2018

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The International Space Station (ISS) is the greatest endeavour in low Earth orbit since the beginning of the space age and the culmination of human outposts like Skylab and Mir. While a clear schedule has yet to be drafted, it is expected that ISS will cease operation in the 2020s. What could be the layout for a human outpost in LEO with lessons learnt from ISS? What are the use cases and applications of such an outpost in the future? The System Analysis Space Segment (SARA) group of the German Aerospace Center (DLR) investigated these and other questions and developed the Orbital Hub concept. In this paper an overview is presented of how the overall concept has been derived and its properties and layout are described. Starting with a workshop involving the science community, the scientific requirements have been derived and strawman payloads have been defined for use in further design activities. These design activities focused on Concurrent Engineering studies, where besides DLR employees also participants from industry and astronauts were involved. The result is an expandable concept that is composed of two main parts, the Base Platform, home for a permanent crew of up to 3 astronauts, and the Free Flyer, an uncrewed autonomous research platform. This modular approach provides one major advantage: the decoupling of the habitat and payload leading to increased quality of the micro gravity environment. The former provides an environment for human physiology experiments, while the latter allows science without the perturbations caused by a crew, e.g. material experiments or Earth observation. The Free Flyer is designed to operate for up to 3 months on its own, but can dock with the space station for maintenance and experiment servicing. It also has a hybrid propulsions system, chemical and electrical, for different applications. The hub's design allows launch with just three launches, as the total mass of all hub parts is about 60,000 kg. The main focus of the design is on autonomy and reducing crew maintenance and repair efforts, and reducing the need for extravehicular activities. Following a description of the design approach and technical details, a cost estimation and a detailed discussion of the use cases for such a station concept, along with the possible scenarios of international cooperation, are also presented in this paper.

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Conceptual data model: A foundation for successful concurrent engineering

Cited by 19 publications

References 14 publications

Optimum preliminary design of ion thrusters in concurrent design facility

Optimum preliminary design of ion thrusters in concurrent design facility

Spacecraft Interface Management in Concurrent Engineering Sessions

Orbital Hub: a concept for human spaceflight beyond ISS operations

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