Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion

Abstract

In a low delay ignition confirmation system and confirmation method applied to rocket ground information infusion, a comprehensive detection and control apparatus of a ground test launch control system receives an initial ignition signal sent by a central display and control station; after ladder diagram and logical calculation and signal conditioning, a timing system zero point signal is output; a flight control computer determines whether each one-chip microcomputers on the rocket work normally according to time synchronization after receiving the timing system zero point signal; a flight control procedure is started upon normal work and a determining result is fed back to a central computer; the flight control procedure is stopped upon abnormal work and a determining result is fed back to the central computer and ground post processing is expected; the central computer receives the rocket results; for the normal work signal, an intermediate ignition signal is output to the comprehensive detection and control apparatus; a final ignition signal is output by the comprehensive detection and control apparatus after receiving the intermediate ignition signal; and an initiating explosive device is detonated by a second launch control conditioning plate, so the rocket and the ground are reliably separated.

Description

technical field [0001] The invention relates to a low-delay ignition confirmation system and method for rocket-ground information fusion, and belongs to the technical field of aircraft launch control. Background technique [0002] The ignition signal is a key signal in launch control technology. It is used to detonate the ignition pyrotechnics to realize the separation of the rocket and the ground. It is also used as the time zero point of the flight control computer on the rocket to enter the flight control calculation program. [0003] Such as figure 1 As shown, in the traditional control scheme, after the integrated measurement and control device receives the "initial ignition signal" from the central display console, it performs logic operations and signal conditioning, and simultaneously outputs the "final ignition signal" and "time system zero signal" to drive the ignition respectively. pyrotechnics and launch flight control solver. The following problems exist in th...

AI Technical Summary

Problems solved by technology

The following problems exist in the traditional design scheme: if the state of the equipment or software on the arrow is abnormal while the ignition propellant is driven, and the flight control program is not entered normally, and at the same time the ignition propellant has detonated and the rocket body takes off, the launch mission will inevitably fail

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