A Precise Guidance Method Based on Virtual Proportional Guidance for the Sub-stage Return Stage of Launch Vehicle

Abstract

The invention relates to a virtual proportion guided precise guidance method for a sublevel return section of a carrier rocket and belongs to the technical field of guidance and control. The method comprises the following steps: acquiring the position and the velocity vector of a sublevel under an inertial system through socket-carried GPS / INS navigation measuration; calculating components of a virtual inertial view angular velocity in a ground system by combining an expected target droppoint position and velocity information of a task; acquiring the components of the virtual inertial view angular velocity in a trajectory system through a coordinate conversion matrix from the ground system to the trajectory system; and acquiring a virtual proportion guided overload command of gravity compensation and inputting the command into a grid fin control system to achieve control. The method has the characteristic of improving the guidance precisions of sublevel drop regions and sublevel reusereturn effectively.

Description

technical field [0001] The invention relates to a precise guidance method for the sub-stage return section of a launch vehicle based on virtual proportional guidance, and belongs to the technical field of guidance and control. Background technique [0002] Currently active launch vehicles are all disposable. The cost of rocket development, production, and launch has remained high for a long time. The cost of transporting 1kg of material into space is about 10,000-20,000 US dollars, which greatly affects the scale and benefits of human development of space. . As the currently relatively cheap Falcon-9 rocket, the total cost is about more than 50 million U.S. dollars, and the cost of its propellant is only 200,000 U.S. dollars. Therefore, if the rocket sub-stage can be recovered non-destructively and reused after simple repairs, the launch cost can be greatly reduced. The first stage of the launch vehicle in active service will no longer be controlled after separation, and w...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the sub-stage of the existing launch vehicle has a too large dispersal radius in the landing area and it is difficult to realize the non-destructive recovery of repeated use, and provides a sub-stage of the launch vehicle based on virtual proportional guidance with the grid rudder as the actuator Returning to the precise guidance method, the technical solution adopted is as follows:

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