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Flat Panel Post-Buckling Analysis with Implicit Method using OptiStruct Flat Panel Post-Buckling Analysis with Implicit Method using OptiStruct Learn More
Flat Panel Post-Buckling Analysis with Implicit Method using OptiStruct
Many commercial aircraft are designed so that fuselage skins can elastically buckle below limit load and continue to operate safely and efficiently. This design regime makes for a very lightweight semi-monocoque structure compared to a non-buckling design. Therefore, predicting the local buckling, post-buckling behavior, and failures are critical to design and optimization of this kind of structure. The local panels buckle in a combination of compression and shear. Excess compression is redistributed to surrounding axial members (frames and stringers) and shear is continued to be carried by the buckled panels via tension parallel to the buckle waves. The compression redistribution and diagonal tension put special strength considerations on all involved structural components. This post-buckling behavior and the analysis method are both called intermediate diagonal tension (IDT).

MDO Director Datasheet MDO Director Datasheet Learn More
MDO Director Datasheet
A multi-disciplinary optimization (MDO) approach allows you to explore all design requirements simultaneously and achieve lighter products, faster. Until now, enabling this process on live vehicle programs has been a challenge. Altair's MDO Director is a novel set of software tools that provides a process to rapidly set up, execute, post-process and explore the design of MDO problems.

Multi-physics Electric Motor Optimization for Noise Reduction Multi-physics Electric Motor Optimization for Noise Reduction Learn More
Multi-physics Electric Motor Optimization for Noise Reduction
In an electric machine, the torque is generated by electromagnetic forces which also create some parasitic vibrations of the stator. These vibrations excite the mechanical structure on which the motor is fixed and generate sound. When designing the electric machine, this aspect has to be taken into account from the start since it depends on the harmonic content of the currents that feed the machine, on the shapes of the rotor and stator, and on the interaction of the electric frequencies with the natural mechanical modes of the structure.
To simulate this phenomenon, a coupling between electromagnetic calculations and vibration analysis has to be set-up. Some optimization procedure can also be added in order to reduce the noise.
In what follows, it is shown how Altair HyperWorks suite; specifically FluxTM, OptiStruct®, HyperMesh® and HyperStudy® products have been successfully used to perform a multi-physics optimization for noise reduction in a fuel pump permanent magnet motor.

OptiStruct for Structural Analysis: Not Just for Optimizations Anymore OptiStruct for Structural Analysis: Not Just for Optimizations Anymore Learn More
OptiStruct for Structural Analysis: Not Just for Optimizations Anymore
Reprint of Engineering.com article on OptiStruct as a structural analysis tool with built-in optimization capabilities

Design-Optimization of a Curved Layered Composite Panel Using Efficient Laminate Parameterization Design-Optimization of a Curved Layered Composite Panel Using Efficient Laminate Parameterization Learn More
Design-Optimization of a Curved Layered Composite Panel Using Efficient Laminate Parameterization
In this paper, presented at the 2016 SAMPE Long Beach Conference, an aircraft door surround model is optimized with respect to the objectives and constraints typical for this type of component using HyperStudy and ESAComp.

Design and optimization of a high performance C-Class catamaran with HyperWorks Design and optimization of a high performance C-Class catamaran with HyperWorks Learn More
Design and optimization of a high performance C-Class catamaran with HyperWorks
Reprint of the article published on composite solutions magazine 2/2016.

Efficient Design and Analysis of Airborne Radomes Efficient Design and Analysis of Airborne Radomes Learn More
Efficient Design and Analysis of Airborne Radomes


Computer Simulation's Role in Advancing Composite Aircraft Structures Computer Simulation's Role in Advancing Composite Aircraft Structures Learn More
Computer Simulation's Role in Advancing Composite Aircraft Structures
Reprint of an article published on the December 2014 issue of Aerospace & Defense Technology magazine


Optimal Design Exploration Using Global Response Surface Method: Rail Crush Optimal Design Exploration Using Global Response Surface Method: Rail Crush Learn More
Optimal Design Exploration Using Global Response Surface Method: Rail Crush
As design exploration and optimization methods have become commonly accepted across a range of industries, such as aerospace, automotive or oil and gas, they are frequently utilized as standard practice to efficiently produce designs and aid critical engineering decisions. This paper present an overview of the practical usage of Altair HyperStudy's GRSM optimization algorithm, followed by application problems of rail
crush design optimization for a single and multi-objective formulation.


