System and method for measuring attitude angle rate signal of carrier rocket

Abstract

The invention discloses a system and a method for measuring an attitude angle rate signal of a carrier rocket. To each channel in pitching channel, jaw channel and roll channel for the carrier rocket, the angle rate signal is obtained through an attitude angle signal of a strapdown inertial measurement unit and by substituting a rate gyroscope; the attitude angle signal is subjected to quaternion algorithm; the angle rate signal is subjected to filtering; the quaternion algorithm result and angle rate signal filtering result are subjected to corrective network difference equation calculation to obtain swinging angle control instruction. Under the conditions of not increasing carrier rocket rate gyroscope hardware configuration and software algorithm complexity, gyroscope signal in the strapdown inertial measurement unit is fully used to join in the control of the attitude angle rate channel, the redundancy design problem of the carrier rocket attitude angle rate signal measurement is solved, and the beneficial effect of improving the flying reliability of the carrier rocket is achieved.

Description

technical field [0001] The invention relates to the technical field of launch vehicle redundant control systems, in particular to a measurement system and method for a launch vehicle attitude angular rate signal. Background technique [0002] figure 1 It is a block diagram of the attitude control system of the pitch channel of the existing launch vehicle. like figure 1 The existing attitude control system shown includes an inertial measurement system with two sets of strapdown inertial sets and a rate gyroscope, an arrow machine, and a servo mechanism. During the rocket's flight, the inertial measurement system measures the rocket's attitude angle and attitude angular velocity signal in real time, wherein the attitude angle signal is measured by the strapdown inertial set, and the attitude angular velocity signal is measured by the rate gyro. The arrow machine samples the measurement information, and obtains the corresponding control command through the comprehensive oper...

AI Technical Summary

Problems solved by technology

Since the accuracy of attitude angle rate measurement is directly related to the success or failure of the attitude control of the launch vehicle, and then affects the success or failure of the launch vehicle flight, the redundancy of the rate gyro will be limited by the installation location, carrying capacity, etc.

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