A study on re-planning orbit of exoatmospheric vehicle

After some exo-atmospheric maneuvering, a long-term flight vehicle will reach at a terminal point on the Earth surface that greatly deviates from the normal final position. In order to attain the special flight mission, the flight orbit must be adjusted to make the final point as close to the required terminal point as possible. This paper deals with the orbit re-planning issue based upon the well-known Lambert guidance scheme. The rotation and the ellipsoid shape of the Earth are taken into account. With the modified scheme and only one orbit adjustment, the vehicle can reach at the new scheduled terminal point within a tolerant error. In the preliminary simulation, the actual state and the dynamic response of the attitude control and divert system are involved.