Applications of Advanced Composite Simulation and Design Optimization Applications of Advanced Composite Simulation and Design Optimization Learn More
Applications of Advanced Composite Simulation and Design Optimization
Usage of fiber reinforced composite material entered an new era when leading aircraft OEMs took an unprecedented step to design and manufacture essentially full composite airframe for commercial airliners. Composite structures offer unmatched design potential as the laminate material properties can be tailored almost continuously throughout the structure. However, this increased design freedom also brings new challenges for the design process and software. Moreover, as a relatively new material, composite behaviors are more complex and less fully understood by design engineers. Therefore, reliable simulation for highly complex events like bird strike and ditching can play an important role in shortening the product design cycle. This paper showcases two area of CAE tools for composite applications. On advanced simulation, bird strike simulation with Altair RADIOSS [1] is demonstrated on an aircraft underbelly fairing. On design optimization, an airplane wing structure is designed using an innovative composite optimization process implemented in Altair OptiStruct [1-3]. OptiStruct has seen increasing adoption among aerospace OEMs, as demonstrated in the Bombardier application process described in this paper.

A Comprehensive Process for Composite Design Optimisation A Comprehensive Process for Composite Design Optimisation Learn More
A Comprehensive Process for Composite Design Optimisation
Composite structures offer unmatched design potential as laminate material properties can be tailored almost continuously throughout the structure. Moreover, composite laminate can be manufactured to fit the ideal shape of a structure for aerodynamic and other performances. However, this increased design freedom also brings new challenges for the design process and software. It is shown in this paper that optimization technology is well suited to exploit the potentials that composite materials offer.

Hawk T Mk2 - Arrestor Barrier (BAN MK2) Engagement Analysis Hawk T Mk2 - Arrestor Barrier (BAN MK2) Engagement Analysis Learn More
Hawk T Mk2 - Arrestor Barrier (BAN MK2) Engagement Analysis
As the UK Ministry of Defence (MoD) Design Authority for Aircraft Arrestor Barrier Nets, AmSafe products are used to stop aircraft from over-running the end of the runway. The British Arrestor Net (BAN) Mk2 is suspended across the runway over-run area by two electrically driven stanchions and raised or lowered by remote control from the Air Traffic Control tower.

This paper describes the process and results of a FE analysis of the engagement of the Hawk T Mk2 aircraft into a Type A Barrier (BAN Mk2). The analysis was performed using RADIOSS, an advanced non-linear explicit Finite Element solver.

Targeting Composite Wing Performance – Optimising the Composite Lay-Up Design Targeting Composite Wing Performance – Optimising the Composite Lay-Up Design Learn More
Targeting Composite Wing Performance – Optimising the Composite Lay-Up Design
This paper shows how Altair OptiStruct, part of the HyperWorks suite, is used to provide a complete solution when designing with laminated composites, taking the design through concept stages to producing the final ply lay-up sequence. The technology is applied to the design of a laminated wing cover to produce a mass optimised design which meets the requested structural targets.

Multi-Disciplinary Design of an Aircraft Landing Gear with Altair HyperWorks Multi-Disciplinary Design of an Aircraft Landing Gear with Altair HyperWorks Learn More
Multi-Disciplinary Design of an Aircraft Landing Gear with Altair HyperWorks
NAFEMS invited several software vendors to a roundtable in 2007 to demonstrate their best processes in the design of a
realistic aircraft landing gear system. (Figure 1). The emphasis was on simulation processes that can make problem solving innovative, accurate and efficient. This paper explains the
processes followed by engineers at Altair and should help increase awareness regarding the powerful tools available for solving realistic design problems.

Resource Scaling for Antenna Placement Modeling on a SAAB JAS-39 Gripen Aircraft Resource Scaling for Antenna Placement Modeling on a SAAB JAS-39 Gripen Aircraft Learn More
Resource Scaling for Antenna Placement Modeling on a SAAB JAS-39 Gripen Aircraft
This white paper demonstrates how resource requirements scale for the computational electromagnetic modeling of a modern fighter aircraft when the frequency increases. It also demonstrates how different simulation methods may be applied and how they scal relative to each other

Radar Cross Section of Aircraft with Engine Inlets Radar Cross Section of Aircraft with Engine Inlets Learn More
Radar Cross Section of Aircraft with Engine Inlets
At radar frequencies, 1GHz and above, asymptotic methods are usually preferred to calculate the radar cross section (RCS) of targets like aircraft, since the main parts of the target are more than an order of magnitude larger than the wavelength. The challenge is how to combine these methods to compute the RCS. In this white paper the two-step method that obtains accurate results in limited time is detailed.

