A method for real-time measurement of rocket sled track gravity

Abstract

A rocket sled orbit gravity real-time measuring method comprises the steps that (1) in a current navigation period, according to the relationship between latitude information and height information in a rocket sled orbit, actual height information hB of a rocket sled body in the current navigation period is obtained, and accordingly a height error signal deltah is obtained, wherein deltah=h-hB; (2) integration control is conducted on the height error signal deltah to obtain a control component x and PID control is conducted on the height error signal deltah to obtain a height controlled variable uh; (3) low-pass filtering is conducted on the component x to obtain a gravity deflection value x', and then the gravity deflection value x' and an earth gravity model value gh are summed to obtain a real-time measurement gravity value g0; (4) the uh and the g0 are fed back to an inertia navigation system, and the inertia navigation system conducts resolving to obtain the corrected height h of the rocket sled body; (5) a next navigation periods starts, the inertia navigation system resolves the latitude information of the rocket sled body, the actual hB in the current navigation period is obtained according to the relationship between the latitude information and the height information in the rocket sled orbit and a height error signal deltah is obtained again; the step (2) is switched to and the following steps are executed circularly.

Description

technical field [0001] The invention relates to a design method of an integrated navigation system, in particular to a method for real-time measurement of rocket sled track gravity, which can be used in occasions with high-precision navigation accuracy, such as aerospace, surveying and mapping and other fields. Background technique [0002] In inertial navigation systems, the characteristic equation of the altitude channel has a positive root In the error propagation of the height channel with A proportional component that grows exponentially with time. Obviously, if there is an initial height error Δh in the skyward channel 0 , the initial celestial velocity error, the celestial accelerometer scale factor error and the constant value error, the error of the height channel is dispersed with time. To solve this problem, it is necessary to introduce external information into the height channel for damping. Commonly used external altitude information includes data provide...

AI Technical Summary

Problems solved by technology

[0003] In addition, the currently used gravity measurement method is based on the geodetic system for fixed-point measurement, the measurement time is long, the number of measurement points is large, and continuous measurement is not possible

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