A Precise Control Method for the Launching Orbit of a Launch Vehicle under Fire

Abstract

The present application belongs to the technical field of launch vehicle guidance. Specifically, a precise control method for the launch track of a launch vehicle running into fire is provided. The method includes: when the flight segment of the launch vehicle is the final stage entry segment or the terminal velocity correction segment, determining the shutdown amount of the launch vehicle in the current control period according to the first shutdown control parameter of the launch vehicle; The amount of shutdown during the cycle determines whether shutdown control of the launch vehicle is required. Based on the technical solution provided by the present application, when the operating orbit of the launch vehicle transitions from a closed orbit to a non-closed orbit, the high-precision and reliable shutdown requirements of its orbital energy state are met.

Description

technical field [0001] The present application relates to the technical field of launch vehicle guidance, and in particular, to a precise control method of a launch vehicle running through fire. 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, the orb...

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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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