Abstract: An inflation control apparatus includes seal heads at ends of a container liner on a rack; a rotary inflation connector includes a static component and a rotating component. The rotating component is connected with the seal head; an inflation core tube is in the container liner, air holes are in the inflation core tube, and the two ends of the inflation core tube are connected with the static component of the rotary inflation connector respectively. A temperature and pressure sensor is in the container liner; an air compressor provides air for an air heater, the air heater introduces the heated air into an air inlet of the inflation core tube, an air outlet of the inflation core tube is connected with an air inlet of a flow regulating valve, and an air outlet of flow regulating valve is connected with an air inlet of the air compressor.

Abstract: A method for controlling an antenna of a mobile communication application system based on double quaternions in MEMS inertial navigation. The method comprises: introducing an antenna control quaternion based on a navigation attitude quaternion; in each interrupt cycle of a navigation computer, updating the two quaternions respectively using a carrier system measured by a gyroscope relative to a rotation vector of an ideal platform coordinate system; in each filter cycle, correcting the error of the navigation attitude quaternion respectively using a Kalman filter; according to the relationship between the attitudes determined by the two attitude quaternions, determining the angular speed in an antenna control instruction; and finally, driving a servo system to rotate at an antenna servo control angle converted by an antenna control quaternion attitude.

Abstract: A method for controlling an antenna of a mobile communication application system based on double quaternions in MEMS inertial navigation. The method comprises: introducing an antenna control quaternion based on a navigation attitude quaternion; in each interrupt cycle of a navigation computer, updating the two quaternions respectively using a carrier system measured by a gyroscope relative to a rotation vector of an ideal platform coordinate system; in each filter cycle, correcting the error of the navigation attitude quaternion respectively using a Kalman filter; according to the relationship between the attitudes determined by the two attitude quaternions, determining the angular speed in an antenna control instruction; and finally, driving a servo system to rotate at an antenna servo control angle converted by an antenna control quaternion attitude.