The method of compensation of construction deformation for lagre spacectaft antenna

The method of compensation of construction deformation for a spacecraft transformed antenna is proposed within the application of a two freedom degree turn drive, located in the attachment point of a load-carrying structure with a reflector. The method allows compensating the antenna ration-technical characteristics degradation, caused by antenna structure deformation. In particula one of the deformation constituents is compensated as a shift main beam of the anglular pattern, relative to the nominal location in the spacecraft coordinate system (the location, demanded for a full value antenna functioning for the indentend application). The corresponding mathematical simulation was carried out, and as a result the efficiency of the method by example of an umbrella type offset antenna with 12 meters diameter is proved. While simulating the spacecraft is located on a geostationary orbit when the location of the Suns corresponds to the equinox position. The deformation compensating in sixteen position of a spacecraft on orbit was ceried out, which corresponds to maximum of antenna construction deformation (significant cases). The significant cases location belongs to one turn driving of a spacecraft on the orbit. The input data of calculation were the result of the antenna construction temperature analysis, with NII PMM of TGU in particularized software names ANSYS were cerried out. During the temperature analysis the directing sun radiation heating only takes into account. The major point of the method application is discussed referred to the spaceborne system of performance charactiristics control for large size transformed antenna, as well as the possible solution methods are considered.