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Methods and systems of inertial navigation and initial orientation of rocket and space technique

Work number - P 7 AWARDED

Presented Казенним підприємством спеціального приладобудування "Арсенал"

In research results of navigation instruments and systems creation, and also means of initial orientation for the rocket and space engineering are presented. The composition of means and systems of inertial navigation is described; paths of the decision of scientific and technical problems of creation of domestic sensors for strapdown navigating systems (SINS) are defined. New methods of calibration and testing of navigation instruments by means of SINS functional algorithms with use of multiple-purpose software «NavLab» are described. Such software allows realizing all SINS functional algorithms for testing, both in real-time mode, and at a stage of post-handling of files with arrays of experimental data. Besides, in this software mathematical models (simulators) of dynamics and device errors, and also generators of trajectories (test signals) that allow examining influence of different factors and conditions of use of navigation instruments be means of simulation modeling are included.

Results of sensors laboratory and field test, instruments and systems for the carrier rocket "Tsiklon-4", tactical missile "Grim-2", cruise missile "Neptune" are reduced.

Path of development of initial azimuth orientation instruments are defined. The theoretical fundamentals of modern orientation instruments constructed on the basis of feelers of various types are disclosed.

The basic modern technical decisions and tests of orientation instruments on the basis of a gyroscopic floating lever, the two-sedate sensor of an angular velocity and with used of SINS alignment mode are considered.