Parametric Approach To The Near Range Relative Orbital Maneuvering Control Problem

With the development of manned space flight, the study of near range relativeorbital maneuvering control problem becomes extremely important in the field ofspace technology. The typical control tasks of near range relative orbitalmaneuvering include space interception, space rendezvous, space hover, spaceflying around, etc. This thesis aims to study the near range relative orbitalmaneuvering control problem. This thesis presents unified solution framework tothe near range relative orbital maneuvering control problem, designs peremetriccontroller and conducts numerical simulation for specific maneuvering tasks. Themajor results consist of the following three parts.Firstly, a dynamic model describing spacecrafts near range relative motion isestablished. Starting from the equation which describes the absolute motion ofspacecrafts in the inertial coordinate system, under the assumptions of sphericalcenter of gravity body and near range relative motion, the dynamic equationdescribing relative motion in the target spacecraft orbital coordinate system isobtained by using some mathematical transformation. The dynamic equation iscalled C-W equation when target spacecraft’s orbit is circular or T-H equationwhen target spacecraft’s orbit is elliptical. The dynamic equation is transformedinto state space form, and then a unified mathematical description of the nearrange relative orbital maneuvering control problem is proposed.Secondly, a parametric approach is proposed to solve the near range relativeorbital maneuvering control problem. By using eigenstructure assignment andmodel reference output tracking control, the controller existence condition andthe algorithm of parametric approach design are derived. Then the solving ofcontroller design based on the parametric approach are discussed for specifictasks such as interception, rendezvous, hover and flying around. Numericalsimulations are provided to verify the effectiveness of the designed controller.Finally, the relative orbital maneuvering control problem when targetspacecraft’s orbit is elliptical is studied. Mathematical description of the relativeorbital maneuvering control problem is derived. Then the controller existencecondition and the algorithm of parametric approach design are discussed. Underthe hovering command signal, parametric controller design and numericalsimulations are given. The simulation results demonstrate the validity of the proposed method.