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Output adjusting method of switching networked flight control system based on alternating event triggering

A technology of event triggering and output regulation, applied in special data processing applications, instruments, electrical digital data processing, etc.

Active Publication Date: 2019-10-01
DALIAN MARITIME UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] According to the above-mentioned technical problems that the continuous event trigger mechanism and periodic sampling mechanism in the existing event trigger technology produce too much unnecessary data transmission and easy omission of effective information, resulting in network delay and data packet loss, a method based on Output regulation method of switching networked flight control system triggered by alternate events

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  • Output adjusting method of switching networked flight control system based on alternating event triggering
  • Output adjusting method of switching networked flight control system based on alternating event triggering
  • Output adjusting method of switching networked flight control system based on alternating event triggering

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Embodiment 1

[0134] In this embodiment, take the F-18 aircraft developed by McDonnell-Douglas as the research object. F-18 is a carrier-based jet propulsion multi-purpose combat aircraft. Performance is the mainstream aircraft of the U.S. Navy. During the entire flight process, the initial stage of the longitudinal movement of the aircraft is mainly short-term movement. Due to its short period and rapid change, the pilot does not have enough time to take corrective measures. Therefore, the vertical short period Movement has a great influence on flight safety and shooting accuracy, especially in the study of F-18 aircraft; the nonlinear dynamic model of F-18 aircraft is as follows

[0135]

[0136] Among them, α and q represent the angle of attack and pitch rate, m represents the mass of the aircraft, and Indicates the aircraft dynamic pressure along the OX axis component and the average geometric chord, S indicates the wing area, U 1 and θ 1 represent the aircraft velocity along th...

Embodiment 2

[0148] By designing an alternate event-triggered mechanism and based on the control input δ E and δ PTV Based on the controller of the event-triggered mechanism, the output regulation problem of the networked flight control system is transformed into the output regulation problem of the networked switching system;

[0149] The construction of the alternate event triggering mechanism is specifically:

[0150] S21. In order to study the output adjustment problem of the flight control system based on the network switching control based on the event trigger mechanism, the following assumptions are given:

[0151] Assumption 1. Under the switching signal σ(t), the switching sequence of the flight control system based on networked switching control is expressed as where t k is the switching time, at this time the system mode changes from switch to σ(t k )=i≠j, i,j∈M;

[0152] Assumption 2. The event-triggered transmission sequence satisfying the event-triggered communication...

Embodiment 3

[0167] The error feedback controller based on the alternate event trigger control is specifically:

[0168]

[0169] Among them, H σ(t) and E σ(t) represents a constant matrix of appropriate dimensionality, represents the controller gain to be designed, ξ(t) represents the internal state of the controller, Indicates the switching signal of the controller, d 0 = 0, d k Indicates the controller u i (mode is i) lagging behind the delay of the corresponding subsystem i, that is 0≤d k Mi , d Mi Indicates the controller u i maximum lag time.

[0170] Such as image 3 As shown, since the alternate event trigger mechanism and the asynchronous switching signal cooperate with each other, the specific form of the error feedback controller is discussed in the following four cases:

[0171] Case 1, when , according to the alternate event trigger mechanism (2), the sensor is in the waiting phase during this time period; if , the sensor waiting time is h; if When , t...

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Abstract

The invention provides an output adjusting method of a switching networked flight control system based on alternating event triggering. An alternating event trigger mechanism switched between periodicsampling and continuous event trigger mechanisms is constructed, trigger information and modal information are transmitted to a controller, missing of effective information is avoided by continuouslydetecting trigger conditions, and data transmission and updating are reduced by introducing a sampling period. A flight control system is described as a networked switching system; asynchronous switching control based on an event trigger mechanism is designed under the condition that network induced time delay and packet loss exist. The flight control system accords with model dynamic rapid change characteristics in the flight control system and actual flight working conditions of data transmission and processing between internal components based on a real-time network, reduces data calculation load of the flight control system, saves limited data transmission bandwidth, and improves overall performance and precision requirements. According to the technical scheme, only the output error information needs to be used, state information of the sensor and the aircraft is not depended, and engineering implementation is easy.

Description

technical field [0001] The present invention relates to the technical field of network control, in particular to an output regulation method for switching networked flight control systems triggered by alternate events. Background technique [0002] As the tasks of modern aircraft become more and more complex, the amount of data transmission in the closed-loop system consisting of sensors, controllers and actuators inevitably increases. The flight control system realizes data sharing and data transmission between internal components based on a real-time network, so that the aircraft is modeled as a networked flight control system. In recent years, the theoretical research results of switching systems have emerged continuously, and its characteristics of being easy to describe fast-changing models have greatly promoted the application of switching technology in flight control systems. Therefore, using the dynamic model information of each operating point within the full envel...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/18Y02P90/02
Inventor 李莉莉邹存名宋林阳葛新金翠丽李业成
Owner DALIAN MARITIME UNIVERSITY
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