Initial Orbit Determination of Space Debris Based on the Sparse Space-based Angle Measurement
- Paper number
IAC-11,A6,1,12,x10470
- Author
Dr. Lei Liu, 1)Science and technology on aerospace flight dynamics laboratory, Beijing; 2)Beijing aerospace control center, Beijing;, China
- Coauthor
Mr. Lue Chen, Science and technology on aerospace flight dynamics laboratory, China
- Coauthor
Ms. Mei Wang, Science and technology on aerospace flight dynamics laboratory, China
- Year
2011
- Abstract
\S The number of space debris is growing quickly, which brings more and more collision threats to functional spacecrafts. There are two ways of tracking space debris, i.e. space-based measurement and ground measurement. Comparatively, the former can overcome limits of the latter, such as terrain, time and weather, et al. Currently, the space-based tracking techniques include SBR (space-based radar) and SBV (space-based visible). SBV is already in the test phase. Therefore, this article focuses on initial orbit determination (IOD) of space debris with spare SBV data that greatly depresses requirements on measurement equipments. \S The essence of IOD based on sparse space-based angle measurement (SSBAIOD) is identical to the traditional ground optical IOD, but has its own traits. The phenomena of iteration divergence and self-solution (i.e. the IOD result is the orbit of the space-based platform) occur frequently, when the classical Laplace and Gauss IOD methods together with simple iterative algorithms of the ground IOD are employed. The phenomena, which are almost unavoidable under the situation of the platform orbit above or approximating to the debris orbit, can be resolved only by resort to improvement on IOD model and algorithms. \S Aiming at the problem and utilizing instead of discarding the spare space-based angle measurement, the article works on the SSBAIOD model and algorithms for space debris. First, a new double $\rho$ iteration SSBAIOD model is presented to replace the traditional double r ground IOD model. Second, the adjustable-scale algorithm and genetic algorithms including two kinds of simple genetic algorithms (SGA) and a multi population genetic algorithm (MPGA) are adopted for the model. At last, the new model and algorithms are applied to the SSBAIOD simulations to prove their efficiency and validity. \S According to the simulations, conclusions are drawn as follows: \begin{itemize}\item The double $\rho$ iteration model, which is also suitable to solve common IOD cases and to employ various algorithms, can overcome the drawbacks of the traditional ground methods on the SSBAIOD in the situation of the platform orbit above the debris orbit.\end{itemize} \begin{itemize}\item The adjustable-scale algorithm can solve more than 90\% cases of the platform orbit above or approximating to the debris orbit, and has a favorable convergence speed. \end{itemize} \begin{itemize}\item The genetic algorithm generally gets more satisfying solutions than traditional algorithms. Comparably, SGA is weak on complicated cases of the SSBAIOD, and MPGA is a more powerful global search algorithm to solve the problems of SSBAIOD.\end{itemize}- Abstract document
- Manuscript document
(absent)