Low Orbit Spacecraft with Earth Orientation Device

摘要

The utility model relates to the field of aerospace instrumentation, in particular to optical-electronic devices for orienting spacecraft (SC), and can be used in the design of onboard automatic control systems for spacecraft. This technical solution can be used for Earth orientation instruments that make radial intersections of the horizon (hereinafter “serifs”) with an instant field of view. On low-orbit spacecraft, the lower edge of these “serifs” can be located at angles of more than 90 ° to the axis of the device, which makes it difficult to place it on the spacecraft The essence of the claimed technical solution lies in the fact that additional mirrors are placed on the spacecraft’s body, directing the lower part of each “notch” in the direction of the adjacent “notch”, so that the viewing angles (angles between the axis The field of view and the axis of the device) in the entire field of view of the device do not exceed 90 °.