Analysis of Lap Region between Skirt and Composite Case under Axial Force in Solid Rocket Motor

2011 ◽  
Vol 71-78 ◽  
pp. 4357-4360
Author(s):  
Hong Chao Liu ◽  
Chun Guang Wang ◽  
Yong Qiong Liu ◽  
Bo Yuan
Keyword(s):  
Carrying Capacity ◽  
Element Model ◽  
Optimization Method ◽  
Rocket Motor ◽  
Load Carrying Capacity ◽  
Solid Rocket Motor ◽  
Proposed Model ◽  
Load Carrying ◽  
Solid Rocket ◽  
Main Factor

To study load carrying capacity for Lap Region between the Skirt and Composite Case(LRSC) of the solid rocket motor(SRM),made the stress of layer out of skirt as the research object, established the two-dimensional axisymmetric finite element model for compsite case,analysed the main factor(lap length) for carrying capacity of LRSC,and verified the conclusions by calculation.Optimized the lap length ranged from 40mm to 60mm, proposed model of the optimal lap length and optimization method,calculated optimal lap length under different axial loads.The results show that, with the increase of lap length of skirt, the load bearing capacity of LRSC enhances first and depresses then,exists a great value,which of the corresponding lap length is optimal;With the increase of axial load,optimal lap length monotonously will increase.

Determination of the Load Carrying Capacity of Honeycomb Panels at Fixing Points under an External Load

2020 ◽  
Vol 299 ◽  
pp. 1184-1189
Author(s):  
V.V. Zhukov ◽  
Anton V. Eremin ◽  
D.V. Stepanec
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Finite Element Model ◽  
Carrying Capacity ◽  
External Load ◽  
Element Model ◽  
Load Carrying Capacity ◽  
The Finite Element Method ◽  
Load Carrying ◽  
Honeycomb Panel

In this article, the object of study is a three–layer honeycomb panel with fixing elements (FE), which are used for transporting the panel, and fixing it to the spacecraft. The goal of the work is to determine experimentally the load carrying capacity of the fixing elements under various types of loading, to determine the load carrying capacity of the honeycomb panel of the spacecraft at fixing points and further comparison of the experimental results with the finite element method results calculated by MSC.Patran / Nastran. A method for conducting static tests of fixing elements of a spacecraft honeycomb panel under an external load is described, a description of computer technology of a finite–element solution to the problem of static strength of a honeycomb panel structure in the MSC.Patran environment is presented, and a finite–element model of a honeycomb panel is designed. An assessment of the strength of a three–layer structure at fixing points was carried out, followed by validation of the finite–element model of a honeycomb panel. On the basis of the validated model, the evaluation of the strength of the honeycomb structure was carried out; based on results obtained, the conclusion has been made about the convergence of the results by the finite element method with the results obtained during the experiment.

Analysis of the Load-Carrying Capability of the Casing Plug Joint of Steel Tube Structures Considering the Contact Effect

2008 ◽  
Vol 33-37 ◽  
pp. 321-326 ◽  
Author(s):  
Xiu Gen Jiang ◽  
Yang Yang ◽  
Feng Jie Zhang ◽  
Jin San Ju ◽  
Xiao Chuan You
Keyword(s):  
Finite Element ◽  
Carrying Capacity ◽  
Element Model ◽  
Steel Tube ◽  
Nonlinear Finite Element ◽  
Tube Length ◽  
Load Carrying Capacity ◽  
Ansys Software ◽  
Load Carrying ◽  
Nonlinear Finite Element Model

Nonlinear finite element model analysis of the casing plug joints of steel tubular has been realized by ANSYS software. The law of load-carrying capability and stiffness of joint are separately gained by changing the ratio of length and diameter (R/L) and the ratio of the casing length and the main tube length (l/L). The influence of the casing thickness on the load-carrying capability and stiffness are also discussed. The results indicated that the load-carrying capability and stiffness of the joints both increase with the ratio(R/L) increment and the ratio of the casing length and main tube length (l/L). When the main tube thickness is equal to casing thickness, the load-carrying capacity of joints achieves the most.

