Reserch And Analysis On Iterative Guidance Self-adaptablility Of Vehicle Base On Precise Control Of Solution

In order to meet the requirements of space activities in the future, Countries ismaking great efforts to develop the launch vehicle technology to support theirability and level of access to space. Since its own complexity of space explorationtask wanting higher requirements of the launch vehicle, it needs a kind of highprecision and well adaptive guidance method to achieve the high-precision orbitalinsertion, in another word, it put forward higher accuracy requirements of launchvehicle guidance system. This paper studies the iterative guidance method based onprecise control of solution which didfferent from traditional in the calculationformula of the value of the geocentric angle, the gravitational loss amendmentconstant K and the exact command to control the attitude angle, and then analyzesits adaptability Systematic. The specific work includes the following aspects.Firstly, this paper established launch vehicle’s dynamics and kinematics model,gave a derivation of the optimal control solution in the form of what based onoptimal control theory, simplified Launch vehicle’s equation of motion based on itsflight characteristics, derived the calculation formula of remaining time by aniterative approach, calculated the value of the geocentric angle, derived thecalculation formula of the gravitational loss amendment constant K, and alsoderived a formula for calculating the exact command to control the attitude angle,therefore, completed the specific process of iterative guidance method whichdidfferent from traditional.Secondly, based on the above established guidance model, this papercompleted launch vehicle simulation example based on the two orbital mission, putforward programs of the amendment directives in a corner of the last paragraph toimprove the guidance accuracy which proved the validity of the iterative guidancemethod described in this article.Thirdly, in MEO tasks, this paper made simulation and analysis of theadaptability of the methods provided that it happen deviations such as enginespecific impulse, sec consumption, initial mass, initial position, speed deviation,pitch angle, yaw angle command. And the self-adaptation of the iterative guidancemethod described in this article provided that it has sudden faults in launch vehicle guidance flight phases such as engine specific impulse, sec consumption, andguidance commands transmission. The simulation results demonstrate that theiterative guidance method has a good self-adaptability.