Simulation test system and test method for rocket sub-stage recovery comprehensive controller

Abstract

The invention relates to a simulation test system and test method for a rocket sub-stage recovery comprehensive controller. The system comprises a dynamics simulation machine, a servo control system,a steering engine loading system, a three-axis turntable, an optical fiber inertial measurement unit and a GNSS simulator, wherein the dynamics simulation machine is used for rocket body attitude calculation; the servo control system is used for steering engine action control and actual rudder deflection angle acquisition; the steering engine loading system is used for outputting damping torque; the three-axis turntable is used for receiving attitude angle information of a transmitting coordinate system of the dynamics simulation machine and driving the turntable to rotate; the optical fiber inertial measurement unit measures own inertial information; and the GNSS simulator receives the position information of the dynamics simulation machine and is used for simulating satellite navigationconstellation information. By means of the system, simulation and algorithm verification of the autonomous navigation and attitude control process of the return type carrier rocket can be improved.

Description

Technical field [0001] The invention relates to the field of simulation technology, in particular to a return-type rocket integrated controller simulation test technology and algorithm verification. Background technique [0002] The rocket sub-level landing and recovery integrated controller (abbreviated as the integrated controller) is the core control component of the rocket return control. It collects the rocket sub-level separation signal, optical fiber inertial group signal, GNSS navigation receiver signal, and outputs the grid according to the guidance method and control rate The swing angle signal of the lattice wing steering engine plays a decisive role in the accuracy of the rocket's return to the sub-level position, the guidance algorithm, and the attitude stability control. Therefore, the design verification of its own algorithm is essential. [0003] At present, the test of the sub-level landing recovery controller can be divided into hardware function test and softwar...

AI Technical Summary

Problems solved by technology

Due to the highly dynamic characteristics of the landing of the rocket sub-stage, the above-mentioned software model simulation test cannot assess the complete process and control information of the rocket sub-stage return process, and the grid wing deflection angle feedback cannot be applied to stability control and cannot cover the constraints of the landing recovery process , resulting in the rocket sub-stage landing and recovery control algorithm not being fully verified

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