scholarly journals Understanding the Mechanism of Load-Carrying Capacity between Parallel Rough Surfaces through a Deterministic Mixed Lubrication Model

Lubricants ◽  
2022 ◽  
Vol 10 (1) ◽  
pp. 12
Author(s):  
Yuechang Wang ◽  
Abdullah Azam ◽  
Gaolong Zhang ◽  
Abdel Dorgham ◽  
Ying Liu ◽  
...  
Keyword(s):  
Carrying Capacity ◽  
Rough Surfaces ◽  
Elastohydrodynamic Lubrication ◽  
Mixed Lubrication ◽  
Stribeck Curve ◽  
Future Research ◽  
Load Carrying Capacity ◽  
Proposed Model ◽  
Load Carrying ◽  
Lift Off

Experimental results have confirmed that parallel rough surfaces can be separated by a full fluid film. However, such a lift-off effect is not expected by the traditional Reynolds theory. This paper proposes a deterministic mixed lubrication model to understand the mechanism of the lift-off effect. The proposed model considered the interaction between asperities and the micro-elastohydrodynamic lubrication (micro-EHL) at asperities within parallel rough surfaces for the first time. The proposed model is verified by predicting the measured Stribeck curve taken from literature and experiments conducted in this work. The simulation results highlight that the micro-EHL effect at the asperity scale is critical in building load-carrying capacity between parallel rough surfaces. Finally, the drawbacks of the proposed model are addressed and the directions of future research are pointed out.

scholarly journals Axial Load-carrying Capacity of Steel Tubed Concrete Short Columns Confined with Advanced FRP Composites

2020 ◽  
Author(s):  
Ali Raza ◽  
Syyed Adnan Raheel Shah ◽  
Mudasser Muneer Khan ◽  
Faraz ul Haq ◽  
Hunain Arshad ◽  
...  
Keyword(s):  
Finite Element ◽  
Compressive Strength ◽  
Finite Element Model ◽  
Carrying Capacity ◽  
Axial Load ◽  
Element Model ◽  
Confined Concrete ◽  
Superior Performance ◽  
Load Carrying Capacity ◽  
Load Carrying

Fiber Reinforced Polymers (FRPs) have wide applications in the field of concrete construction due to their superior performance over conventional materials. This research focuses on the structural behavior of steel tube FRP jacket–confined concrete (STFC) columns under axial concentric loading and proposes a new empirical equation for predicting the axial load-carrying capacity of STFC columns having thickness of FRP-fabric ranging from 0.09 mm to 5.9 mm. A large database of 700 FRP-confined concrete specimens is developed with the detailed information of critical parameters, i.e. elastic modulus of FRPs (Ef), compressive strength of unconfined concrete (fc’o), diameter of specimen (D), height of specimen (H), total thickness of FRPs (N.tf), and the ultimate strength of confined concrete (fc’c). After the preliminary evaluation of constructed database, a new empirical model is proposed for the prediction of axial compressive strength of FRP-confined specimens using general regression analysis by minimizing the error functions such as root mean squared error (RMSE) and coefficient of determination (R2). The proposed FRP-confinement strength model presented higher accuracy as compared with previously proposed models. Finally, an equation is proposed for the predictions of axial load carrying capacity of STFC columns. For the validation of proposed equation, an extensive parametric study is performed using the proposed nonlinear finite element model (FEM). The FEM is calibrated using the load-deflection results of STFC columns from literature. A close agreement was observed between the predictions of proposed finite element model and proposed capacity equation.

scholarly journals A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors

2019 ◽  
Vol 2019 ◽  
pp. 1-12
Author(s):  
Yanjie Ma ◽  
Futing Bao ◽  
Weihua Hui ◽  
Yang Liu ◽  
Yijie Gao
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Large Scale ◽  
Rocket Motor ◽  
Small Scale ◽  
Solid Rocket Motor ◽  
Combustion Gas ◽  
Proposed Model ◽  
Solid Rocket

