2results about How to "Eliminate static errors" patented technology

This invention relates to the field of integrated circuit technology and discloses a three-temperature equipment gas heating system, comprising four modular heating groups connected in parallel to the main air intake pipeline. Each group includes a first-stage electro-gas heating unit, a series connecting pipeline, and a second-stage electro-gas heating unit. The two stages of heating units are connected by a Teflon flexible pipeline. The main controller controls the first-stage electro-gas heating unit to undertake 70% of the total system heat load for large-temperature-rise coarse preheating, and controls the second-stage electro-gas heating unit to undertake 30% of the total heat load for small-temperature-rise fine-tuning heating. This invention overcomes the thermal inertia lag and temperature overshoot caused by single-stage heating through stepped temperature rise distribution and segmented composite dynamic control, controlling the steady-state temperature fluctuation of the output airflow within ±1 degree Celsius, and utilizing a redundant architecture to ensure the continuous gas supply capability of the equipment under single-point failure.

The invention relates to a target projectile launching device attitude control method, which is based on integral separation PID (Proportion Integration Differentiation) target projectile launching device attitude control, and comprises the following steps: 1) setting the number of particle swarms and the initial position and speed of each particle; 2) for each particle, calculating the corresponding performance of the control system according to the current position of the particle; 3) for each particle, comparing the current fitness with the historical optimal fitness, and updating the optimal position of the individual; 4) finding out the particle with the best fitness from all the particles, and calling the position of the particle as a global optimal position; 5) updating the speed and the position of the particle based on the individual optimal position and the global optimal position of each particle; according to the method, the attitude control which is rapid, stable and high in precision is realized, and the working efficiency of preparation work before launching is improved. The method comprises the following steps of: (1) carrying out the following steps of: (2) repeatedly executing the steps (2) to (5) until a preset stop condition is met, and (7) outputting a PID parameter corresponding to a global optimal position as a final optimal solution when the stop condition is met.