scholarly journals Kilowatt Reactor Using Stirling TechnologY (KRUSTY) Demonstration. CEDT Phase 1 Preliminary Design Documentation

2015 ◽  
Author(s):  
Rene Gerardo Sanchez ◽  
Jesson D. Hutchinson ◽  
Patrick Ray Mcclure ◽  
William L. Myers
Keyword(s):  
Phase 1 ◽  
Preliminary Design ◽  
Design Documentation

scholarly journals Geometric modeling and development of custom libraries in the design of engineering facilities

2020 ◽  
pp. 1-7
Author(s):  
Elena Sergeevna Reshetnikova ◽  
Irina Aleksandrovna Savelyeva ◽  
Ekaterina Anatolyevna Svistunova
Keyword(s):  
Design Process ◽  
Computer Aided Design ◽  
Geometric Modeling ◽  
Three Dimensional ◽  
3D Models ◽  
Conveyor Belt ◽  
General Idea ◽  
Design Stage ◽  
Preliminary Design ◽  
Design Documentation

The subject of research is the process of designing a conveyor belt. The authors consider parameterization in geometric modeling of parts and components of equipment and the creation of custom libraries in Compass 3D as a means of reducing the complexity and improving the quality of the design process. The preliminary design is the design stage of the development of design documentation and aims to determine the fundamental design solutions for a general idea of the device, operating principles and dimensions of the product. It is advisable to develop a preliminary design before the stage of developing a technical project and creating design documentation. Today, at all stages of work on the project, modern computer-aided design (CAD) systems are used, which not only accelerate the design process, but also make it possible to demonstrate to the customer the finished project at the stage of making technical decisions. This allows making timely changes in accordance with the requirements of the customer and to carry out high-quality preparation of the project for its implementation. The volume and time for further stages of work depend on the timing of the presentation of the preliminary design, therefore, the use of three-dimensional modeling parametrization in CAD is an effective way for designing engineering objects. Parameterization when working with 3D models allows you to get a set of typical product designs based on a once-created model by changing the set values of the variables, which significantly reduces the time spent on the project.

scholarly journals CERBERUS: CEDT Phase-1 Preliminary Design for Cu Critical Experiment

2021 ◽  
Author(s):  
Kelsey Amundson ◽  
Theresa Cutler ◽  
Robert Little ◽  
Joetta Goda ◽  
Jesson Hutchinson ◽  
...  
Keyword(s):  
Phase 1 ◽  
Preliminary Design ◽  
Critical Experiment

Improving design and documentation by using partially automated synthesis

1994 ◽  
Vol 8 (4) ◽  
pp. 335-354 ◽  
Author(s):  
A. Cristina Bicharra Garcia ◽  
H. Craig Howard ◽  
Mark J. Stefik
Keyword(s):  
Parametric Design ◽  
Preliminary Design ◽  
Community Practice ◽  
Design Rationale ◽  
Running System ◽  
Requirements Change ◽  
Design Documentation ◽  
Design Documents ◽  
Air Conditioning Systems ◽  
Project Life

AbstractOne of the products of engineering, besides constructed artifacts, is design documentation. To understand how design participants use documentation, designers and typical documentation users were interviewed and protocols were taken of them both creating and using design documentation. The protocols were taken from realistic projects of preliminary design for heating, ventilation, and air conditioning systems (HVAC). The studies of document creation and use revealed three important issues: (1) design participants not only look up design facts; they frequently access documents to obtain information about the rationale for design decisions; (2) the design rationale that they see often is missing from the documents; and (3) design requirements change frequently over a project life cycle so that design documents are often inconsistent and out of date. Recognizing these documentation issues in design practice, a new approach was developed in which documents are no longer static records, but rather interactive design models supporting a case. The feasibility of the approach was demonstrated by constructing a running system and testing it with designers on realistic problems. The costs and benefits of creating and using documentation of design rationale also were analyzed. In particular, the active documents approach was evaluated for a routine, preliminary design in domains where community practice is widely shared and largely standardized. The approach depends on the feasibility of creating a parametric design model for the design domain.

Research and selection of MALE wing profile

2019 ◽  
Vol 91 (2) ◽  
pp. 264-271 ◽  
Author(s):  
Cezary Gorniak ◽  
Zdobyslaw Jan Goraj ◽  
Bartosz Olszanski
Keyword(s):  
Wind Tunnel ◽  
Early Stage ◽  
Phase 1 ◽  
Lift Coefficient ◽  
High Volume ◽  
Aerodynamic Characteristics ◽  
Preliminary Design ◽  
Content Type ◽  
Wing Section ◽  
Selection Of

Purpose The purpose of this research is a preliminary selection of wing section, which would be the best suited for PW-100 – a MALE class UAV of 600 kg weight. PW-100 will be used as a testing platform in different institutions such as research institutes, industry research centers or universities of technology (phase 1) to enable the in-flight testing of various on-board systems (mobile radars, thermovision sensors, chemical sensors, antennas, teledetection systems and others). Untypical layout of PW-100 resulted from the plans of further development of this configuration for a military application. Design/methodology/approach Important role in the research described in this paper plays the selection of main wing section to fulfil the preliminary requirements regarding maximum lift coefficient, minimum drag, aerodynamic efficiency etc. Two different wing sections (R1082 and SA19) were tested in wind tunnel, both with flaps deflected at the range of 0°-30°. Experimental measurements were performed in the low turbulence wind tunnel with closed test section of 45 cm × 35 cm. Numerical simulations of the flow around the wing sections were performed using MSES code. Boundary conditions were assumed basing on the typical mission of PW-100 for flight altitude around 9,000 m, speed of 110 km/h what results in Re = 956,000. Findings Lift coefficients obtained from both experimental and numerical methods for single slatted airfoil SA19 are much higher than that of get for Ronch R1082 airfoil. PW-100 aircraft with SA19 airfoils will be able to be trimmed and fly at any altitude up to 9,000 m and with an arbitrary weight up to 600 kg. Aerodynamic characteristics of SA19 remain smoother and more predictable than that of R1082 airfoil. The very promising properties of SA19 airfoil are well known to the authors since the beginning of last decade when PW team worked together with IAI team on CAPECON project and now it was fully confirmed by this research. Practical implications It was confirmed that selection of the proper wing section for the special mission performed by UAV is of the highest importance decision to be taken at the preliminary design phase. Because there is a limited access to the base of technical parameters in many different UAVs classes and the classical analysis of trends cannot be fully applied, the wing section analysis, either experimental or numerical, must be performed. The situation is much worse than in the case of manned aircrafts because most of the modern UAVs are made of carbon or glass fiber, and therefore, there is no chance for analysis of trends. Originality/value This paper presents a very efficient method of assessing the influence of wing section on aircraft performance adopted for MALE class UAV, especially in an early stage of preliminary design process. The assessment is built mainly on three requirements: Maximum 2D lift coefficient for take-off configuration with flap deflected on 20 degrees should be greater than 2.4. Endurance factor CL1.5/CD for loitering conditions (Ma = 0.5 and CD0 = 0.008) should be greater than 110. The relative wing section thickness should be greater/equal than 19 per cent (it is required for high volume fuel tank located in the wings).

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