Download or read book Computational Fluid Dynamic Studies of a Solid and Ribbon 12 gore Parachute Canopy in Subsonic and Supersonic Flow written by and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1995 with total page 944 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerospace America written by and published by . This book was released on 1995 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Energy Research Abstracts written by and published by . This book was released on 1995 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 3 D Parachute Descent Analysis Using Coupled Computational Fluid Dynamic and Structural Codes written by and published by . This book was released on 1997 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational tool that models the terminal descent characteristics of a single or a cluster of parachutes is a technology that is needed by parachute designers and engineers. As part of a technology program annex (TPA), a joint effort between the U.S. Army Natick Research, Development, and Engineering Center (NRDEC) and the U.S. Army Research Laboratory (ARL) to develop this computational tool is now under way. As a first effort, attempts are being made to analyze both two-dimensional (2- D) and three-dimensional (3-D) flow fields around a parachute using a coupling procedure in which the fluid dynamics are coupled to 2-D and 3-D structural dynamic (SD) codes. This effort uses computational fluid dynamic (CFD) codes to calculate a pressure field, which is then used as an input load for the SD code. Specifically, this report presents the methods and results of the flow field plus the structural characteristics of a single axisymmetric parachute and a 3-D gore configuration for the terminal descent velocity. Computed results have been obtained using the payload weight and unstretched constructed geometry of the canopies as input. Significant progress has been made in determining the terminal descent flow field along with the terminal shape of the parachute. A discussion of the fluid and structural dynamics codes, coupling procedure, and the associated technical difficulties is presented. Examples of the codes' current capabilities are shown.
Download or read book The Finding Guide to AIAA Meeting Papers written by American Institute of Aeronautics and Astronautics. Technical Information Service and published by . This book was released on 1995 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA Journal written by American Institute of Aeronautics and Astronautics and published by . This book was released on 2000 with total page 1144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational Fluid Dynamics Modeling of Parachute Clusters written by and published by . This book was released on 1997 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational tool that models the terminal descent characteristics of a single or a cluster of parachutes is a technology that is needed by parachute designers and engineers. As part of a technology program annex (TPA), a joint effort between the U.S. Army Natick Research, Development, and Engineering Center (RRDEC) and the U.S. Army Research Laboratory (ARL) to develop this computational tool is now under way. As a first effort, attempts are being made to analyze both two-dimensional (2- D) and three-dimensional (3-D) flow fields around a parachute using a coupling procedure in which the fluid dynamics are coupled to 2-D and 3-D structural dynamic (SD) codes. This effort uses computational fluid dynamic (CFD) codes to calculate a pressure field, which is then used as an input load for the SD code. Specifically, this report presents the methods and results of the flow field plus the structural characteristics of a single axisymmetric parachute and a 3-D gore configuration for the terminal descent velocity. Computed results have been obtained using the payload weight and unstretched constructed geometry of the canopies as input. Significant progress has been made in determining the terminal descent flow field along with the terminal shape of the parachute. A discussion of the fluid and structural dynamics codes, coupling procedure, and the associated technical difficulties is presented. Examples of the codes' current capabilities are shown.
Download or read book Computational Fluid Dynamics Modeling of Parachute Clusters written by and published by . This book was released on 1997 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational tool that models the terminal descent characteristics of a single or a cluster of parachutes is a technology that is needed by parachute designers and engineers. As part of a technology program annex (TPA), a joint effort between the U.S. Army Natick Research, Development, and Engineering Center (RRDEC) and the U.S. Army Research Laboratory (ARL) to develop this computational tool is now under way. As a first effort, attempts are being made to analyze both two-dimensional (2- D) and three-dimensional (3-D) flow fields around a parachute using a coupling procedure in which the fluid dynamics are coupled to 2-D and 3-D structural dynamic (SD) codes. This effort uses computational fluid dynamic (CFD) codes to calculate a pressure field, which is then used as an input load for the SD code. Specifically, this report presents the methods and results of the flow field plus the structural characteristics of a single axisymmetric parachute and a 3-D gore configuration for the terminal descent velocity. Computed results have been obtained using the payload weight and unstretched constructed geometry of the canopies as input. Significant progress has been made in determining the terminal descent flow field along with the terminal shape of the parachute. A discussion of the fluid and structural dynamics codes, coupling procedure, and the associated technical difficulties is presented. Examples of the codes' current capabilities are shown.
