In superluminescent diode (SLD), the height difference between the two shoulders of the kovar bracket (referred to as the shoulder difference) has a significant impact on the rate of change of SLD full temperature power (ΔP). To reduce the rate of change of SLD full temperature power, this paper verifies the influence of four sets of double shoulder differences at different heights on SLD full temperature power, and establishes a quantitative relationship between double shoulder differences and SLD full temperature power stability. The experimental results show that the shoulder difference is less than 10um, the mean Δ P is 1.86%, and the standard deviation is 0.008; the shoulder deviation is between 10um and 20um, with a mean Δ P of 2.88% and a standard deviation of 0.014. The shoulder deviation is between 20um and 40um, with a mean Δ P of 3.87% and a standard deviation of 0.016; the shoulder difference is greater than 40um, with a mean Δ P of 5.9% and a standard deviation of 0.040.
Wide dynamic guided cannonballs need to be air-aligned after firing, and the precise acquisition of their initial roll angle has been a technical difficulty in the industry. In order to solve the problem that the driveless MEMS gyroscope cannot calculate the initial roll angle on a gentle trajectory, and the attitude information obtained by solving only the crest point is too few, this paper proposes a combined measurement scheme of driveless MEMS gyroscope and accelerometer based on adaptive complementary filtering technology, and the extended Kalman filter and Hilbert transform are used to solve the attitude calculation, which can obtain comprehensive attitude information and solve the problem of gentle trajectory attitude measurement of guided projectile. Both theoretical curve analysis and experimental results analysis prove the effectiveness of the method in this paper.
Fiber optic gyro (FOG) is a kind of angular velocity gyro based on the Sagnac effect, and the high reliability of long lifespan of the FOG are very important to the development of high requirement security control equipment. Spherical inertial measurement unit is designed, six axis redundancy FOGs is adopted, and the sensitive axis of any two gyros are not colinear, and the sensitive axis of any three gyros are not coplanar in this combination structure with a highly reliable orthogonal oblique configuration, when one of the sensitive components fails, other FOGs can also ensure the normal operation of the system, which greatly improves the accuracy, reliability and stability of the gyroscope. In the inertial measurement unit (IMU), the system works properly as long as the gyros in three different directions are working properly.
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