Optimization of a New High Rotary Missile-Borne Stabilization Platform

Abstract

The passive semi-strapdown roll stabilized platform is an inertial platform, which can isolate the rolling of a projectile body by a special mechanical device. In the passive semi-strapdown roll stabilized platform, the bearing device plays an important role in isolating the rolling of the projectile body. The smaller the friction moment of bearing, the smaller the swing angular velocity of the platform, the smaller the range of inertial sensors required, the higher the accuracy of the navigation solution. In order to further reduce the swing angular velocity of the platform and improve the navigation accuracy, the bearing nested structure that could reduce the friction torque is proposed. Combined with the working principle of the passive semi-strapdown roll stabilized platform, the mechanical calculation model of friction at the moment of bearing the nested structure was established. A series of simulation analysis and tests showed that the output stability value of the friction moment was 47% that of a single bearing; the roll rate of the platform based on the bearing nested structure decreased to 50% of that based on the single bearing structure; the position and attitude errors measured of the platform based on the bearing nested structure decreased to more than 50% of that based on the single bearing structure. It showed that the bearing nested structure could effectively reduce the friction moment, improve the axial reliability of the bearing, and provide a more stable working environment for the passive semi-strapdown roll stabilized platform.

Optimal Design and Analysis on High Overload Buffer Structure of Passive Semi-Strapdown Inertial Navigation System

“…The core part of passive semi-strapdown inertial navigation measurement unit is the isolation rolling platform, which is designed based on the compound pendulum movement under gravity, the remaining strapdown with the projectile in pitch and yaw bearing, and connection with the projectile in rolling axis via bearing; its mechanical model is shown in Figure 2. The isolation rolling platform retains the stable compound pendulum movement in a balanced position under the friction torque between the gravity restoring torque and the bearing friction torque so as to reach the high-speed rotation of the isolation projectile and provide an appropriate measurement environment for the MIMU with a low measurement range and a high accuracy [21]. The outer cylinder is installed with an optical encoder to measure the relative the angle between the isolation rolling platform and the projectile on the rolling axis [22].…”

A Low-Cost MEMS Missile-Borne Compound Rotation Modulation Scheme

“…However, the measurement errors of the inertial devices themselves introduced into the navigation solution cause the errors to accumulate over time [ 1 , 2 , 3 , 4 ]. Especially in the practical application of missile environment, long-term storage will lead to constant error drift, and the special application conditions determine that the IMU, which is mounted on the missile, cannot timely and accurately calibrate in advance [ 5 ]. RM technique is used to modulate the constant and slowly changing drift into sine/cosine form by periodically rotating one or more axes of the inertial navigation system [ 6 ].…”

Integrated Guidance and Control Using Model Predictive Control with Flight Path Angle Prediction against Pull-Up Maneuvering Target

“…Research on missile guidance and control fields is being actively conducted nowadays, as it has always been [1][2][3][4][5][6][7][8][9][10]. Traditionally, the guidance system and control system of an interceptor missile are separately designed.…”

“…All of the aforementioned guidance studies [1][2][3][4][5][6][7][8][9][10], as well as advanced guidance research such as Impact Angle Control Guidance (IACG) [11][12][13], Impact Time and Angle Control Guidance (ITACG) [14], or circular navigation guidance [15] only consider some form of guidance problems. As they are combined with the control loops, most of them suffer from terminal instability issues in the vicinity of the impact.…”