Abstract
Long March 7 (CZ-7) launch vehicle is China’s new generation of non-toxic, non-polluting, high performance, low cost and high thrust medium launch vehicle series. As an important part of launch vehicle flight control system, the main function of the guidance system is to control the center of mass motion using the motion parameters provided by navigation system, ensure that the launch vehicle along a predetermined trajectory. At present, CZ-7 launch vehicle guidance system used global navigation satellite system (GNSS) and the strapdown inertial navigation system (SINS) loosely integrated navigation mode. In the first flight phase of launch vehicle, the positioning antenna of satellite receiver disturbed largely, and launch vehicle injection accuracy is decided by the guidance accuracy of second flight phase, thus GNSS/SINS loosely integrated navigation mode used only in the second flight phase of launch vehicle. In order to further improve injection accuracy of CZ-7 launch vehicle, the BD2/SINS deeply integrated which applied in the CZ-7 launch vehicle guidance system are discussed in this paper. The system structure and applicability condition for BD2/SINS deeply integrated navigation are analysis briefly in the paper, based on the new characteristics of CZ-7 launch vehicle. The research results can provide a theoretical basis and technical support for the new launch vehicle guidance system.
Published Version
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