scholarly journals Common Bulkhead Tank Design for Cryogenic Stage of an Indian Launch Vehicle

2022 ◽  
Vol 72 (1) ◽  
pp. 3-9
Author(s):  
Yogesh Pratap Singh ◽  
Harjit Singh ◽  
Prahlad Kumar Sahu ◽  
Muthukumar R
Keyword(s):  
Cost Effective ◽  
Launch Vehicle ◽  
Launch Vehicles ◽  
Space Technology ◽  
Indian Space Research Organization ◽  
Vehicle Mass ◽  
Payload Capacity ◽  
Sandwich Type ◽  
Foam Filled ◽  
Tank Design

Indian Space Research Organization (ISRO) has been advancing in space technology with its cost-effective techniques. Currently, ISRO, in its cryogenic stages, uses truss type intertank structure, which induces large concentrated loads at the truss interfaces. As a remedial measure, works on closed intertank are being carried out by them, but this configuration will considerably increase the launch vehicle mass compared to truss type. Therefore, after a thorough literature survey, a Common bulkhead (CBH) tank seemed to be the best solution to the aforementioned problem. Detailed research on sandwich-type CBH has been carried out in this paper with the motivation of saving mass and height in launch vehicles. Suitable core and facesheet material were selected. A novel foam-filled honeycomb core is suggested in this work. Several comparisons in various CBH dome designs were carried out to reach for the best possible configuration and composition that can be used. MATLAB®, SolidWorks®, and ANSYS® were used in parallel for all computations dealing with design and analysis. A mass saving of approximately upto 490 kgs and a height reduction of upto 1.755 m was obtained with the final selected configuration with respect to the current GSLV configuration. These savings can add extra payload capacity to ISRO launch vehicles in their future missions.

scholarly journals United States Launch Vehicle Systems

1990 ◽  
Vol 123 ◽  
pp. 325-332
Author(s):  
Robert B. Krause
Keyword(s):  
United States ◽  
Space Shuttle ◽  
Cost Effective ◽  
The United States ◽  
Launch Vehicle ◽  
Launch Vehicles ◽  
National Space ◽  
Manned Spacecraft ◽  
Operational Life ◽  
Heavy Lift

AbstractUnited States policy for national space launch capability provides for a balanced mix of launches, utilizing the Space Shuttle and Expendable Launch Vehicles (ELVs). It also directs government agencies to encourage and support the development of a domestic commercial expendable launch vehicle industry. This is to be accomplished by contracting for necessary ELV launch services directly from the private sector and by facilitating access by commercial launch firms to national launch and launch-related property and services they request to support these commercial operations.The current mixed fleet includes the Space Shuttle and four expendable launch vehicles - Titan, Atlas, Delta and Scout. New small class launch vehicles, including Pegasus, are in development. In addition, studies are underway to assure that the United States has cost-effective, reliable access to space, heavy-lift launch capability, and a new manned spacecraft after the current Space Shuttle reaches the end of its operational life. This paper will highlight the current capabilities of the mixed fleet and summarize the plans for new or modified United States launch vehicles through the first decade of the next century.

Ballistic Impact Response of Foam-Filled Sandwich Composites

2001 ◽  
Author(s):  
Uday K. Vaidya ◽  
Biju Mathew ◽  
Chad A. Ulven ◽  
Brent Sinn ◽  
Marian Velazquez
Keyword(s):  
Cost Effective ◽  
Impact Response ◽  
Sandwich Composites ◽  
High Velocity Impact ◽  
Honeycomb Core ◽  
Velocity Impact ◽  
Foam Filling ◽  
Foam Filled ◽  
Honeycomb Cores ◽  
The Cost

Abstract Sandwich composites find increasing use as flexural load bearing lightweight sub-elements rail / ground transportation and marine bodies. In recent year, alternatives to traditional foam and honeycomb cores are being sought. One such development includes filling the cells of the honeycomb core with foam. The increased surface area allows stress forces to dissipate over a larger area than that offered by the honeycomb alone. This allows for use of lowering the cost of the honeycomb cells, and thereby making the design extremely cost-effective. In the present research, phenolic impregnated honeycomb / corrugated cells with polyurethane foam filling has been considered. The intermediate and high velocity impact response of these types of sandwich constructions has been studied. The applications for such cores would be in rail and ground transportation, where impacts in the form of flying debris are common.

scholarly journals Preliminary study on launch vehicle design: Applications of multidisciplinary design optimization methodologies

2017 ◽  
Vol 26 (1) ◽  
pp. 93-103 ◽  
Author(s):  
Loïc Brevault ◽  
Mathieu Balesdent ◽  
Sébastien Defoort
Keyword(s):  
Design Optimization ◽  
Design Process ◽  
Concurrent Engineering ◽  
Multidisciplinary Design Optimization ◽  
Launch Vehicle ◽  
Multidisciplinary Design ◽  
Vehicle Design ◽  
Launch Vehicles ◽  
Data Set ◽  
Launch Vehicle Design

The design of complex systems such as launch vehicles involves different fields of expertise that are interconnected. To perform multidisciplinary studies, concurrent engineering aims at providing a collaborative environment which often relies on data set exchange. In order to efficiently achieve system-level analyses (uncertainty propagation, sensitivity analysis, optimization, etc.), it is necessary to go beyond data set exchange which limits the capabilities of performance assessments. Multidisciplinary design optimization methodologies is a collection of engineering methodologies to optimize systems modelled as a set of coupled disciplinary analyses and is a key enabler to extend concurrent engineering capabilities. This article is focused on several examples of recent developments of multidisciplinary design optimization methodologies (e.g. multidisciplinary design optimization with transversal decomposition of the design process, multidisciplinary design optimization under uncertainty) with applications to launch vehicle design to illustrate the benefices of taking into account the coupling effects between the different physics all along the design process. These methods enable to manage the complexity of the involved physical phenomena and their interactions in order to generate innovative concepts such as reusable launch vehicles beyond existing solutions.

