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First stage reentry control system and method of launch vehicle, simulation system and method

A technology for a launch vehicle and a control system, which is applied in the field of a sub-stage reentry control system of a launch vehicle and a simulation system, can solve problems such as hidden safety hazards, difficulty in search and recovery, and easy disassembly, and achieve good aerodynamic characteristics and good control characteristics. The effect of the deceleration characteristics and the high accuracy of the landing zone

Active Publication Date: 2019-06-28
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Moreover, the wreckage of the first sub-stage of the rocket is easy to disintegrate during the actual flight, causing safety hazards and making it more difficult to search and recover

Method used

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  • First stage reentry control system and method of launch vehicle, simulation system and method
  • First stage reentry control system and method of launch vehicle, simulation system and method
  • First stage reentry control system and method of launch vehicle, simulation system and method

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Embodiment 1

[0056] This embodiment describes in detail the re-entry control system of the first sub-stage of the launch vehicle of the present invention. A cabin section is expanded at the head of the first sub-stage of the launch vehicle, and the re-entry control system is installed in the extended cabin section. Its structural diagram is as follows figure 1 As shown, it includes: a grid rudder 15 and a grid rudder control system. The grid rudder control system is used to control the re-entry flight attitude of the grid rudder, and then control the re-entry flight attitude of the first sub-stage of the launch vehicle.

[0057] In the present embodiment, the grid rudder control system includes: navigation system 11, trajectory generation system 12, stability control system 13 and trajectory tracking system 14, navigation system 11 and grid rudder 15, stability control system 13 and trajectory generation system 12 respectively connected, the navigation system 11 is used to obtain the real-t...

Embodiment 2

[0069] This embodiment describes in detail the re-entry controller of the first sub-stage of the launch vehicle of the present invention, which is a re-entry control method realized by the first-sub-stage re-entry control system of the launch vehicle of Embodiment 1, which includes the following steps:

[0070] S11: the grid rudder control system produces the flight parameters of the reentry flight attitude of the control grid rudder;

[0071] S12: The grid rudder generates aerodynamic force, provides stable control force during the re-entry flight according to the flight parameters, and drives the re-entry flight of the first sub-stage of the launch vehicle.

[0072] Wherein, step S11 specifically includes:

[0073] S111: The navigation system measures the real-time flight parameters of the grid rudder, and transmits the real-time flight parameters to the trajectory generation system and the stability control system;

[0074] S112: The trajectory generation system receives t...

Embodiment 3

[0078] This embodiment describes in detail the first sub-stage reentry simulation system of the launch vehicle of the present invention, and its structural schematic diagram is as follows image 3 As shown, it includes: trajectory optimization unit 21, guidance calculation unit 22, aerodynamic simulation data unit 23, control unit 24, re-entry kinematics model unit 25, re-entry kinematics model unit 26 and navigation calculation unit 27, wherein , the trajectory optimization unit 21 is connected with the guidance calculation unit 22, and is used to provide the guidance calculation unit 22 with a reentry trajectory through ballistic optimization; The model unit 25 is connected to provide aerodynamic data for the guidance calculation unit 22, the control system 24 and the reentry kinematics model unit 25; the guidance calculation unit 22 is connected to the control system 24 for solving Calculate the outer loop slow loop rudder control amount, and transmit it to the control syst...

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Abstract

The invention discloses a control system and method for sublevel reentry of a carrier rocket, and a simulation system and method. The control system comprises a grid rudder and a grid rudder control system, wherein the grid rudder control system is used for controlling the reentry flying attitude of the grid rudder, so as to control the reentry flying attitude of the sublevel of the carrier rocket. The control method is realized by the control system. The simulation system comprises a trajectory optimization unit, a guidance resolving unit, a pneumatic simulation data unit, a control unit, a reentry kinematic mechanical model unit, a reentry kinematic model unit and a navigation resolving unit. The simulation method can adopt the simulation system for realizing simulation. According to the control system and method for sublevel reentry of the carrier rocket, and the simulation system and method provided by the invention, the grid rudder is adopted for controlling, so that the stroll radius of a sublevel falling area is greatly reduced and the purpose of correcting the falling area is achieved, the probability of sublevel decomposing is greatly reduced, and the problems of falling area safety and sublevel wreckage searching are solved.

Description

technical field [0001] The invention relates to the technical field of re-entry control technology of a launch vehicle sub-stage, in particular to a launch vehicle-sub-stage re-entry control system and method, and a simulation system and method. Background technique [0002] The launch vehicle generally adopts a multi-stage configuration to complete the flight mission, and one sub-stage will be thrown away after completing the work to reduce the excess structural weight. The first sub-stage of the launch vehicle in active service is separated from the upper stage for uncontrolled flight, and then enters the atmosphere after gliding for a period of time. The landing points are distributed in a wide range, and are generally randomly distributed in an area 50km long and 30km wide on the center line of the navigation area. The central line of the navigation area passes through inhabited areas such as towns, which will cause safety problems. Moreover, the large range of first-le...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 刘冬雪徐大富林剑锋吴佳林盛英华陈雪巍刘玉玺李鑫
Owner SHANGHAI AEROSPACE SYST ENG INST
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