Solid-liquid power sounding rocket land launching sequential control system

Abstract

The invention discloses a solid-liquid power sounding rocket land launching sequential control system which comprises a main control computer, a ground sequential control system and a rocket-mounted single chip computer control system, wherein the main control computer sends a control command to the ground, sequential control of a rocket-mounted engine igniter is achieved through the ground sequential control system which is further used for conducting the sequential control on a rocket-mounted engine liquid path valve and the rocket-mounted single chip computer control system, and meanwhile opening and closing condition information of the rocket-mounted engine igniter and the liquid path valve is obtained and sent to the main control computer. The sequential control of a rocket-mounted engine pressurized valve is achieved by the rocket-mounted single chip computer control system, and meanwhile the closing and opening condition information of the rocket-mounted engine pressurized valve is obtained and sent to the main control computer through the ground sequential control system. The solid-liquid power sounding rocket land launching sequential control system has the advantages of solving the key problems of matching the solid-liquid power sounding rocket ground sequential control with a rocket-mounted sequential control circuit and meeting millisecond level requirements of launching sequential errors.

Description

technical field [0001] The invention belongs to the field of control systems, in particular to a ground launch timing control system for solid-liquid powered sounding rockets. Background technique [0002] The solid-liquid powered sounding rocket is a new type of aircraft that uses a solid-liquid rocket engine as a power device and has the characteristics of adjustable thrust and repeatable start. The working principle of the engine is that after the igniter is triggered, the liquid valve is opened to release the liquid oxidant. The oxidant contacts and burns with the solid fuel in the combustion chamber, and the engine starts to work. At the same time, the booster valve is opened to adjust the oxidant flow rate and change the combustion rate of the propellant. Realize the variable thrust adjustment of the engine. Among them, the precise timing control of igniter, hydraulic valve and booster valve is the key link of engine work. The precise control of timing is the key tec...

AI Technical Summary

Problems solved by technology

In the document Missile and Space Launch Technology-2004-1 (34) "Manned Space Launch Vehicle Ground Test Launch Control System", although a test launch control system is introduced, its structure is complex, the procedure is cumbersome, the volume is large, and it is not easy to move , can not be controlled remotely, and cannot adapt to the conditions of mobile launch in the field

The portable rocket engine ground test measurement and control system introduced in the invention patent "Portable Rocket Engine Ground Test Measurement and Control System" with the publication number CN102042122A is mainly used to realize the pressure, temperature, flow and thrust during the rocket engine ground test process. The acquisition of test parameters, such as the acquisition of test parameters, but the precise timing control function of the ignition of the engine igniter, the opening and closing of the electromagnetic valve, etc. is not perfect; this portable rocket engine ground test measurement and control system is only suitable for ground tests under laboratory conditions , it is not suitable for the launch of aircraft under the conditions of the launch site, let alone the launch control work of new solid-liquid powered rockets

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