Study On The Range Of Spacecaft Orbital Maneuver And Track Optimization

Along with the rapid development of space technology, more and more peopleare focusing into outer space, the various countries are vigorously expanding theresources for active use of outer space, in order to compete and control the limitedexternal space resources, inevitably there will be a space combat. In the space ofconfrontation process, require a large range of spacecraft orbital maneuveringcapabilities, so as to ensure to occupy military and technological high ground. Inaddition to considering the context of war, in human space exploration process, theorbital maneuvering technology also plays an irreplaceable role, such as in-orbitservicing of satellites in orbit filling, emergency rescue operation will involve aseries of orbital maneuvers technologies. Meanwhile, in order to fuel the optimal oroptimal time as the optimization target orbit optimization techniques, will play tothe maximum extent spacecraft role.In this paper, considering perturbation factors (Earth flat rate, atmosphericdrag) under the influence after a numerical way to get a spacecraft in the pulse andcontinuous finite thrust spacecraft orbit under the action of the reach ofmaneuvering, including absolute and up range Relative up range, which is theorbital optimization design provides a certain theoretical basis. Finally for largeinclination orbit maneuver to change this process can be optimized to time optimalas the optimization targets, obtained the trajectory of the spacecraft and otherrelevant parameters.For absolute reach of spacecraft problems, namely the spacecraft orbitalelements of the changes, we use numerical methods, were calculated pulse andcontinuous finite thrust under the absolute reach of spacecraft and analyzed throughthe Gauss equation The results were compared to verify the accuracy of numericalcalculation and kinematics of the Gauss equation in orbit on the application, butwill calculate the orbital elements of double pulse on the impact of changes.For the relative reach of spacecraft problems, namely the distance between thetwo spacecraft changes, this article uses the same method to calculate numericalcalculation, obtained in the pulse and continuous action of two finite thrust relativereach of spacecraft. Optimal design for the track, combined with large inclination orbit maneuverthis instance, the use of mixing and Gaussian pseudo general methods, combinedwith the corresponding nonlinear programming algorithm to optimize the design,and ultimately won the same principles and minimum values of the solution. Verifythe Gauss method as a pseudo P emerging theory, without transverse conditions, thesolution orbital optimization problems.