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Optimization method of communication network topology for distributed control system of turbo-based combined cycle engine

A distributed control, turbine-based combination technology, applied in transmission systems, bus networks, data exchange networks, etc., can solve the problems of complex surface conditions of aero-engine casings, affecting the topology structure of communication network control systems, and reduce system complexity. Sex, the effect of reducing length

Active Publication Date: 2019-08-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

In addition, the surface of the aero-engine casing is complicated, and there are installation areas for large components such as engine accessories or areas with high temperature. The communication bus in these areas should avoid detours, which will affect the connection path of the communication bus between control nodes. The setting forms certain constraints and affects the topology structure of the communication network control system

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  • Optimization method of communication network topology for distributed control system of turbo-based combined cycle engine
  • Optimization method of communication network topology for distributed control system of turbo-based combined cycle engine
  • Optimization method of communication network topology for distributed control system of turbo-based combined cycle engine

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[0064] The present invention will be further described below in conjunction with drawings and embodiments.

[0065] The present invention can be better understood from the following examples. However, those skilled in the art will readily understand that the specific material ratios, process conditions and results described in the examples are only used to illustrate the present invention, and should not and will not limit the present invention described in detail in the claims .

[0066] The TBCC engine is a propulsion device that organically combines a turbine engine with a sub-combustion / scramjet engine to realize a variable cycle working process, so that the aircraft can obtain good propulsion performance under different flight conditions (subsonic, supersonic, hypersonic) . figure 1 Shown is a schematic diagram of the tandem TBCC structure. The characteristic of the tandem layout is that the ramjet engine is placed behind the turbine engine, and the two engines share th...

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Abstract

The invention discloses an optimization method for a communication network topology structure of a distributed control system of a turbine based combined cycle engine. The method comprises the following steps of 1), establishing a TBCC engine geometric model and a mesh model; 2), optimizing positions of intelligent central nodes of a star structure; and 3), optimizing a TBCC engine bus-star hybridtopology structure. According to the method, the topology connection of intelligent nodes in the TBCC engine is converted into shortest distance and business travel problems, thereby optimizing solution problems; connection modes among the nodes are optimized through graph theory knowledge and a genetic algorithm; and a distributed control system topology network with the shortest inter-node connection bus harness is obtained.

Description

technical field [0001] The invention belongs to the technical field of aerospace combined engine control, and in particular relates to a hybrid topology optimization method for a communication network of a distributed control system of a turbine-based combined cycle engine. Background technique [0002] Hypersonic aircraft has become the main strategic development direction of future aircraft. Its flight range is very wide, and its flight Mach number extends from subsonic, transonic, supersonic to hypersonic. Today, the flight Mach number of an aero turbine engine is generally 0-3, the flight Mach number of a sub-combustion ramjet engine is 2-6, and the flight Mach number of a scramjet engine is greater than 6. It can be seen that any single air-breathing engine cannot meet the above requirements. Therefore, since the 1960s, foreign countries have launched extensive and in-depth research on combined power. Hypersonic technology is currently one of the key technologies activ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H04L12/24H04L12/40H04L12/44G06F17/50
Inventor 潘慕绚梅满黄金泉李岩戴冬红聂聆聪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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