Rocket last-stage attitude time-sharing control method and device based on fuzzy membership function

Abstract

The invention relates to a rocket last-stage attitude time-sharing control method based on a fuzzy membership function, a fuzzy logic strategy is introduced into a last-stage rocket body attitude control system of a simplified side jet flow device, and the side jet flow device comprises a plurality of axial and radial jet pipes arranged on the outer side wall of the circumference of a cylindrical rocket body. The jet pipes jet airflow to provide pitching, yawing and rolling control moments for the rocket body, the final-stage attitude of the rocket is controlled according to the control characteristic quantity, different control jet pipe combinations are reasonably selected by using fuzzy logic rules, and a control strategy is executed. The core of the method is fuzzy logic design, a fuzzy control stylization method is utilized, the characteristic control quantity attitude angle and the attitude angular rate obtained through calculation of an inertial measurement unit are used as input, a fuzzy strategy is generated, then a corresponding control spray pipe is selected to act to apply control torque to a rocket body, and the attitude angle and the angular rate of the rocket body are changed. And the rocket body attitude meets the design requirements.

Description

technical field [0001] The invention belongs to the field of side jet attitude control of carrier rockets, and in particular relates to a time-sharing control method, device, electronic equipment and storage medium for rocket final stage attitude based on a fuzzy membership function. Background technique [0002] The core task of the launch vehicle is to send the given load to the predetermined orbit. During the entire final stage of flight, the launch vehicle will continuously correct the orbit through the guidance algorithm. The highly reliable side jet device (attitude control system) acts as a It is one of the main means of attitude control of the launch vehicle in the final flight stage. The orbital accuracy of the launch vehicle largely depends on the control accuracy of the side jet attitude control system. Since the side jet control itself is a switch control, and the nozzle cannot be opened and closed at any time, when forming a closed-loop control structure , the ...

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Problems solved by technology

The orbital accuracy of the launch vehicle largely depends on the control accuracy of the side jet attitude control system. Since the side jet control itself is a switch control, and the nozzle cannot be opened and closed at any time, when forming a closed-loop control structure , the side jet flow is a very significant nonlinear link, and the traditional side jet flow attitude control algorithm based on the limit cycle is generally used. The design method based on the limit cycle analyzes the dynamic process of the system on the phase plane. The switch area of ​​the arrow body makes the attitude angle and the attitude angle rate of the rocket body form a limit cycle on the phase plane, and achieves the purpose of simultaneously limiting the attitude angle and the attitude angle rate of the rocket body within a given interval, but this design method ignores the The disturbance that may exist during the flight of the body will disturb the shape of the limit cycle, resulting in a difference between the designed target attitude angle and attitude angle rate range and the actual value

At the same time, in order to reduce the production cost of the rocket and shorten the research and development period, on the premise that the side jet flow device can provide sufficient control ability to ensure the stable flight of the rocket, the number of execution nozzles is reduced, the layout of the nozzles is simplified, and the control of multiple channels is adopted. Using some strategies of the same nozzle, this also brings great difficulty to the traditional control method

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