Universal controller of spaceflight carrier rocket

Abstract

The invention discloses an universal controller of a spaceflight carrier rocket, comprising a control plate, a time sequence plate and an attitude control plate, wherein the time sequence plate comprises M paths of ignition units; the attitude control plate comprises N paths of attitude control drive modules, N paths of attitude control recovery modules, pressure collection modules and remote -measuring power distribution and interruption modules; the control plate comprises a processor DSP (Digital Signal Processor), a programmable logic controller CPLD (Complex Programmable Logic Device), an isolated power supply, an analogue switch, an isolation amplifier, M paths of time sequence recovery modules, M paths of ignition recovery modules, P paths of indication input modules, M paths of time sequence drive modules, a rudder control output module, a rocket-borne CAN isolation drive module, and a ground CAN isolation drive module. The controller is characterized in that controllers in four cabins are combined into one universal controller and has the advantages of modular design, good universality and strong compatibility.

Description

technical field [0001] The invention relates to the field of space launch vehicle control, more specifically, to a general controller of space launch vehicle. Background technique [0002] A certain solid launch vehicle is a type of launch vehicle equipment mainly for civil and commercial spaceflight, as well as for military spaceflight. In order to reduce the length of the cable network on the arrow, the general controller adopts the principle of distributed control, and a general controller is placed in the tail section, the rear section of the interstage II, the front section of the interstage II, and the propulsion control cabin. The section mainly completes grid rudder control and primary ignition, tail section battery activation, primary separation I timing control, voltage quantity and indicator signal measurement, etc.; , secondary ignition, secondary separation, secondary unlocking I, secondary unlocking II, safety control battery activation, main propulsion attitu...

AI Technical Summary

Problems solved by technology

The functions of the four-chamber control units of the solid launch vehicle are similar. If the four control units are designed separately, it will greatly waste design human resources, increase test costs, and increase the waste of single-unit spare parts (according to aerospace quality requirements, all newly developed units need Do the corresponding example test), increase the difficulty of production site status management

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