Gridding launching trajectory planning method

Abstract

The invention provides a gridding launch trajectory planning method, which firstly proposes a thought of constructing a trajectory planning database with dynamic range adaptive capacity in advance according to a gridding method for a preset launch point location, and can preferentially select a launch trajectory for a task planning stage. In the actual task execution process, a launch trajectory is quickly matched and corrected to provide support; the thought of multi-element combined marshalling such as launching point location, launching trajectory and carrier model under multi-constraint conditions such as current task state, satellite constellation configuration, carrier rocket train loading condition, task deployment condition and satellite transit reconnaissance is proposed for the first time; the problem of quick matching of satellites, rockets, resources, environments and the like under the confrontation condition can be systematically solved; through empirical data accumulation, aiming at a launching trajectory evaluation problem, a launching trajectory evaluation index system is relatively completely proposed for the first time, and a support is provided for evaluating a preferred launching scheme and a backup launching plan.

Description

technical field

[0001] The invention belongs to the technical field of solid carrier rockets, and in particular relates to a gridded launch trajectory planning method. Background technique

[0002] Trajectory planning for conventional launch missions is mainly aimed at the flight trajectory design of liquid rockets for launch missions with fixed launch stations and long launch preparation periods. Since the launch tasks undertaken by each launch station have a clear division of labor, that is, the type of launch vehicle supported is fixed, the launch point is determined, and the type of launch orbit is planned in advance; therefore, the trajectory planning of conventional launch tasks only It is necessary to quickly determine the launch station and the launch vehicle model based on the carrying capacity and orbital height. The focus is on re-optimizing the trajectory at a fixed point based on the change in orbital height. There is no such thing as a distance offset from the ...

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