Structure optimization of strap-down inertial navigation system support

In order to meet the requirement of inertial navigation components and minimizing the system´s weight, topological optimization and size optimization were conducted under conditions of random vibration and impact. Firstly, the structure of inertial navigation support was designed according to types of missile connection and space arrangement of electronic components; and topological optimization was conducted. Then, according to the dynamic characteristics of missile and requirement of inertial navigation system, the method of transforming multi-loading cases to multi-loading constraints was used to optimizing the size of the support under conditions of random vibration and impact. Comparing to the original support structures, the weight of optimal structures reduced by 28.1%; RMS accelerations in installed points reduced by 25.2% under random vibration; the structures also met the requirement of inertial navigation system under condition of impact. The support structure shows improvements in both dynamic characteristic and light weight comparing with the original one.