Hypersonic flight test device boosting section control system simulation platform

A simulation platform and hypersonic technology, applied in general control systems, control/regulation systems, instruments, etc., to achieve the effect of improving development efficiency

Inactive Publication Date: 2020-06-16
HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Hypersonic test vehicles and booster rockets have a very complex system structure and diverse system components, which put forward higher technical requirements for the control system simulation platform, and currently there is no special control system simulation for the hypersonic test vehicle booster section In order to improve the development efficiency of the hypersonic vehicle booster control system, shorten the development cycle, and find and correct possible faults at the lowest possible cost, it is necessary to seek a special control system simulation platform to solve the above problems. question

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  • Hypersonic flight test device boosting section control system simulation platform
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  • Hypersonic flight test device boosting section control system simulation platform

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Embodiment 1

[0040] Embodiment 1 of the present invention provides a simulation platform for the control system of the booster section of a hypersonic flight test vehicle. The simulation platform includes a parameter setting subsystem, a trajectory optimization subsystem, a guidance solution calculation subsystem, an attitude control subsystem, and a dynamic Kinematics model subsystem and navigation solution subsystem.

[0041] It should be noted that the simulation model of the hypersonic test vehicle is a combination of the upper stage and the lower stage of the booster rocket.

[0042] The parameter setting subsystem includes a simulation parameter setting module, a dynamics kinematics parameter setting module, a dynamic parameter setting module, a pneumatic setting module and a deviation setting module. The simulation parameter setting module is system initialization setting, the dynamic parameter setting module, aerodynamic setting module and deviation setting module are connected wit...

Embodiment 2

[0055] Embodiment 2 of the present invention provides a kind of simulation method of hypersonic speed vehicle booster section control system, and simulation platform adopts this simulation method in embodiment 1, specifically comprises the following steps:

[0056] S1: The trajectory optimization subsystem provides a flight trajectory for the guidance solution subsystem through trajectory optimization;

[0057] S2: The parameter setting subsystem provides data for the guidance solution subsystem, the control subsystem and the dynamic kinematics model subsystem;

[0058] S3: The guidance calculation subsystem is used to calculate the outer loop slow loop rudder control amount according to the flight trajectory and parameter data, and transmit it to the attitude control system;

[0059] S4: The attitude control system inputs the outer-loop slow-loop rudder control amount of the guidance solution subsystem and the inner-loop fast-loop control amount calculated by itself according...

Embodiment 3

[0064] Embodiment 3 of the present invention provides a kind of assembly motion simulation model, and the simulation model applicable to the simulation platform described in Embodiment 1 is an assembly; the assembly includes an upper level 2 and a lower level 1; and the upper level 2 is a face Said, the following level 1 is axisymmetric.

[0065] The simulation model is as follows:

[0066] (1) Define the relevant coordinate system

[0067] Body coordinate system ox b the y b z b : The origin is the center of mass of the assembly, the x-axis points to the head of the assembly, that is, the test vehicle, the y-axis is perpendicular to the symmetry plane of the test vehicle and the x-axis, and the z-axis is determined according to the right-hand rule.

[0068] launch coordinate system ox L the y L z L : The origin is at the launch point, the x-axis points to the launch direction, the y-axis is perpendicular to the horizontal plane, and the z-axis is determined by the righ...

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Abstract

The invention provides a hypersonic flight test device boosting section control system simulation platform. The simulation platform comprises a parameter setting subsystem, a track optimization subsystem, a guidance resolving subsystem, an attitude control subsystem, a kinetic kinematics model subsystem and a navigation resolving subsystem.

Description

technical field [0001] The invention belongs to the technical field of hypersonic speed, and in particular relates to a simulation platform for a hypersonic speed test vehicle booster section control system. Background technique [0002] It is a technical means commonly used at home and abroad to verify the aerodynamic shape and stability characteristics of the designed hypersonic vehicle by flight test. To meet the test conditions of the test vehicle, the rocket booster is usually used to accelerate it to Mach 4-5 by means of pushing. Due to the separation conditions of the high dynamic pressure area and the limitation of the aerodynamic layout, the fairing cannot be used to improve its aerodynamic characteristics during the boost flight. Therefore, the aerodynamic characteristics of the high lift-to-drag ratio of the test aircraft located at the head will inevitably lead to the pressure center of the longitudinal channel of the entire aircraft moving forward. , which grea...

Claims

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Application Information

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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 罗世彬李晓栋
Owner HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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