Measurement And Alignment Of Remote Controlled Trajectory Correction Ballistics Projectile

In this paper, based on theory research, the correction methods of Remote Controlled Trajectory Correction Ballistics Projectile (RCTBP) in low rotate speed were studied considering the present situation of domestic weapons.1. Utilizing modern micro-electronics techniques and nonlinear filter, the measure of RCTBP's gesture and the methods of aglinment were proposed based on Dopple Radar and Three Axis Magnetometer (TAM).2. The 6 Degree of Freedom simulation model was established for trajectory correction projectile, Based on the model, the characteristic of the trajectory correction with the impulse force engine was studied, the effects of impulse interval, impulse force, plus attackangle vibration and attenuation on the correction distance only with impulse force during the flight were analyzed . It can be concluded from the research that there is an optimization ignition time (OIT) and it should be chose. If the impulse force does not work on the centroid of projectile, the correction effect under OIT can achieve that when force work on the centroid, the machining and assemble tolerances can be lower, and a better correction can be achieved.3. TAM are broadly used in MAVs (Micro Air Vehicle) with the characters of large batch, high consume and limited space. However, there exist problems of bad in anti-jamming and bringing in system errors of magnetism navigation. An algorithm based on ellipse-specific fitting error compensation method were brought out to quickly calculate the gestures of trajectory correction projectile. After the analysis of error, ellipse hypothesis and the characters of RCTBP attiude, the process of the algorithm and experiment results were presented in detail.4. Considering the movement characters of RCTBP, the installations of Gyros-free Micro Inertial Measurement Unit (GFMIMU) , and Strapdown inertial navigation were analyzed with the use of GFMIMU , Current statistical model and the outlies, a new method is proposed. It can be concluded from the experimental research that with correct accelerometer installation and Kalman Filter, the cumulate errors can be reduced to some extent. Utilizing assistant navigation equipment, the precision of GFMIMU can be improved good enough to be used in navigation of RCTBP under dynamic situation instead of pursuing for high precision accelerometer. 5. The methods of combination measure and agliment , the error model and the simulation results were introduced in this chapter. Considering the aiming process of Remote Controlled Trajectory Correction Ballistics Projectile, every matching scheme of initial aiming was analyzed ,and then it is believed that velocity matching plus attitude change matching is fit for correction of projectiles. After analyzing the error model of Strapdown inertial navigation Unit, the simplifications of error eos(equations of state) and observation equations are proposed. Aiming at Unscented Kalman Filter, the method for the calculation on sigma point was improved with the use of SRUKFå’ŒGuass-Newton UKF, the error situation satisfy the initial aiming demand.