METHOD FOR DETERMINING traction HYPERSONIC ramjet engine according to the results of flight test of its hypersonic flying laboratory

摘要

method u043eu043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 force u0442u00a0u0433u0438 u0433u0438u043fu0435u0440u0437u0432u0443u043au043eu0432u043eu0433u043e u043fu0440u00a0u043cu043eu0442u043eu0447u043du043eu0433u043e air jet u0434u0432u0438u0433u0430u0442u0435u043bu00a0 results of flight testing it on u0433u0438u043fu0435u0440u0437u0432u0443u043au043eu0432u043eu0439 flying u043bu0430u0431u043eu0440u0430u0442u043e u0440u0438u0438 (u0433u043bu043b), including the measurement of overload, the aerodynamic forces along the axis of u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 u0441u0432u00a0u0437u0430u043du043du043eu0439 u0433u043bu043b, the u0442u00a0u0433u043eu0442u0435u043du0438u00a0 and u0442u00a0u0433u0438 u0434u0432u0438u0433u0430u0442u0435u043bu00a0, defined s u0443u0441u043au043eu0440u0435u043du0438u00a0 force u0442u00a0u0433u0438 in flight, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 orderwhat previously known aerodynamic characteristics u0433u043bu043b large aerodynamic quality u0432u044bu0447u0438u0441u043bu00a0u044eu0442 u0437u043du0430u0447u0435u043du0438u00a0 angular measuring axes the three accelerometers on the longitudinal axis u043eu04451 respectively from the conditions of equality to zero vector full aerodynamic forces, the minimum and the maximum h u0443u0432u0441u0442u0432u0438u0442u0435u043bu044cu043du043eu0441u0442u0438 accelerometers to u043au043eu043bu0435u0431u0430u043du0438u00a0u043c angle of attackwhich u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 private derivative on the angle of attack of the aerodynamic coefficients u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 angles of inclination measurement axes accelerometers u043eu0442u043du043eu0441u0438u0442u0435u043b u044cu043du043e construction axis u043eu04451 u0433u043bu043b on formulas;where d, DX1, DY1 - angles of inclination measurement axes of the three accelerometers on the construction axis oX1 u0433u043bu043b, computed by the formulae (1, 2, 3).;k - lift to drag ratio.;angle of attack;- private derivatives on corner attack from the corresponding aerodynamic coefficients;then, according to this calculation, establish the accelerometers at the centre of gravity u0433u043bu043b, measurement control in flight u0432u044bu0447u0438u0441u043bu00a0u044eu0442 force u0442u00a0u0433u0438 u0434u0432u0438u0433u0430u0442u0435u043bu00a0 on fort mule:;where is the angle of vector forces u0442u00a0u0433u0438 on u043eu04451 u0433u043bu043b construction axis.;nDT - average for the period of the attack value of overload, an accelerometer with a first angle d, if the u043fu043eu043au0430u0437u0430u043du0438u00a0u0445 third axel u0435u0440u043eu043cu0435u0442u0440u0430 angle of the DY1 present high frequency u043au043eu043bu0435u0431u0430u043du0438u00a0 overload from variations in angle of attack, and in the u043fu043eu043au0430u0437u0430u043du0438u00a0u0445 second accelerometer with angle DX1 he and there is no use value nDT,in the absence of the high frequency fluctuations in the angle of attack also use value of the overload nDT at the first sensor, which will u0441u043eu0445u0440u0430u043du00a0u0442u044cu0441u00a0 u043fu043eu0441u0442u043eu00a0u043du043du044bu043c and u0437u0430u0432u0438u0441u00a0u0449u0438u043c only with the force of u0442u00a0u0433u0438 u0434u0432u0438u0433u0430u0442u0435u043bu00a0.