A Design Method for Multi-modal Control System of Aircraft

A control system and system design technology, applied in the direction of instruments, calculations, special data processing applications, etc., can solve problems that do not support system requirements capture and system analysis, cannot define system functions, physics, software architecture, etc., to reduce research and development Cycle and design and production costs, guaranteed design indicators, and the effect of improving design efficiency

Inactive Publication Date: 2017-12-08
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 is that it cannot define the function, physics, and software architecture of the system. , and does not support requirements capture and system analysis for the system

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  • A Design Method for Multi-modal Control System of Aircraft
  • A Design Method for Multi-modal Control System of Aircraft
  • A Design Method for Multi-modal Control System of Aircraft

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Embodiment Construction

[0034] The present invention will be further described below in conjunction with the accompanying drawings.

[0035] 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 design method for an aircraft multi-mode control system, including three stages of requirement analysis, system analysis and system design. The input data comes from the user requirements (stakeholder requirements) knowledge base; the output data is the requirements confirmed by the aircraft system, and is used as one of the system analysis inputs of the aircraft system; the input data of the mode switching design in the system design stage comes from the The control mode required by tactical design and tactical types; its output data is the control mode switching controller that meets the tactical needs; the co-simulation and verification in the system design stage refers to: the mechanical, hydraulic, etc. involved in the aircraft control system The heterogeneous models in the domain are co-simulated in the built simulation environment. This method can define the function, physics and software architecture of the system, and can also support the requirement capture and system analysis of the system.

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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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