Guidelines on COOMET key comparison evaluation. Final report: COOMET supplementary comparison of capacitance at 10 pF and 100 pF (COOMET.EM-S13) / O. Final report on COOMET key comparison of capacitance at 100 pF (COOMET.EM-S4) / O.
Final report on COOMET key comparison of capacitance at 10 pF (COOMET.EM-K4) / O. Final report on the APMP comparison of capacitance at 100 pF (APMP supplementary comparison APMP.EM-S7) / L. Final report on the APMP comparison of capacitance at 10 pF: APMP.EM-K4.1 / L. Linking the results of key comparison CCEM-K4 with the 10 pF results of EUROMET.EM-K4 / F. Final report on key comparison CCEM-K4 of 10 pF capacitance standards / A.-M. Model selection in the average of inconsistent data: an analysis of the measured Planck-constant values / G. The evaluation of key comparison data: determining the largest consistent subset / M. The evaluation of key comparison data / M. The model combines technological, operational, and design parameters, and is the basis for the formation of algorithm for choosing the parameters of an aircraft fueled by solar energy. We obtained a generalized analytical model of mass-energy balance of an aircraft, taking into account common operation modes and the laws of solar energy generation, which allows us to conduct analytical prediction of characteristics of prototypes. Results of the study might be used in the process of creation of aircraft, fueled by solar energy, at the stage of outline design. The model is proposed for determining the mass of an aircraft in general, which takes into account weight characteristics of the industrial components of an aircraft.
We described the factors that affect performance of solar panels of an aircraft, in particular shading, V-shape of a wing, geometry of aerodynamic profile, cloudiness, and orientation relative to the Sun. Under the takeoff and landing modes, as well as during a maneuver, the current deficit of the generated power may be compensated for by power of the battery. The power surplus is accumulated in the battery. Under the mode of a horizontal flight, there should be enough power, generated by solar panels, to fuel all systems. The principles of power supply of the aircraft systems under all flight modes were defined. To create a mathematical model that describes interrelations between the basic parameters of an aircraft, fueled by solar energy, it was proposed to describe the main components in stages, namely: power, required for the implementation of a horizontal flight total power consumption for performing of a flight, including take-off and maneuvers magnitude of energy, generated during a flight total take-off mass of an aircraft. To understand the characteristics and principles of creation of an aircraft, fueled by solar energy, the fundamentals of providing mass-energy balance and its specificity were considered. Analysis of mass-energy balance of unmanned aircraft fueled by solar energy