Noncopanar Rendezvous Orbit Design And Guidance Method For Satellites

With the development of aerospace science and technology and people’sexploration of outer space having been furthered, the competition for outer space hasbecome increasingly fierce, and it has become a urgent and important task to foundfacilities of large-scale in space. It tends to occur that the facilities in outer space needto be supplied, fuel, or regular maintenance, repair or recycling. Thus, it can’t livewithout the support of satellite rendezvous technique. Thence, the study of satelliterendezvous technique is especially significant. In this background, this treatise is aresearch of satellite tracking and target satellite using coplanar Hohmann transfer tomeet and guiding the satellite tracking in zero control orbit.First of all, this article introduces several common coordinate systems and buildssome models of satellites’ rendezvous and guidance, including the dynamic model andkinematic model of satellite tracking and target satellite.Then, this article introduces several common designs of satellites rendezvous inbasically and does some research of the principle of Hohmann transfer rendezvous,including the features of Hohmann transfer and the requirements it has to fulfill.Besides, based on the research of Hohmann transfer, it analyzes the coplanar Hohmanntransfer and divides this into three cases, based on the consideration of features of theorbital parameters of coplanar intersection. It also does some research of therequirements of the satellites’ coplanar intersection in those3cases and reaches anconclusion of the coplanar Hohmann transfer.After that, since the thrust of the booster engine when the chase satellite enterHohmann transfer orbit is not large enough and the time it acts cannot be ignored, thechase satellite has deviated from the Hohmann transfer orbit when the action of thrust iscompleted. In this way, it adopt the approach of zero control track to correct the chasesatellite and reach the conclusion of the orbit control engine act to correct the orbit andthe attitude angle need to adjust.Last, several charts of the final position, attitude angle and fuel consumption oftarget satellite and chase satellite got by simulation was drawn and an analysis of theeffect of satellites coplanar rendezvous and guidance using zero control orbit.The work of this article, offers theoretical support for satellites coplanarrendezvous and guidance using zero control orbit and plays an important role inpromoting the development of satellite rendezvous technique.