Simulation And Experiment Of Inertial Measurement System With Single-gyro And Multi-accelerometers

As a kind of routine suppression weapon, rocket launchers with rapid-firing can strong supporting the ground operations, but as the war prominent advantages, improve the change in patterns of long-range rocket fire strike accuracy is more urgent needs. In face of the limited funds, transformation for guidance with reasonable low cost is the effective way to make full use of unguided rocket artillery. At the same time, it has important significance for improving the adaptability and operational efficiency of the weapons and equipment for the war in the future.In the process of guidance transformation for rocket artillery, accurately obtaining its flight attitude, speed and location information during a flight is the precedent conditions for drawdown. Conventional munitions flight at a high speed rotation state after launching to increase their flight stability, but inertial measurement systems typically use the gyro to measure angular rate that is difficult to meet the high accuracy rate of angles in a wide dynamic range. Gyro-free inertial measurement system can be sensitive to the speicial force of the accelerometer array on the body to solve the angular rate indirectly, but low precision angular velocity exists commonly. To further improve the angular rate for calculating precision will need to introduce more accelerometer redundant information, and then increased the system cost burden. For the existing deficiencies of Inertial measurement solutions and the urgent needs, this paper discussed a effective solution to test the high rotation of ammunition effective and proposed an inertial measurement program which is based on single-gyro and multi-accelerometers. This program based on the application environment of high-rotation munitions, combining the conventional inertial measurement programs and non-gyro inertial measurement solutions, introducing the external assistance of gyros to solve all the angular motion information. The program also has the advantage of low costing, small size and high accuracy except meeting the harsh demanding with the environment. It realized to test the whole attitude, position and other inertial parameters of the projectile in flight.