Designing method for multimode control system of aircraft

A technology for control system and system design, applied in instrumentation, computing, special data processing applications, etc., can solve problems such as inability to define system functions, physics, software architecture, not supporting system requirement capture and system analysis, etc., to reduce research and development. Cycle time and design and production costs, the effect of improving design efficiency and strengthening verification efforts

Inactive Publication Date: 2015-04-29
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Stateflow is an event-driven system with a finite state machine. When a specific event occurs, it transfers from the current state to the next state, but its defect i

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  • Designing method for multimode control system of aircraft
  • Designing method for multimode control system of aircraft
  • Designing method for multimode control system of aircraft

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Embodiment Construction

[0033] The present invention will be further described below in conjunction with the accompanying drawings.

[0034] The design principle of the present invention is: the design method of the semi-physical platform in the past is abandoned, and the system design is carried out by completely adopting the virtual environment. Use the SysML requirement diagram and use case diagram in Rhapsody software to describe the requirements of the multi-mode switching control system of the aircraft, and track and link the described system requirements with user requirements; according to the system requirements, use the SysML sequence diagram and state diagram Carry out the task scheduling planning of the aircraft control system, the design of multi-modes and the design of the switching mechanism between modes. Use SYSML to analyze and develop the various components of the flight control system and their coupling relationships, and design each part in the Simulink and Rhapsody software envi...

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Abstract

The invention discloses a designing method for a multimode control system of an aircraft. The designing method comprises demand analysis, system analysis and system designing stages, and is characterized in that the demand analysis, and management and confirmation data are from user demand (stakeholder demand) knowledge base; output data is a demand confirmed by an aircraft system and serves as one of system analysis inputs of the aircraft system; the input data of mode switching design at the system design stage is from a control mode conforming with tactics design and tactics type needs; output data are a mode switching controller conforming with the tactics need; co-simulation and verification at the system design stage refers to that co-simulation is performed on isomerism models of an aircraft control system in the fields of machines, hydraulic and the like in a built simulation environment. According to the method, the functional, physical and software system structure of the system can be defined, and demand capturing of the system and system analysis can also be supported.

Description

technical field [0001] The invention belongs to the technical field of aircraft control system design, and relates to a design method for an aircraft multi-mode control system. Background technique [0002] In recent years, with the rapid development of aviation technology, the missions undertaken by aircraft have gradually increased, and the flight control system is developing towards the direction of aviation integrated system, which integrates flight control, fire control, target detection, navigation system, display system, etc. Coupled into an integrated flight management system, so that these systems can work together better to complete the flight mission. Correspondingly, the scale of the flight control system is getting larger and larger, and the number of control modes increases, which makes the design of the flight control system more and more complicated. [0003] The flight process of the aircraft is a switching process of multi-mode flight control laws, which i...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 曹云峰庄丽葵丁萌袁小敏刘同磊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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