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Description of the pneumatic work cycle of the starting unit of the UAV launcher

Jastrzębski G.

Journal of KONES

2017

Vol. 24, No. 4

61--70

The publication presents a UAV pneumatic launcher designed and built in ITWL. The basic element of the pneumatic launcher is the launch mechanism. The starting mechanism determines the energy parameters that will be reached on the launch pad. The work of the launch engines used in propulsion systems has been reviewed and their advantages and disadvantages are discussed when used in pneumatic launchers. A detailed description of the author’s solution of the pneumatic launching mechanism from the launcher is presented. In order to determine guidelines for the design of pneumatic starter systems, a description of the cycle of operation of the complex pneumatic system was analysed. The description of the pneumatic system’s work cycle was based on the parameters of the flow of the compressed air C and b (C – the sound conductivity of the pneumatic element, b – the critical pressure of the pneumatic element). A set of equations describing the pressure change in the filled and emptied valve compartment and the equation of motion are presented. The equations of a mathematical model describing the pneumatic component and the replacement value of flow parameters for the pneumatic system of series pneumatic components are presented. For the mathematical model, a calculation algorithm is presented which takes into account the initial conditions and the boundary conditions of the various periods of the pneumatic system cycle. Examples of calculation results for a specific pneumatic trigger mechanism are shown. The results obtained were compared with the results of the pneumatic starter station tests and the mathematical model of the pneumatic starter was evaluated.