Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane

In order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation system (CNS)/global positioning system (GPS) integrated navigation system of an aerospace plane. The complementary filters are designed to achieve the estimations of attitude, velocity, and position in the SINS/CNS/GPS integrated navigation system, respectively. The simulation results show that the proposed information fusion method can effectively realize SINS/CNS/GPS information fusion. Compared with FKF, the method based on complementary filter (CF) has the advantages of simplicity, small calculation, good real-time performance, good stability, no need for initial alignment, fast convergence, etc. Furthermore, the computational efficiency of CF is increased by 94.81%. Finally, the superiority of the proposed CF-based method is verified by both the semi-physical simulation and real-time system experiment.

Performance and Technological Feasibility of Aerospace Plane Horizontal Launch and Landing with Ekranoplane Assistance

Numerous attempts to reduce the cost of launching a satellite into low Earth orbit (LEO) were undertaken in many countries and characterize the current trend to make space projects economically viable and less costly. This is necessary for the progress of the development of our earthly civilization, its evolution according to the plans of the outstanding Russian thinker, the founder of cosmonautics Konstantin E. Tsiolkovsky. Mastering of the Moon and Mars are the necessary steps in the cosmic evolution of earthlings. Unfortunately, this process has not led presently to a sharp decrease in the specific launch cost. The concepts of such task solving are considered in this paper.

Investigation of wing structure layout of aerospace plane based on the finite element method

The aerospace plane is an innovative kind of reusable aircraft, which is able to reach the low earth orbit flying like the conventional plane. Two kinds of aerospace plane wing structures are designed and parameterized for the delta wing with a strake, one of which is an equal percentage multi-web structure, and the other is a parallel multi-web structure. The two types of structure layouts were analyzed in the subsonic, transonic, supersonic, and hypersonic conditions using the finite element method. Contrasting the strength and stiffness characteristics, and estimating the structure weight, it demonstrated that the parallel multi-web wing had better performance than the equal percentage multi-web wing in terms of mechanical characteristic and weight. Then, based on the parameterized parallel multi-web wing, the thicknesses of webs, skins, and ribs were optimized to reduce the structure weight.