The association of Harold Roxbee Cox with the Air Registration Board began in 1938 (the year following its formation) with his appointment as its first chief technical officer — a post to which he was eminently suited by virtue of his experience and already formidable reputation in a wide range of technical aspects of aviation. Interrupted by the war, his service to the ARB was renewed first as consultant and member of the board, later (as Sir Harold Roxbee Cox) as its vice chairman and finally (as Lord Kings Norton) as its chairman.

During the period 1970–1990 the Military Aircraft Division of British Aerospace based at Warton developed a structural sizing and optimisation system initially based on an “in-house” developed finite element analysis (FEA) system. This subsequently progressed to using NASTRAN, which was rapidly evolving to be the standard FEA system used within all divisions of British Aerospace (BAe).

The many problems associated with the development and application of this evolving system are described. These problems covered a wide range from software development, engineering application, resource management and hardware dependence.

One problems which has received a great deal of attention since 1990 is the incorporation of the panel buckling constraint particularly when applied to laminated structures. This paper describes an early attempt to incorporate this constraint followed by a brief description of the application and integration of a specialised Panel Buckling code.

The paper concludes by describing how BAe Military Aircraft Division is attempting to incorporate the buckling constraint using NASTRAN into a high performance computing (HPC) environment. In addition this development illustrates how many of the problems described earlier are being overcome by working in partnership with software vendors, hardware vendors and other business units within BAe.

A methodology has been developed to integrate the vulnerability discipline into the conceptual/preliminary design process of combat aircraft. An interactive and programmable solid modelling Computer Aided Design (CAD) system is used to generate a CAD solid model of the aircraft’s critical components. The aircraft’s components’ sizes and shapes are pre-defined by a conceptual/preliminary design synthesis computer model. A systematic Child-Parent assembly process is used to model the aircraft vulnerability, by defining the criticality degree of each component in the aircraft assembly. Solid Modelling CAD techniques have been modified to develop techniques to perform the two main standard vulnerability assessments, namely the shotline and vulnerable area methods.