Interaction of Liquid Propellant and Coupled System Structure for Atlas V Launch Vehicle

2010 ◽  
Author(s):  
Kirk W. Dotson ◽  
Brian H. Sako ◽  
Daniel R. Morgenthaler
Keyword(s):  
Hydraulic System ◽  
Coupled System ◽  
Launch Vehicle ◽  
System Structure ◽  
Liquid Oxygen ◽  
Launch Vehicles ◽  
Liquid Propellant ◽  
Pressure Oscillations ◽  
Maximum Acceleration ◽  
Structure Interaction

In structural modeling of launch vehicles, liquid propellant is sometimes rigidly attached to feedline walls. This assumption precludes the interaction of structural modes with propellant pressure and flow. An analysis of fluid-structure interaction (FSI) for the Atlas V launch vehicle revealed that structural models with rigidly-attached propellant yield unconservative response predictions under some conditions. In particular, during the maximum acceleration time of flight, pressure oscillations acting at bends in the Atlas V liquid oxygen (LO2) feedline excite 15–20 Hz structural modes that have considerable gain on the feedline and at the spacecraft interface. The investigation also revealed that the venting of gas from the pogo accumulator is an excitation source and changes the dynamic characteristics of the hydraulic system. The FSI simulation produced during the investigation can be adapted to mission-specific conditions, such that responses and loads are conservatively predicted for any Atlas V flight.

scholarly journals Trends in the Development of Video Telemetry Systems for Measuring the Temperature of Thermally Loaded Areas of Launch Vehicles

2020 ◽  
Vol 7 (4) ◽  
pp. 90-96
Author(s):  
D. I. Klimov ◽  
◽  
T. T. Mamedov ◽  
I. R. Gubaidullin ◽  
◽  
...  
Keyword(s):  
Block Diagram ◽  
Human Vision ◽  
Frame Rate ◽  
Contactless Method ◽  
Launch Vehicles ◽  
Space Technology ◽  
Video Information ◽  
Emergency Situations ◽  
Technology Products ◽  
Planck Distribution

Nowadays the appearance of publications, scientific and research, and also research and development works on the creation of video monitoring systems for rocket and space technology products is caused by a well-known fact about the most reliable information channel — vision (human vision provides 95 % of information on surrounding objects), hence the inclusion of video information in the control system significantly increases the reliability of information from existing telemetry facilities of objects to track their normal functioning, as well as for rapid and unambiguous identification of the causes of abnormal and emergency situations that occur during the flight of rocket and space technology products. The article proposes a method for processing information from a video telemetry system about the temperature of thermally loaded elements of launch vehicles and upper stages by a remote contactless method with visual representation by converting a signal received from video cameras based on the principle of color pyrometers and Planck distribution. To implement the algorithm for processing video information for calculating the temperature, a block diagram of the solver is developed. A method for presenting video information and temperature measurements is presented provided that there is a color video image with a reduced frame rate and wide spectral range.

scholarly journals Calculated estimation of electromagnetic compatibility of radio-electronic means of space systems and complexes

2021 ◽  
Vol 24 (2) ◽  
pp. 49-54
Author(s):  
Yevgeny E. Krivobokov
Keyword(s):  
Electromagnetic Compatibility ◽  
Mutual Influence ◽  
Integrated Approach ◽  
Design Stage ◽  
Launch Vehicles ◽  
Space Systems ◽  
Space Technology ◽  
Radio Electronic ◽  
Analytical Assessment ◽  
Technical Measures

This article presents the methods of complex computational and analytical assessment of ensuring electromagnetic compatibility of technical means (electrical, electronic and radio-electronic means of launch vehicles and spacecraft). These methods allow us to conduct a comprehensive computational and analytical assessment of the electromagnetic compatibility of the technical means of rocket and space technology, which in its essence allows us to assess the mutual influence of the technical means of rocket and space technology already at the design stage of rocket and space technology objects. The analysis of the results of the assessment of the electromagnetic compatibility of the technical means of rocket and space technology allows us to develop organizational and technical measures aimed at ensuring the electromagnetic compatibility of the technical means of rocket and space technology at all stages of the life cycle of objects of rocket and space technology. To assess the electromagnetic compatibility of the technical means of rocket and space technology, an integrated approach was chosen due to the large dimension of the initial data and the variety of possible variants of interference penetration.

Model Fidelity Refinement for System-Level Design of a Reusable Launch Vehicle

2011 ◽  
Author(s):  
Natasha Smith
Keyword(s):  
Model Uncertainty ◽  
System Analysis ◽  
Launch Vehicle ◽  
System Level ◽  
Reliability Based Design ◽  
Reusable Launch Vehicle ◽  
Component Design ◽  
Level Design ◽  
Reliability Based Optimization ◽  
Tank Design

This paper extends research in multidisciplinary reliability-based design optimization by using model uncertainty quantification to integrate multiple levels of design. The bi-level design of a reusable launch vehicle with a component fuel tank is studied from this perspective. The system design includes a conceptual, low-fidelity weights analysis with significant model uncertainty, while the tank design provides a more rigorous analysis for the weight of one component with significantly less uncertainty. Evaluating the uncertainties of the disciplinary analysis provides two important benefits. The first is as a metric for selecting appropriate disciplinary model(s) to integrate into the system-level analysis for a desired level of reliability. The second benefit is as the basis for iterating between design levels. Rather than fully integrating the system and component analyses, this method uses model uncertainty to leverage the component design to refine the system analysis. Thus the communication between design levels is less stringent than for fully-integrated reliability based optimization.

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