Abstract: The subject of the invention is a detonation rocket engine comprising an annular detonation chamber (5) connected to the Aerospike nozzle (4) and lines (2, 3) for supplying propellant components connected to the detonation chamber (5). The detonation chamber (5) has a bottom (9) connecting the inner wall (10) and the outer wall (11) between which the outlet (6) is formed. At the outlet (6) of the detonation chamber (5) there are at least three evenly distributed centring elements (1) connecting the inner wall (10) and the outer wall (11) of the detonation chamber (5), with cooling channels (7) connected to one of the lines (2, 3) supplying the propellant components to the detonation chamber (5).

Abstract: The subject of the invention is a detonation rocket engine comprising an annular detonation chamber (5) connected to the Aerospike nozzle (4) and lines (2, 3) for supplying propellant components connected to the detonation chamber (5). The detonation chamber (5) has a bottom (9) connecting the inner wall (10) and the outer wall (11) between which the outlet (6) is formed. At the outlet (6) of the detonation chamber (5) there are at least three evenly distributed centring elements (1) connecting the inner wall (10) and the outer wall (11) of the detonation chamber (5), with cooling channels (7) connected to one of the lines (2, 3) supplying the propellant components to the detonation chamber (5).

Abstract: A microwave-based radio system for realising a precise landing approach (MLS), characterised in that an azimuth antenna transmitter and/or an elevation signal transmitter and/or a DME transmitter, and preferably all three said transmitters, are placed aboard an unmanned aerial vehicle, and in particular on a drone. The object of the disclosure is also a method for realising a precise landing approach using such a system.

Abstract: A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine includes a spray nozzle, a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle. During operation, both a liquid fuel and the gaseous carrier are supplied to the fuel mixing and evaporation chamber of the injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture reaches the combustion chamber. The gaseous carrier is air or, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has an oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

Abstract: The invention relates to a fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine, is characterised in that it comprises: a hydrocarbon liquid fuel spray nozzle, at least one supply of a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle to the engine combustion chamber (C.C.), configured such that, during operation, liquid fuel is supplied and heated and compressed gaseous carrier are supplied to the fuel mixing and evaporation chamber of this injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture of evaporated fuel with a hot gaseous carrier with low oxygen content thus formed reaches the combustion chamber (C.C.

Abstract: A computer-implemented method for in-flight assessment of freedom from flutter of an airplane, involving analyzing the airplane structure vibrations based on signals indicated by sensors located on the airplane structure. The computations are performed in real-time based on current measurement data collected from the sensors. For measurement data from individual sensors there are determined mode shapes of vibrations. The relevancy of modes of vibrations is determined by subtracting from the vibrations signal the particular mode of vibrations and calculating the value of decrease in the rest sum of squares.

Abstract: A computer-implemented method for in-flight assessment of freedom from flutter of an airplane, involving analyzing the airplane structure vibrations based on signals indicated by sensors located on the airplane structure. The computations are performed in real-time based on current measurement data collected from the sensors. For measurement data from individual sensors there are determined mode shapes of vibrations. The relevancy of modes of vibrations is determined by subtracting from the vibrations signal the particular mode of vibrations and calculating the value of decrease in the rest sum of squares.

Abstract: This invention solves the problem of obtaining of a higly-efficient ultrasonic diffuser.An ultrasonic diffuser according to this invention consisting of a ring with equally spaced channels shaped by inter-channel walls permanently connected to at least one side wall of the diffuser is characteristic in that on the inlet side of the diffuser there are inter-channel walls (3) converging (S1, S2, S3 and S4) towards the axis of the diffuser ring (1), and that, on the side of the inside diameter, the diffuser has removable side walls (6 and 7) which can be provided with sharply terminated partial vanes (8).