An approach for the mathematical description of aircraft electrical systems' load characteristics including electrical dependences validation

Aeroplane design is defined by many objectives. One of them is the reduction of weight while maintaining safety, functions and performance. As power measurement campaigns have revealed, weight can be saved, as the electrical system exhibits low capacity utilisation. This is, as there are many requirements (on certification, safety and function) to meet. Also, there are systems, which do not exhibit the degree of dependence they are assumed to have. Their power consumption is lower than expected, as e.g. the dependence on passenger behaviour is lower than expected. In a first step, this paper commences with requirements for a combined electrical load analysis based on measurements and math. In a second step, this paper will show a mathematical approach to describe the actual dependence of electrical aircraft systems' current consumption. The presented approach is one out of several ones being investigated to finally achieve an optimised electrical load analysis and an optimised electrical system. This paper will not deal with the actual certification process.