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The problem of the formation of an optimal control program spacecraft with low thrust at flight between the noncoplanar elliptical and geostationary orbits is considered. A scheme for the joint change of orbital elements within the simple structure of the thrust vector control on the circuit is offered. [ABSTRACT FROM AUTHOR]

The problem of control program formation during orbital rendezvous maneuver at low Earth orbits is studied. Rendezvous of two spacecraft are considered. The first is an active spacecraft, equipped with low-trust engines and, the second, is passive spacecraft. Using the linearized equations of motion, the secular and periodic components of relative motion are explicitly allocated. The control program is a consistent correction of the relative motion parameters to the specified values with transversal and binormal trust direction. During formation of the control program, the analytical solutions and the iterative procedure are used. The numerical simulation of rendezvous maneuver is carried out. [ABSTRACT FROM AUTHOR]

The air of this work is study possibility of caring out inspection maneuvers of International Space Station (ISS) using Spacecraft-Inspector (SCI) that equipped with electric propulsion system. We study simple maneuvers – distinction SCI from ISS and transferring SCI to stationary point, circumnavigation transfer to ellipse or point. Motion is studies in orbital cylindrical reference frame. Control programs defined in linearized model of motion. Numerical simulation of relative motion carried out in original model taking into account atmospheric perturbation. [ABSTRACT FROM AUTHOR]

The air of this research is obtaining of nominal control programs in problem of far rendezvous at geostationary orbit with low transversal thrust. The problem of control program designing in linear approximation divided to control in orbital plane and control in lateral direction. Motion in orbital plane is separate to secular and periodic. Using Pontriagins maximum principle, the structure of optimal control program with transversal thrust is determined. Base on optimal control program, the simple analytical control programs is obtained. Numeric simulation of rendezvous transfer with obtained control programs is carried out. [ABSTRACT FROM AUTHOR]

The air launch is a one of way to deliver spacecraft into orbit. This paper investigates of rocket aerodynamic characteristics with influence from an aircraft. The approach is a calculation of aerodynamic characteristics for an isolated rocket and system of rocket and aircraft by means of computational fluid dynamics methods. Based on the results of the simulation, a comparison was made between drag and lift coefficients and lift-to-drag ratios. [ABSTRACT FROM AUTHOR]