Research On The Location And Tracking Of Near Space Aircraft And The Guidance Of Interceptor

Near space vehicle (NSV), due to its superior flight speed and strong airmobility, enjoys a huge development potential using as offensive weapons. Therefore, the study on near space defense and the realization of effective NSV interception has great practical and strategic significances to the national security, yet there’re still a large number of difficulties to be solved for realizing the effective NSV interception, i.e., early-warning of near space target; effective detection of near space target; effective tracking filter to near space target with airmobility; mid-course guidance control of anti-missile interceptor when the target is approaching the NSV; interceptor pneumatic problems and pulse combination control in near space, etc. This paper, by taking the interception of boost-glide NSV as the background, focuses on the way to make effective detective and tracking filter to the target aircraft, as well as to make the initial and mid-course guidance to the interceptor in this complex system, including the following parts:Firstly, considering the specific characteristics of boost-glide NSV, the space-based early warning satellite system is used in this paper to detect the target aircraft. The early warning satellite observation model is also established, along with the proposition of detection of target aircraft with multiple early warning satellites, while the passive location of space-based early warning satellite system is studied in detail. In this paper, several passive location algorithms are also analyzed based on the different detection conditions of early warning satellite system, including pure geometric method and total least square. The way to realize the passive location on target as accurate as possible using early warning satellite system with the presence of measurement error is studied, along with the performance comparison of several methods in terms of positioning speed and accuracy.Secondly, the way to make tracking filter to the NSV with airmobility based on the information provided by the passive location. The filter tracking algorithm of target aircraft is analyzed in this paper on the basis of the specific characteristics of NSV and basic thought of Interacting Multiple Model (IMM); by combining with the public data, the movement law of aircraft and the possible motion pattern of NSV are also analyzed, while the motion model set of target aircraft is properly selected; adaptive improvement to the target model set is also made. The target is made for trajectory prediction by using the numerical integration algorithm and considering the multiple flight constraints of target aircraft based on the information provided by the tracking filter.Thirdly, the design of interceptor flight program is studied on the basis of trajectory prediction. Again, in this paper, the dynamic model of the interceptor is established, the basic firing data of interceptor is properly selected, and the iterative computation is made for the trajectory data of interceptor using iterative least squares algorithm, while the firing time of interceptor is inversely calculated via the trajectory integration time. The properties of basic firing data of interceptor are also analyzed to verify the iterative algorithm convergence by selecting the iterative initial value. Furthermore, the design of interceptor firing program required by the anti-missile interception of NSV target is solved based on the calculation of interceptor firing program on the specific simulated scene.Fourthly, the way to guide during the mid-course of flight after the interception’s completion of preset program flight is studied. The model is properly simplified by using the basic thought of predictive guidance based on zero effort miss (ZEM) and the specific characteristics of the intercepted NSV, while the ZEM’s calculation method is also analyzed, along with the obtaining of ZEM analytical solution with higher accuracy. And then, on the basis of such analytical solution and based on the simplified linear model and linear quadratic optimal guidance theory, the mid-course guidance command analytical expression of interceptor is solved. The real-time guidance of mid-course trajectory of interceptor during the NSV interception is also worked out.Finally, it comes to the simulation of comprehensive system of all studied contents in this paper. For this, a set of proper constellation configuration program of space-based early warning satellite system and the optimized trajectory for boost-glide NSV are designed in this paper. Then, the full interception process of NSV is comprehensively simulated based on such program and optimized target trajectory, to evaluate the feasibility of overall plan proposed in this paper.