Side jet flow control based elastic vibration suppressing method

Abstract

The invention relates to a side jet flow control based elastic vibration suppressing method. The method includes steps of S1, inputting data of environment specialty; S2, according to elastic movement related data provided by the environment specialty, establishing a mathematics model of elastic arrow angular velocity generated by a side jet flow switch action; S3, designing a corresponding filter according to the elastic movement property of the arrow; S4, designing a control threshold matching the control property and controlling the opening frequency of a side jet flow spray pipe reasonably; S5, designing an intelligent energy-saving control strategy so as to enable the self-adaptive adjustment on the threshold of the opening frequency. According to the invention, intelligent self-adaptive control strategy of the switching action of a side jet flow attitude control engine can be realized, interference on attitude control due to high frequency elastic vibration can be suppressed in the maximal level, so that the control efficiency is enhanced substantially and demands for attitude control precision of a solid carrier rocket are met.

Description

technical field [0001] The invention relates to attitude control of aerospace vehicles, in particular to a method for suppressing elastic vibration based on side jet flow control. Background technique [0002] In recent years, the rapid development of solid launch vehicle technology has put forward more demands. In order to simplify the control system of the launch vehicle, reduce the take-off weight, and achieve the goal of low cost and miniaturization, a scheme of attitude control using a set of side-jet attitude control engines for multiple flight segments is adopted. Side jet flow control obtains control torque through high-speed injection mass, which has the advantages of direct generation of control force, fast response speed, and use without environmental restrictions. At present, it has been successfully applied on many domestic launch vehicles. [0003] When the launch vehicle is flying in each flight segment, the mass, center of mass, moment of inertia and aerody...

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Problems solved by technology

However, the amount of interference in each flight segment of the launch vehicle is different. Since multiple flight segments share a set of side-jet attitude control engines, the control capability is fixed. When the side-jet attitude control engines provide the same control torque , it will appear that the control torque is much greater than the disturbance torque in some cases. In this case, if no measures are taken, the nozzle will open and close repeatedly, which not only consumes a lot of propellant, but also easily produces high-frequency elastic vibration Phenomenon, it is difficult to achieve precise control of attitude angle and attitude angle rate

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