This paper describes a zero-dimensional model for evaluating the mass flow rate history of a solid rocket motor igniter. Based on the results of an igniter-firing experiment, in which the igniter is the only source of combustion gas and no propellant is ignited, the proposed model can be used to compute the mass flow rate of the igniter. Different species and temperature-dependent properties, such as the specific heat for each species, are considered. The coupling between the flow field variables in the combustion chamber and the heat transfer at the gas-solid interface is computed in a segment way. Calculations are performed for different species and properties, and the errors are discussed. Using the computed igniter mass flow rate as a boundary condition, a two-dimensional calculation is performed for validation purposes. The results are in good agreement with experimental data. The proposed model can be used to provide reasonable boundary conditions for solid rocket motor simulations and to evaluate the performance of igniters. Although derived on the basis of a small-scale solid rocket motor, the model has the potential to be used in large-scale systems.

Static Load Carrying Capacity in Four Contact Point Slewing Bearings: Theoretical and Preliminary Finite Element Calculations

2010 ◽  
Author(s):  
Josu Aguirrebeitia ◽  
Mikel Abasolo ◽  
Rafael Avile´s ◽  
Igor Fernandez de Bustos ◽  
Rube´n Ansola
Keyword(s):  
Finite Element ◽  
Theoretical Model ◽  
Finite Element Model ◽  
Carrying Capacity ◽  
Static Load ◽  
Contact Point ◽  
Element Model ◽  
Load Carrying Capacity ◽  
Load Carrying ◽  
Slewing Bearings

This paper presents a theoretical model to calculate the general static load-carrying capacity of four-contact-point slewing bearings under axial, radial and tilting-moment loads, compared with preliminary results obtained from a detailed parametric finite element model of the bearing. The theoretical model is based on a generalization of Sjova¨ll and Rumbarger’s equations and provides an acceptance surface in the load space. The finite element model is based on the modelization of the balls via nonlinear traction-only equivalent spring concept. The aim is to validate the theoretical model to be used as an acceptance curve generator for slewing bearing design.

scholarly journals Structural integrity analysis and experimental investigation for solid rocket motor grain subjected to low temperature ignition

2019 ◽  
Vol 293 ◽  
pp. 04005
Author(s):  
Zhi-Bin Shen ◽  
Liang Zhang ◽  
Yi-Fei Li
Keyword(s):  
Finite Element ◽  
Low Temperature ◽  
Structural Integrity ◽  
Three Dimensional ◽  
Element Model ◽  
Rocket Motor ◽  
Experimental Result ◽  
Solid Rocket Motor ◽  
Temperature And Pressure ◽  
Solid Rocket

The structural integrity of solid rocket motor(SRM) grain is severely tested owing to the combined action of low temperature and pressure load under the load case of low temperature ignition. The three dimensional finite element model of SRM was created to analyze the structural integrity of the SRM grain subjected to low temperature and ignition pressure based on three dimensional viscoelastic finite element method via MSC.Patran/Marc. Meanwhile, cold pressurization test was applied on certain SRM. The experimental result and numerical result were compared based on uncoupling principal of temperature and pressure. The result show that the safety factor of solid rocket motor grain is 2.46 which can meet the requirement of structural integrity. The experimental results are in good agreement with the simulation results. Relevant research methods and conclusions can provide reference for the design, analysis and test of SRMs.

Monolithic Morphing Rib With Selective Stiffness From Embeddable Bi-Stable Elements

2018 ◽  
Author(s):  
D. Matthew Boston ◽  
Andres Arrieta ◽  
Jose Rivas-Padilla
Keyword(s):  
Carrying Capacity ◽  
Design Space ◽  
Element Model ◽  
Parameter Study ◽  
Load Carrying Capacity ◽  
Aerodynamic Loading ◽  
Stable Element ◽  
Aeroelastic Analysis ◽  
Load Carrying ◽  
Stable Elements

A trade-off exists in compliant morphing structures between weight, adaptability, and load-carrying capacity. A truss-like structure utilizing a selectively stiff, bi-stable element is proposed to provide a solution to this problem. The design space of the element is explored in a parameter study using a finite element model. The element is embedded in a rib to correlate its behavior to that of the element in isolation. Finally, an aeroelastic analysis is conducted on the rib to determine the response of the structure to aerodynamic loading.

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