Military Reconnaissance Satellite Constellation Study

The reconnaissance satellite constellation is constituted by some reconnaissance satellites, which cooperate with each other in accomplishing the missions of Intelligence, Surveillance and Reconnaissance (ISR). The dissertation considers cooperation and autonomy are important domains to study the reconnaissance satellite constellation, and some key problems in the domains of cooperation and autonomy are studied in the dissertation.High precision orbit propagation is the basis of the study of orbital dynamics, and the application of general engineering simulation platform, such as MATRIXx, MATLAB, will increase the efficiency and reliability of simulation. A simulation system of High precision orbit propagation is constructed in the integrated environment of MATRIXx, and some problems on the applications of MATRIXx in aerodynamics are discussed. Satellite constellation is a major shape for satellites to cooperate. The method to design global coverage satellite constellation is discussed with the help of simulation analysis. The dissertation presents algorithms of global coverage and regional coverage for satellites to observe space, and these algorithms are proved with the help of aggregate. Space-Based Infrared System are conjectured and analyzed based on these algorithms. The shape of o constellation is an efficient way to program the missions of regional coverage of reconnaissance satellite constellation, the methods to design o constellation are discussed in case of Two-Body or J2 influence. The losses of performance of LEO constellation are analyzed with the help of simulation.Tri-satellites time-difference localization constellation is made up of three satellites restricted by some geometry shape. Two methods to position one fixing object are discussed, one makes use of data observed in one single time, the other makes use of data observed in one period of time. The localization of mobile object is accomplished by nonlinear Kalman filter. Based on the formulae of localization errors, the rules are analyzed, which describe the relationship between the localization precision and the constellation factors, such as constellation shape, the height of satellite. The method to design the constellation is presented with the help of these rules.Orbital maneuver is the primary condition for satellite autonomy, and it is the basis of phase keeping, phase maneuver and rendezvous. The dissertation presents a new method for Orbital maneuver based on Zero Effort Miss Steering, and many problems in this method are studied. The problem of control benchmark is solved by the use of HPOP, and the problem of constant thrust control is solved by H control theory and PWPF modulator.