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Universal controller of spaceflight carrier rocket

A launch vehicle and controller technology, applied in the field of aerospace launch vehicle control, can solve the problems of wasting design human resources, increasing test costs, increasing the difficulty of production site state management, etc., and achieve the effect of improving reliability and anti-interference

Active Publication Date: 2017-01-11
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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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

Method used

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  • Universal controller of spaceflight carrier rocket

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[0040] The processor is DSP (TMS320F28335), with a maximum frequency of 150MHz, 512KB built-in FLASH, 68KB built-in RAM, no less than 16 channels of 12-bit ADC, 1 channel of SPI interface, 2 channels of CAN interface, and 16 / 32-bit XINTF interface;

[0041] The CPLD shown is EPM1270T144, which has 1270 LEs and 116 GPIOs;

[0042] The shown CPLD and DSP are connected through the XINTF bus;

[0043] The steering control output module shown is 4-way 12-bit D / A (DAC7714), and the output voltage range is ±10V;

[0044] The controller in the ground CAN isolation drive module shown above adopts SJA1000T chip, which communicates with DSP through 8-bit data (data, address line multiplexing) lines, and the controller and DSP use 3.3V to 5V power supply. Level conversion chip for signal transfer;

[0045] The CAN isolation driver on the arrow shown has an impedance switching function, so that after the first, second and third stages are separated, the CAN node of the corresponding cabi...

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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...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
CPCB64G1/244G05D1/101
Inventor 但春华丁波宋长哲陶金杜鹏谢扬张洪倩陈明欣吴翔郑宇
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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