Adaptive Incremental Particle Filtering Method for Mars Atmosphere Entry Section
A technology of particle filter and entry section, which is applied in the field of aerospace navigation, can solve problems such as not suitable for Mars atmosphere entry section, noise statistics error, etc.
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[0060] The present invention relates to the self-adaptive incremental particle filter method of Martian atmosphere entry section, and specific implementation steps are as follows:
[0061] When the spacecraft enters the Martian atmosphere along the flight trajectory, the flight mechanics set its dynamic system parameters and system noise distribution according to the Martian environment. The measurement system is established based on the only measurement method that the Martian atmosphere enters into the actual project. The measurement noise is also approximated by the analysis and estimation of the measurement equipment, and the system error is difficult to determine as an unknown measurement system error when there are few measurement data. The nonlinear kinematic equations and measurement equations corresponding to the dynamical system are as follows:
[0062] equation of motion x k = 10 + 0.5 ...
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