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1995 with total page 824 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation of Drag and Stabili Ty of Parachutes at Supersonic Speeds written by Nickolai Charczenko and published by . This book was released on 1964 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Characteristics of 6 foot Drogue stabilization Ribbon Parachutes at High Altitudes and Low Supersonic Speeds written by Clinton T. Johnson and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Performance data are presented for two types of ribbon parachutes. The parachutes were forcibly deployed from an air-launched test vehicle at altitudes from 55,000 feet to 70,000 feet and at Mach numbers between 0.92 and 1.52. Opening shock, steady-state drag performance, and canopy-porosity effects are evaluated with respect to Mach number and dynamic pressure. The conical canopy design appears to function far better than the flat canopy at supersonic deployment speeds. The relatively high-porosity conical design improves the parachute stability, with the added benefit of a low opening shock. The drag efficiency of the conical canopy is equivalent to that of the flat canopy having 50-percent-lower porosity. Riser elasticity and length also appear to be important parameters affecting the parachute stability. Reducing the weight of the test vehicle by a factor of one-third had a negligible effect on the stability and drag characteristics of the parachute.
Download or read book Experimental Determination of the Subsonic Mass Flow Through Several Ribbon Type Parachute Canopies During Inflation and at Steady State Conditions written by Kenneth B. Buchanan and published by . This book was released on 1968 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of studies to determine the mass flow through circular flat ribbon canopies of several geometric porosities at steady flow conditions and during inflation and through 17% and 27% porous Hemisflo canopies during inflation are presented. Pressure distributions which were established as a necessary part of the study are also included. (Author).
Download or read book Determination of the Mass Flow Through Parachute Canopies in Subsonic and Supersonic Flow written by R. J. Niccum and published by . This book was released on with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The success of any parachute system is measured by its performance during the opening sequence and its performance during steady state operation. Earlier presentations in this course have shown that the parachute opening time and opening force are important dynamic parameters which may be used in determining a parachute's desirability for certain applications. Similarly, the steady state aerodynamics such as tangent force coefficient, normal force coefficient, and moment derivative with respect to angle of attack are among the parameters employed for gaging a parachute's steady state worthiness. The purpose of this presentation is to bring to your attention still another parameter that is useful in the design and evaluation of the performance characteristics of parachute systems, namely, the mass flow through a canopy both during its inflation and its steady descent.
Download or read book Flow Characteristics of Rigid Ribbon Parachute Canopies in Supersonic Flow written by H. G. Heinrich and published by . This book was released on 1965 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An inlet diffuser model was used in freestream and wake flows to establish the relationship between shock wave standoff distance and mass flow through a cavity. The results of these experiments were used to devise a method to calculate shock wave stanoff distances as a function of the mass flow through the cavity. By means of further experiments, it was shown that this method is useful for carrying out similar calculations for porous parachutes in supersonic flow. The interaction between suspension line boundary layers and the bow shock of porous parachute canopies, and its effect upon the pressure distribution and the pressure drag coefficient, has been studied. Pressure drag coefficients depending on the number of suspension lines were established. (Author).
Download or read book A Theoretical Analysis of the Aerodynamic and Structural Forces Associated with a Ribbon Parachute Canopy in Steady Descent written by Kenneth Kenichiro Muramoto and published by . This book was released on 1983 with total page 636 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of the Supersonic Guide Surface and the Spiked Ribbon Parachutes written by Helmut G. Heinrich and published by . This book was released on 1965 with total page 71 pages. Available in PDF, EPUB and Kindle. Book excerpt: The location of shock waves, the pressure distribution and the mass flow, which are significant for the functioning of a parachute in supersonic flow, are discussed and some advantageous conditions are postulated. Wind tunnel studies are described in which the validity of the assumptions has been checked by means of models of a modified guide surface canopy combined with a shock producing cone. A configuration was found according to which 4 inch textile models function satisfactorily up to Mach numbers of 4.5. The results of further supersonic wind tunnel tests are shown in which a 4 ft supersonic guide surface parachute, built in accordance with the established aerodynamic parameters, functioned satisfactorily. This parachute collapsed due to structural weakness at a Mach number of 2.8 after being exposed to supersonic flow for approximately 90 minutes. The concept of the wake producing cone in conjunction with ribbon parachute canopies was also tried, but no satisfactory configuration was found. (Author).