A shell facet model for preliminary design of cylindrical composite structures A shell facet model for preliminary design of cylindrical composite structures Learn More
A shell facet model for preliminary design of cylindrical composite structures
The laminated composite lay-up design typically involves trade-offs between material selection, thickness of the layer, orientation of the layers, and the stacking sequence. Finding the right structural concept early in the design process leaves resources for the detailed design. Many structural members made of laminated composite materials have the form of thin walled cylindrical shells that are prone to buckling. Thus it is desirable to find structural designs that satisfy global requirements for structural stability early in the design phases. In this work, thin-walled cylindrical composite shells under different loading conditions have been studied for structural stability. The simulation is performed with a shell facet model implemented in the ESAComp software. Preliminary design tools for structural stability of thin-walled cylindrical composite shells are demonstrated and discussed.

Design-Optimization of a curved layered composite panel using efficient laminate parameterization Design-Optimization of a curved layered composite panel using efficient laminate parameterization Learn More
Design-Optimization of a curved layered composite panel using efficient laminate parameterization
Layered composites have proven essential for the successful design of high-performance space structures. The aviation industry are increasingly using more and more layered composites within commercial aircraft, replacing traditional aluminum designs, to achieve weight savings. When optimizing layered composite structures it is desirable to find design solutions that satisfy global requirements early in the design phases. Particularly because of the number of design variables associated with composite layups once models become more detailed are complex:


Preliminary design of a wing spar bonded joint PrintE-mail Preliminary design of a wing spar bonded joint PrintE-mail Learn More
Preliminary design of a wing spar bonded joint PrintE-mail
Fast tools such as the ESAComp module for bonded joints can be very efficient in the preliminary design of various joint configurations. In this example we consider a tip loaded wing of a small aircraft or wind turbine blade. The wing spar carries a constant in-plane shear (Nxy), which needs to be transferred from the joint laminates to the shear web.

Using Experimental Test Data In The Analysis Of Laminated Structures Using Experimental Test Data In The Analysis Of Laminated Structures Learn More
Using Experimental Test Data In The Analysis Of Laminated Structures
Composite material systems have relatively large variation in their measured properties. A typical approach in engineering problems is deterministic, however. Material stiffness and strength, for example, are described with single values in linear-elastic analyses. Physical dimensions of the material, structural and environmental conditions in the laminate or uncertainties in material properties, for instance, require that several discrete definitions are needed for the material specification.

Design-Optimization Of Cylindrical, Layered Composite Structures Using Efficient Laminate Parameterization Design-Optimization Of Cylindrical, Layered Composite Structures Using Efficient Laminate Parameterization Learn More
Design-Optimization Of Cylindrical, Layered Composite Structures Using Efficient Laminate Parameterization
For many years, layered composites have proven essential for the successful design of high-performance space structures, such as launchers or satellites. A generic cylindrical composite structure for a launcher application was optimized with respect to objectives and constraints typical for space applications. The studies included the structural stability, laminate load response and failure analyses. Several types of cylinders (with and without stiffeners) were considered and optimized using different lay-up parameterizations. Results for the best designs are presented and discussed.

Engineering oriented formulation for laminate lay-up optimization Engineering oriented formulation for laminate lay-up optimization Learn More
Engineering oriented formulation for laminate lay-up optimization
The concept of elementary laminates is used to formulate the design problem for a
laminated composite structure. A parameterized laminate is divided into stacks with periodic patterns of elementary laminates. With elementary laminates desired regularity for the laminate lay-ups is achieved, which is practical for multi-layer laminates. Due to the reduced design space solution time can be considerably reduced. Two laminate lay-up formulation concepts are presented and their performance is evaluated. The design problem used as a reference case involved the optimization of the stacking sequences to maximize plate buckling loads using a genetic algorithm.

