J2 Perturbation Space Rendezvous Strategy Based On Lambert Problem

With the development of science and technology and social economy, space technology is becoming more and more significant in the social and economic value. With the use of new space transportation systems and the development of space equipment assembly technology, human beings will build a variety of large-scale space systems in space. Access to information, materials and energy from space is the long-term goal of the development of the spacecraft. The tasks of communication or detection, such as scientific exploration satellites and communication satellites, are also closely related to space technology.When the spacecraft is flying in space, it is always under the action of all kinds of perturbation force in the space environment, which causes the movement of the spacecraft to deviate from the orbit of the two body problem. The main perturbation is the additional gravitational force produced by the earth’s non spherical shape and mass, which causes the movement of the celestial bodies to deviate from the orbit of the two body problem. How to find an effective algorithm to compensate for the perturbation, to ensure the spacecraft to reach the intersection point or intercept point fast and accurately, is the focus of this paper.In this paper, we first introduce the research progress and some classical algorithms about orbit transfer. Based on the two body dynamics model of the spacecraft, the perturbation of the spacecraft in orbit is discussed, and the two body model and the J2 perturbation model are established for the J2 perturbation. The Lambert theorem is studied, and the relations between the relevant equations and the variables are studied.Secondly, the definition of Lambert is introduced, and the basic properties of Lambert are discussed, including the transfer orbit type and the number of transfer cycles. At the same time, the time transfer equation is also an important factor to solve the Lambert problem. The relationship among several transfer orbit parameters is also introduced. These properties and features of the Lambert problem are the basis for the design of the exact algorithms.At last, the compensation of the perturbation is introduced. In the perturbation of the continuous action, the transfer orbit will often deviate from the target track. In this paper, the specific reasons and models of perturbation are expounded, and the state transition matrix is derived. And through the software and hardware simulation, the effect of the guidance method is verified.