Study On Autonomous Orbit Correction Method Of Large Elliptic Transfer Orbits

A wide range of orbital transfer is one of the key technologies in using kinetic energy weapons to attack enemy's high orbit aero spaces. Suffering from orbital perturbations and the initial orbit error, a drift relative to its nominal orbit will occur during the large ellipse orbit transfer and the apogee accuracy will be degraded. So, a middle way correction is needed to satisfy the requirement of the mission. Aiming at acquiring high apogee accuracy, this paper does research in middle way correction control during the large elliptic orbit transfer and has got such achievements.A control method based on the terminal of Lambert problem was proposed. Based on the current state of the spacecraft, make the transfer nominal terminal as control target, the Lambert algorithm was used to re-plan the transfer orbit, and impose appropriate controls make the spacecraft entering the transfer orbit. The optimization model of one correction contol in the middle way was establishen, The optimal middle correction time algorithm of the optimal fuel-teminal position bias algorithm was given, A method of the nominal terminal correction for the transfer orbit was designed, and orbit change control pulse was was corrected due to pattern search. The simulations show the algorithm has high control precision.A control strategy based on the nominal orbit was proposed. According to the current state of the spacecraft, make the nominal transfer orbit as control target, the use of relative position and relative velocity of the nominal virtual spacecraft in the nomial orbit as the control input, the correction time-fuel optimal law based on pseudo-control was designed, the whole transfer orbit correction control was finished autonomously by the law, The stability was analyzed in theory, and numerical simulations further demonstrated the feasibility and effectivity of the algorithm. Compared to terminal control method, the proposed algorithm can achieve high accurate control without re-planning transfer orbits, but with large fuel consumption.Finally, the effect of deviation of the thruster magnitude and direction for orbrt control precision was analyzed. An orbit thruster calibration algorithm was designed, an autonomous correction method was given, via the mathematical simulation, the orbit control precision was analyzed with the presence of entering orbit time bias and entering orbir location deviation. The results show the method is feasible with little computation for real-time orbit control.