According to W. Edwards Deming, American companies require nothing less than a transformation of management style and of governmental relations with industry. In Out of the Crisis, originally published in 1982, Deming offers a theory of management based on his famous 14 Points for Management. Management's failure to plan for the future, he claims, brings about loss of market, which brings about loss of jobs. Management must be judged not only by the quarterly dividend, but by innovative plans to stay in business, protect investment, ensure future dividends, and provide more jobs through improved product and service. In simple, direct language, he explains the principles of management transformation and how to apply them.

Out of the Crisis

Self-healing polymeric materials: A review of recent developments

Nonlinear Programming: A Unified Approach

This paper is a review of low-velocity impact responses of composite materials. First the term ‘low-velocity impact’ is defined and major impact-induced damage modes are described from onset of damage through to final failure. Then, the effects of the composite's constituents on impact properties are discussed and post-impact performance is assessed in terms of residual strength.

Review of low-velocity impact properties of composite materials

Topology optimization is the process of determining the optimal layout of material and connectivity inside a design domain. This paper surveys topology optimization of continuum structures from the year 2000 to 2012. It focuses on new developments, improvements, and applications of finite element-based topology optimization, which include a maturation of classical methods, a broadening in the scope of the field, and the introduction of new methods for multiphysics problems. Four different types of topology optimization are reviewed: (1) density-based methods, which include the popular Solid Isotropic Material with Penalization (SIMP) technique, (2) hard-kill methods, including Evolutionary Structural Optimization (ESO), (3) boundary variation methods (level set and phase field), and (4) a new biologically inspired method based on cellular division rules. We hope that this survey will provide an update of the recent advances and novel applications of popular methods, provide exposure to lesser known, yet promising, techniques, and serve as a resource for those new to the field. The presentation of each method's focuses on new developments and novel applications.

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A survey of structural and multidisciplinary continuum topology optimization: post 2000

The USAF characteristic K approach for cracks growing from small material discontinuities under combat aircraft and civil aircraft load spectra

The chapter summarises a building block approach that has been used to demonstrate the potential of SPD for repairing and enhancing the airworthiness and integrity of fuselage skins, fuselage lap joints and centre barrel structures. The initial focus is on the application of SPD doublers to fuselage lap joints representative of civil transport aircraft. These successful tests are then supported by an application to an F/A-18 Hornet wing attachment centre barrel laboratory test article that was subsequently tested for more than three design life times without detectable evidence of degradation to the SPD doublers, including those over fastener holes, or the surrounding structure. We also show that even though, during fastener removal to install a Canadian modification, the SPD was damaged there was no cracking or disbonding induced and the SPD, and the surrounding structure, remained intact even after cycling a further 13,000 flight hours, which corresponds to in excess of two lifetimes. This finding highlights the damage-tolerant nature of SPD. As such this test programme revealed SPD to be very durable and that it can be used to restore structural integrity of full-scale aircraft components under a representative fighter aircraft spectrum. As a result it is found that SPD doublers can withstand cyclic stress amplitudes of approximately 200 MPa without disbonding or failure. This is an important finding since it represents a realistic upper bound on the stresses seen on the exterior wetted surface of operation aircraft.

Application of SPD to enhance the structural integrity of fuseage skins and centre barells

Fatigue considerations play a major role in the design of optimised flight vehicles, and the ability to accurately design against the possibility of fatigue failure is paramount. However, recent studies have shown that, in the Paris Region, cracking in high-strength aerospace quality steels and Mil Annealed Ti–6AL–4 V titanium is essentially R ratio independent. As a result, the crack closure and Willenborg algorithm’s available within commercial crack growth codes are inappropriate for predicting/assessing cracking under operational loading in these materials. To help overcome this shortcoming, this chapter presents an alternative engineering approach that can be used to predict the growth of small near-micron-size defects under representative operational load spectra and reveal how it is linked to a prior law developed by the Boeing Commercial Aircraft Company. A simple method for estimating the S–N response of 7050-T7451 aluminium is then presented.

Tools for Assessing the Damage Tolerance of Primary Structural Components

This chapter discusses the development of a bonded composite reinforcement to the integrally stiffened D6ac steel wing pivot fitting (WPF) of F-111 aircraft while in-service with the Royal Australian Air Force (RAAF). Particular attention is given to the building block approach and as such describes the finite element and experimental program used to determine improved stiffener runout geometry as well as the full-scale wing tests required to validate the computed stress reduction. Other aspects of this reinforcement are discussed in this chapter. This represents the first bonded reinforcement to primary structure and was successful in that by reducing the strains at the critical location by approximately 30% it achieved its primary objective namely to stop cracking and wing failure in the RAAF F-111 fleet and Cold Proof Load Test (CPLT; explained later). A significant outcome of the F-111 WPF reinforcement program was that it resulted in a detailed understanding of the design/assessment tools needed for designing damage tolerant repairs to meet the stringent damage tolerant requirements inherent in both JSSG2006 and FAA ac-120-107b. It is also shown that the in-service performance of the WPF reinforcement reveals shortcomings in the approach outlined in the US Composite Materials Handbook CMH-17-3G for the design of bonded joints. It is also shown that not only was the WPF reinforcement the first example of the ability of composite repair technology to eliminate cracking in primary structure it was also the first example to highlight the benefit to be gained by combining composite repair technology with shape optimisation or rework.

Rhys Jones

Papers

The USAF characteristic K approach for cracks growing from small material discontinuities under combat aircraft and civil aircraft load spectra

Application of SPD to enhance the structural integrity of fuseage skins and centre barells

Tools for Assessing the Damage Tolerance of Primary Structural Components

The F111C Wing Pivot Fitting Repair and its Implications for the Design/Assessment of Bonded Joints and Composite Repairs

Effects of plasticity on several fracture parameters for impact damage and related problems