Rocket first-sub-stage integrated flight control system

Abstract

The invention discloses a rocket first-sub-stage integrated flight control system, which comprises a rocket-borne flight control computer module, a communication module, a black box module and a powersupply module, wherein the rocket-borne flight control computer module is used for calculating navigation, guidance laws and control laws, controlling interaction of multi-path serial port end data,and receiving rocket take-off and separation signals sent by a main rocket body at the same time; the communication module is used for communication between the flight control system and a steering engine; the black box module is used for storing the flight condition of a rocket; and the power supply module is used for supplying power to the rocket-borne flight control computer module, the communication module and the black box module. According to the invention, the characteristics of high dynamic, high overload and drastic temperature change of a rocket first-stage recovery and falling areacontrol working environment can be satisfied, and the system has the advantages of low cost, small size and high reliability.

Description

technical field [0001] The invention belongs to the technical field of rocket guidance and control, in particular to a rocket-sub-stage integrated flight control system. Background technique [0002] In order to meet the requirements of the launch vehicle from "how to enter space" to "how to enter space at low cost", the precise navigation, guidance and control technology of the first stage of the rocket has also become a very popular and challenging research field. In order to realize the reliable recovery of the first stage of the rocket in a high-dynamic and high-sonic environment, as well as the high-precision integrated navigation and attitude control of the first stage of the rocket, it is necessary to design a flight control system with high reliability and low cost. [0003] The navigation and control of a high dynamic flying object is of great significance to the flight attitude and flight trajectory of the entire flying object. For the projectile, it can accurately...

AI Technical Summary

Problems solved by technology

[0005] At present, the recovery technology of the first sub-stage of the launch vehicle mostly adopts the recovery technology of the rocket body of the parachute (uncontrolled parachute or controllable parachute). Since the landing speed of the rocket body is determined by the structural quality and the area of ​​the parachute, the volume and mass of the parachute become a constraint for the heavy duty recovery of the parachute. The key factor of the first sub-stage of the rocket has certain technical difficulties; the other is the technology of using the rocket's own power system for vertical take-off and landing recovery, which requires the installation of a landing buffer mechanism, which will lose part of the carrying capacity

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