Research On Trajectory Optimization And Guidance Of Orbital Transfer Vehicle

With the development of the satellite on-orbit technology, the use of orbit transfervehicles has become more and more needs, such as the optimal energy to complete theorbit transfer task, the interaction between the orbiter and the improvement of thevehicle life circle, etc. The orbit transfer vehicles which can provide many solutions tothese missions have drawn much attention in recent years, which involve the orbiter’sstructural design, modeling, trajectory optimization and guidance and control. Thispaper covers research on near-Earth orbit missions which is commonly used, and theresearch is summarized bellow as follows:According to the characteristics of near-Earth orbit Transfer Vehicle missions,different kind of modeling method is discussed, which include two-body problem modelunder inertial coordinate system, CW model and its improved form under LVLHcoordinate system, improved orbit model under gauss coordinate system, nonlineardynamics model under ADBARV coordinate system. By these models, different kindsof orbit transfer tasks are easily described.Summarized orbit transfer trajectories to intercept and rendezvous mission aircraftoutside the atmosphere optimization methods. Indirect method and direct polynomialmethod are used to solve orbit transfer optimization problem with different type ofthrust. Limit continuous thrust orbit interception, continuous thrust orbit rendezvous,pulse thrust orbit interception, pulse thrust orbital rendezvous problem has beendiscussed. Differential-algebraic method has been used to analyze the impact of theinitial orbit errors and ignition timing errors on impulse orbit transfer missions.Summarized orbit transfer trajectories within the atmosphere during the orbittransfer process, indirect method and multi-stage adaptive pseudo-spectral method havebeen used to solve the problem of aero-assisted orbital transfer. Analysis has been doneto fuel optimal control for coplanar orbit transfer mission and non-coplanar orbittransfer. There are two kinds of non-coplanar orbit transfer methods, which is aero-glidemethod and aero-cruise method. For the case of heat flow rate limit, aero-cruise methodhas been proved good performance.For aeroassisted orbital transfer tasks, a composite guidance method which havecombined feedback linearization guidance method and matched asymptotic expansionguidance method is given. The method improved the traditional method of consideringonly the terminal and terminal performance constraints, which leads large guidanceerror between trajectory and nominal optimal trajectory, using the way of the track nearthe piecewise linearization method to simplify the problem. Latitude has been used asthe free variable to rewrite the equation, which is aimed to avoid the free variable ignition timing and late after the estimated impact of the guidance and control, such as apseudo-error. The position change method of the centroid has been proposed in orbitaltransfer vehicle guidance and control methods which has been proved to be an efficientway to achieve the guidance and control target. By precisely measuring and controlingthe position change method of the centroid, to get the desired angle of attack andsideslip angle, thus, achieve guidance control.