Accurate control method of launch vehicle fire-striving launching orbit

Abstract

The invention belongs to the technical field of carrier rocket guidance. The invention particularly provides an accurate control method for a launch vehicle fire-strike launching orbit. The method comprises the following steps: when a flight section of the carrier rocket is a final-stage injection section or a final speed correction section, determining a shutdown amount of the carrier rocket in a current control period according to a first shutdown control parameter of the carrier rocket; and determining whether shutdown control needs to be performed on the carrier rocket according to the shutdown amount of the carrier rocket in the current control period. Based on the technical scheme provided by the invention, when the operation orbit of the carrier rocket is transited to the non-closed orbit from the closed orbit, the high-precision and reliable shutdown requirement of the orbit energy state is met.

Description

technical field [0001] The present application relates to the technical field of launch vehicle guidance, and in particular to a method for precise control of a launch vehicle's fire-running trajectory. Background technique [0002] In the previous launch missions of the launch vehicle, the target orbit of the launch vehicle was an approximately circular or elliptical closed orbit with the earth as the gravitational center. Generally, the semi-major axis of the orbit was used as the control parameter for judging the shutdown, which satisfies the requirement of the energy of entering the orbit. precision requirements. [0003] But in Mars exploration missions, see figure 1 , the launch vehicle needs to send the payload into a non-closed geocentric hyperbolic orbit that is separated from the earth's gravitational field. At this time, the semi-major axis of the orbit does not have an intuitive physical meaning to describe the orbit, and during the flight of the launch vehicle,...

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Problems solved by technology

[0003] But in Mars exploration missions, see figure 1 , the launch vehicle needs to send the payload into the non-closed geocentric hyperbolic orbit away from the gravitational field of the earth. At this time, the semi-major axis of the orbit has no intuitive physical meaning to describe the orbit, and during the flight of the launch vehicle, the orbit undergoes a change from closed to In the non-closed transition process, the semi-major axis no longer changes monotonously and continuously with time (ie figure 1 The trajectory after 2000s in the middle), its magnitude and polarity will change suddenly. At this time, using the semi-major axis of the orbit as the control parameter for judging the shutdown cannot adapt to the traditional shutdown discrimination mechanism of the launch vehicle

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