| 摘要 |
FIELD: equipment of launch vehicles and space vehicles used in test launches. ^ SUBSTANCE: the offered stage has systems of control and measurements of the launch vehicle parameters, adapter with space vehicles installed on it and an additional measuring system. The latter is provided with a self-contained supply system and a system of data transmission to ground points via a satellite network. The given additional system is made in the form of two self-contained subsystems, one of which is installed on one of the space vehicles and connected to the system of transmission of data of this space vehicle to the ground points. The other subsystem is installed in a pressure container, connected to the transducers of the launch vehicle parameters measuring system, has temperature-sensitive elements installed on the end face of the pressure container, and acceleration transducers. The subsystem installed on the space vehicle is provided with an equipment for determination of the coordinates of the launch vehicle stage via a satellite navigation system. When the space vehicle is a component of the stage, this subsystem is connected to the launch vehicle control system and its chemical supply source. The subsystem in the pressure container is additionally supplied from solar batteries. The space vehicle and the pressure container are installed on the end face of the adapter on the side of the incoming aerodynamic flow. The height of installation of the space vehicle exceeds that of the pressure container. This provides for screening of the point of measurement of the air flow temperature by the space vehicle after the release of the launch vehicle fairing. ^ EFFECT: enhanced contents and accuracy of obtained information. ^ 4 dwg
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