A Simulation Research On Measurement And Control Technology Of Earth-Moon Transfer Orbit Of Lunar Probe

Space detection is one of the three developments of space technology. The most important of incinerate space detection is lunar detection. Scientific research and exploration of lunar exchequer and environment is important step to live and work at the strange environment of other planet. Lunar detection is one of the important developments of our space project.To our lunar detection project, measurement and control technology of lunar probe is one of the key techniques. Comparing to spacecraft control near the earth, it is difference of lunar probe. To control station, the measurement distance is farther, the variable rate of measure parameter is smaller. There is only one period of track time to certain deep space station. The first problem of lunar probe is how to get the juncture of Earth-Moon transfer orbit and surrounding lunar orbit. Then we can use different track date of different orbit to get Earth-Moon transfer orbit and surrounding lunar orbit. In real project, using computer to simulate the orbit and control of spacecraft can resolve different problems of control technology in lunar detection earlier. It can also check disposing ability to urgent event of operator, enhance veracity of Real-time control.In this paper, simulation of control on Earth-Moon transfer orbit is studied. It contains theory research, simulation calculation and cartoon simulating. The main works and innovations are as follows:(1). Aiming to characteristic of Earth-Moon transfer orbit characteristic of Earth-Moon transfer orbit, we use taper curve linking method to calculate Earth-Moon transfer orbit, and then get the orbit on base of the six orbit parameters. Because orbit parameters are affected by orbit inhibit conditions, we get parameters of Earth-Moon transfer orbit with program on analytical expressions for designing Earth-Moon transfer orbit expeditiously. This program can get different orbits only needs to input inhibit conditions.(2). Aiming to measurement system and distributing of control station, we get the expressions of the four measurement parameters on base of the calculation of transfer orbit. In order to connect measurement parameters and orbit calculation, we get the transforming matrix from measurement station horizon right angle reference frame to earth's core celestial sphere reference frame. At last, we calculate coverage rate of the...