The Calibration Scheme Optimal Design Of Strapdown Airborne Gravimeter

The calibration of inertial navigation system is a prerequisite for inertial navigation,calibration results have a direct impact on the quality of inertial navigation accuracy.It is a widely studied and applied technology with high technology maturation that calibrating inertia devices with high-precision rotary.The commonly used method is to estimate gyro parameters based on the rotational angular rate test,and estimating accelerometer parameters according to the multiple posited static test.There is a complete scheme of calibrating inertial navigation system now in the laboratory.However,there are different calibration methods in different application environment to the performance indicators of different products.In airborne gravity measurements of flight,the sensitive value of the accelerator towards sky is about 1 g and the output will fluctuate in the stability of pulse.Because The dynamic characteristics of airborne cause a large error to the scale factor of the accelerator,so we should improve the calibration method of the accelerator based on the present calibration method to induce the calibration error.In this paper,we analyse the principle of error production to design a accelerator's calibrating plan in [0.5g,g],and produce a model of turntable error and simulate it.At last,we improve the navigation accuracy of the strapdown airborne gravimeter and induce gravity vector error by navigation test.