Hypersonic speed maneuvering flight anti-rudder surface saturation resistance robust control method

A technology of maneuvering flight and hypersonic speed, applied in the field of flight control

Active Publication Date: 2017-06-13
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to solve the control surface saturation problem, a new anti-saturation auxiliary control system is proposed and introduced into the HSV maneuvering flight control method
HTDDO tracking approximation works well

Method used

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  • Hypersonic speed maneuvering flight anti-rudder surface saturation resistance robust control method
  • Hypersonic speed maneuvering flight anti-rudder surface saturation resistance robust control method
  • Hypersonic speed maneuvering flight anti-rudder surface saturation resistance robust control method

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Embodiment Construction

[0086] The robust control method for anti-rudder surface saturation of hypersonic maneuvering flight proposed by the present invention will be described in detail below in conjunction with the embodiments and accompanying drawings. The embodiment adopts a Winged-Cone configuration model proposed by NASA Langley Research Center as the research object.

[0087] Establish twelve state equations of HSV (Mooij E.Motion of a vehicle in a planetary atmosphere[J].NASA STI / Recon Technical Report N,1994,96:11743). Its specific form is as follows:

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[0100]The aerodynamic model of the aircraft mainly comes from Keshmiri S, Colgren R, Mirmirani M. Six DoFNonlinear Equations of Motion for a Generic Hypersonic Vehicle [C]. AIAA Atmospheric Flight Mechanics Conference and Exhibit, United States: AIAA, 2007, 1-28.

[0101] The present invention only c...

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Abstract

The invention discloses a hypersonic speed maneuvering flight anti-rudder surface saturation resistance robust control method, belongs to flight control methods in the technical field of aviation and aerospace, and aims to solve the problem of poor control system performance of a HSV (hypersonic vehicle) caused by operating control surface amplitude saturation and composite disturbance in the hypersonic speed maneuvering flight process. The method provides a novel saturation resistance auxiliary design system, the order of the system is as same as that of an attitude control system, and the system is applicable to an SISO (single input single output) system and an MIMO (multiple input multiple output) system. Variables of the auxiliary system is led into a back-stepping method error variables, HSV maneuvering flight control laws are designed by the aid of the back-stepping method ideologies, and the closed loop stability of a system is ensured. The invention provides a disturbance observer based on a mixed tracking differentiator, tracking and approach for composite disturbance are performed by the disturbance observer, and compensation control laws are designed.

Description

[0001] Technical field: [0002] The invention relates to a flight control method in the field of aerospace technology, in particular to a hypersonic maneuvering flight anti-rudder surface saturation robust control method, especially suitable for flight under the condition of control rudder saturation and composite interference during hypersonic maneuvering flight Control Method. [0003] Background technique: [0004] Hypersonic Vehicles (HSV) refer to aircraft with a flight speed above Mach 5, which are mainly active in the airspace 20km to 100km above the ground. Due to the characteristics of large flight envelope, complex flight environment, high maneuverability, and multi-task mode, HSV inevitably has uncertainties caused by internal structure and aerodynamic parameters, as well as interference caused by the external environment. Highly coupled, the controlled object presents strong nonlinear dynamic characteristics. These factors will increase the difficulty of attitude...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 张鹏都延丽孙萍项凯
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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