Hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint

A hypersonic and attitude control technology, applied in the aerospace field, can solve problems such as not considering the angle of attack constraint

Active Publication Date: 2014-11-19
HARBIN INST OF TECH
View PDF6 Cites 21 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention solves the problem that the aircraft attitude control in the prior art does not consider the angle of attack constraint when designing

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint
  • Hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint
  • Hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0057] Specific implementation mode one: combine figure 1 and figure 2 To illustrate this embodiment, the process of a hypersonic aircraft pitch channel attitude control method considering the angle of attack constraint is as follows:

[0058] Step 1: Establish the mathematical model of the longitudinal attitude control system of the hypersonic vehicle, the specific steps are as follows:

[0059] alpha c is the angle of attack command, the maximum value is α cmax , the minimum value is α cmin ; α is the actual angle of attack, and α is required to be in the interval [α min ,α max ]; when the angle of attack command α c Satisfy α min cmin ≤α cmax max When , define the angle of attack command α c In order to allow the command of the angle of attack; when the initial value of the angle of attack α(0) satisfies α min -α cmin +α c (0)max -α cmax +α c (0), define the initial value of the angle of attack α(0) as the initial value of the allowable angle of attack, where...

specific Embodiment approach 2

[0102] Specific embodiment two: performances such as the stability and convergence rate of the closed-loop system formed by inspection formula (10) and (14) of step 3 described in this embodiment, select control parameter k 1 and k 2 The realization is completed with the help of computer numerical simulation tool Matlab / Simulation.

[0103] Other steps are the same as in the first embodiment.

specific Embodiment

[0104] Step 1: Establish the mathematical model of the longitudinal attitude control system of the hypersonic vehicle, the specific steps are as follows:

[0105] Given angle of attack command α c , to design an appropriate elevator deflection angle command δ z , so that the actual angle of attack α asymptotically tracks the command angle of attack α c , that is, asymptotically converges to zero, while making the actual angle of attack α always in the interval [α min ,α max ] = Change within [-4°, 4°]. Therefore, the value range of the allowable initial value of the angle of attack α(0) is (-4°, 4°). Let the angle of attack command be α c =3°exp(-5t 2 ). Apparently, the angle-of-attack command is an allowable angle-of-attack command. because α c quickly converges to near zero, so it can be considered that: α cmax = 3°, α cmin = 0°. Therefore m=-4°, M=1°. The mathematical model of the hypersonic vehicle longitudinal attitude control system is as follows:

[0106] ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a hypersonic aircraft pitch channel attitude control method in consideration of attack angle constraint, and relates to a attitude control system design method for a hypersonic aircraft pitch channel, so as to solve the problem that attack angle constraint is not considered when aircraft attitude control is designed in the prior art. Appropriate control algorithm is designed according to the given attack angle instruction alpha C, a lifting rudder instruction deltaz is generated to enable the actual attack angle alpha to track asymptotically the attack angle instruction alpha C and to enable the actual attack angle alpha to vary constantly in the range of [alphamin, alphamax]. During the flying process of the aircraft, the attach angle can track asymptotically the attack angle instruction, variation of the attach angle does not exceed the allowable range, and thus a motor can be ensured to work normally and realization of the flying task can be ensured. The method of the invention can be applied to attitude control of the hypersonic aircraft pitch channel.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to a design method for an attitude control system of a pitch channel of a hypersonic vehicle that fully considers the constraints of the angle of attack during design Background technique [0002] Vehicles flying at speeds greater than Mach 5 are called hypersonic vehicles. Due to the strong military and civil application prospects of hypersonic vehicles, countries all over the world are setting off an upsurge of research and development of hypersonic vehicles. Major countries such as the United States, Russia, and the United Kingdom all regard the exploration and development of hypersonic technology as an important goal in the aerospace field to ensure their position on the future world stage. [0003] The hypersonic vehicle adopts an airframe-engine integrated lifting body configuration, coupled with the influence of hypersonic speed and a large range of flight speed changes,...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05B13/04
Inventor 段广仁侯明哲谭峰吴文娟章智凯
Owner HARBIN INST OF TECH
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap