Noise Suppression Method for Trajectory Planning Measurement

Abstract

A trajectory planning and measuring and noise suppressing method includes the steps of firstly, measuring the geocentric distance rc, the longitude theta c, the latitude phi c, the velocity Vc, the flight path angle gamma c and the course angle psi c at the initial moment of a current guidance period of a lunar explorer to serve as current state variables, and calculating the voyage to fly s0 of the explorer according to the current point and the target point of the lunar explorer; secondly, calculating the state value, from the current point to the target point, of the lunar explorer and the voyage sf(k), from the current point to the target point, of the lunar explorer, if the difference between the sf(k) and the s0 is larger than 25 Km / R0 and k is smaller than 10, executing the third step, if the difference between the sf(k) and the s0 is smaller than or equal to 25 Km / R0, executing the fifth step, and if the difference between the sf(k) and the s0 is larger than 25 Km / R0 and the k is larger than or equal to 10, executing the fifth step according to the equation sigma0(k) is equal to sigma0(1); thirdly, conducting differentiation on the sf(k) and the sigma0(k) obtained in the second step to obtain the results (please see the expressions in the specification); fourthly, obtaining a guidance heeling angle instruction iterative new value signal0(k+1) through the iterative method, executing the next iterative step, namely, automatically adding 1 to the k, enabling the obtained new value sigma0(k+1) to serve as signal0(k) in the next iterative step, and executing the second step again in a circulated mode; fifthly, entering the next guidance period when the guidance instruction of the current guidance period is signal0(k), and executing the first step till guidance is ended.

Description

technical field [0001] The invention belongs to the field of aerospace and relates to a new method for suppressing noise in trajectory planning measurement. Background technique [0002] The prediction and correction algorithm can be applied to the trajectory planning problem and closed-loop guidance problem of the lunar exploration and return vehicle. The focus of this algorithm is to find the roll angle amplitude command σ that should be used to fly from the current flight point to the end point 0 , the specific amplitude is determined by the longitudinal distance requirements from the aircraft to the landing point. It needs to be obtained by solving a nonlinear, univariate root-finding problem. looking for σ 0 The problem is reduced to solving the following equation [0003] s f (cosσ 0 )-s 0 =0 [0004] root problem, where s f Indicates the range of the aircraft, s 0 Indicates the flight to be flown. Generally, the secant method is used to iteratively solve th...

AI Technical Summary

Problems solved by technology

[0010] The technical solution of the present invention is to provide a new method for suppressing measurement noise in trajectory planning, which can better solve the problem of suppressing measurement noise in trajectory planning compared with the prior art

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