| 摘要 |
FIELD: transport.SUBSTANCE: set of inventions relates to a structure of parts and elements of aflying device, predominantly to arrangement of a spaceplane (SP) afterbody, as well as to methods for a trajectory correction and optimisation of lift of the SP rocket motor. The SP fuselage (11) in the afterbody is provided with an annular skirt (10) where the rocket motor (2) nozzle (4) is located. Panels or blades (3a, 3b, 3c, 3d) are pin-jointed to the skirt (10). These blades are moved and can firstly take up position of the nozzle (4) masking (protection) and lowering the SP afterbody effect. In this position the blades (3a, 3b, 3c, 3d) extend the SP fuselage (11). Secondly, the blades can be fully deployed in the position of the SP aerodynamic resistance increase. In both cases the rocket motor (2) is switched off. Finally, the blades (3a, 3b, 3c, 3d) can take up multiple intermediate positions between the said first and second positions. In these positions when the motor (2) is switched on its power optimisation is achieved by means of degree of the jet expansion control using the blades. By asymmetrical deflection of blades, direction of the SP motion along a trajectory is changed. This is possible both when the motor (2) is switched on and switched off (when the SP flies in the atmosphere).EFFECT: providing fuselage afterbody structure with active functions for the aircraft (SP) motion control virtually in all flight phases and thereby lowering the overall mass of the vehicle auxiliary systems.19 cl, 9 dwg |