PROBABILISTIC LAMINATE ANALYSIS USING ESACOMP SOFTWARE PROBABILISTIC LAMINATE ANALYSIS USING ESACOMP SOFTWARE Learn More
PROBABILISTIC LAMINATE ANALYSIS USING ESACOMP SOFTWARE
Engineering design problems include always
uncertainties such as variation in material properties or environment, incomplete statistical data to generate input, modelling and human errors. Yet, the design in general relies on single numbers obtained from engineering equations. In case of strength prediction the material strength is derived using statistical methods
and the uncertainties is included in the design value (A or B-value).

CFRP Electronics Housing for a Satellite (ESA 2005) CFRP Electronics Housing for a Satellite (ESA 2005) Learn More
CFRP Electronics Housing for a Satellite (ESA 2005)
The drive for continuous mass reductions in spacecraft structures has promoted the use of carbon fibre reinforced plastics. CFRP has excellent specific stiffness and strength, which makes it possible to construct lightweight structures. CFRP is typically used in applications where electrical, thermal and radiation protection properties are not decisive.

Transverse shear in Laminate Analysis Transverse shear in Laminate Analysis Learn More
Transverse shear in Laminate Analysis
This paper describes the method for transverse shear analysis to be applied in the composites design program ESAComp. The correlation of the method to the formulations used in the commercial finite element programs is presented and the results from the selected method are compared to the exact elasticity results. The results show good agreement with the exact solutions for cross-ply and unsymmetric angle-ply laminates. Symmetric angle-ply laminates create bending twisting coupling that the theory cannot accurately model.

FACILITIES IN ESACOMP FOR ANALYSIS AND DESIGN OF ADHESIVE BONDED JOINTS FACILITIES IN ESACOMP FOR ANALYSIS AND DESIGN OF ADHESIVE BONDED JOINTS Learn More
FACILITIES IN ESACOMP FOR ANALYSIS AND DESIGN OF ADHESIVE BONDED JOINTS
This paper presents a newly developed analysis and design module for adhesive bonded joints implemented in ESAComp, software for analysis and design of composite laminates and laminated structures.

Pressure vessels: The composite solution from ComposicaD and ESAComp Pressure vessels: The composite solution from ComposicaD and ESAComp Learn More
Pressure vessels: The composite solution from ComposicaD and ESAComp
With composite pressure vessels foreseen as a significant industrial growth sector, Mike Skinner, from Seifert and Skinner & Associates, talks us through their approach and how the composite solution offered by ComposicaD and ESAComp provides efficient design and analysis to meet the emerging markets.

Considering large deflections in panels - ESAComp 4.4 introduces nonlinear analysis Considering large deflections in panels - ESAComp 4.4 introduces nonlinear analysis Learn More
Considering large deflections in panels - ESAComp 4.4 introduces nonlinear analysis
In composite panels with large support spans, deflections are primarily due to bending. Out-of-plane shear can also play a significant role in sandwich structures. While these deformation types are considered in the typically used linear static analyses, the results are not accurate when going beyond the small deflections regime. When a panel is firmly fixed at its edges, it starts to carry loads partly like a membrane already at low load levels. The panel exhibits stress stiffening. Consequently, with an appropriate analysis approach more efficient structures can be designed.

ESAComp meets challenging marine applications ESAComp meets challenging marine applications Learn More
ESAComp meets challenging marine applications
In this article we learn about ESAComp's role in the design-development of a carbon composite RIB "Rigid-hulled Inflatable Boat", the latest project from Dr. Luca Olivari, a naval architect, founder and owner of the Italian company Olivari Composites Engineering.

At the origins of delamination stresses - Free edge analysis gives insight At the origins of delamination stresses - Free edge analysis gives insight Learn More
At the origins of delamination stresses - Free edge analysis gives insight
When you make a tensile test for [±45/0/90]s and [90/±45/0]s laminates you may observe different failure strengths. This may seem first surprising since the laminates are basically the same - only the stacking sequence is different, which should not influence on the in-plane values.

Anisogrid Payload Adaptor Structure For Vega Launcher Anisogrid Payload Adaptor Structure For Vega Launcher Learn More
Anisogrid Payload Adaptor Structure For Vega Launcher
In the framework of a development project promoted by the European Space Agency (ESA/ESTEC), Airbus Defence & Space (EADS CASA Espacio, ECE) has designed, manufactured and tested a technology demonstrator representative of the payload adaptor (PLA) of VEGA Launcher, by using an anisogrid concept, called anisogrid payload adaptor (APA).

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