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General simulation method for liquid rocket engine

A simulation method, liquid rocket technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as limited token analysis capabilities and complex solvers, achieving good stability and robustness, and operating efficiency. High, speed up the effect of running

Active Publication Date: 2013-03-13
BEIJING INST OF AEROSPACE TESTING TECH
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  • Abstract
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Problems solved by technology

However, its solver is extremely complicated, and its workload is no less than developing a separate compilation environment, and its ability to analyze tokens is limited

Method used

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  • General simulation method for liquid rocket engine
  • General simulation method for liquid rocket engine
  • General simulation method for liquid rocket engine

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Embodiment Construction

[0018] The present invention is a generalized simulation method for liquid rocket engines, and the schematic diagram of the software structure for realizing the method is shown in image 3 , consists of six parts: model construction unit, system construction unit, code generation unit, calculation unit, data processing unit, and graphic display unit. Each part is independent and closely related to each other, forming an inseparable whole together. Among them, the model construction unit and the code generation unit are the core parts of the software, and also the basis for the realization of the software versatility. :

[0019] The specific implementation steps of the model construction unit are as follows: First, design the identification code (ID) of the model class, which is determined when the model class is created and is unique. No matter how the user edits the model class, its ID will not be changed unless the model class is deleted from the model class library. Befor...

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Abstract

The invention discloses a general simulation method for a liquid rocket engine, which can provide services more flexible, general and easy to operate to users. The method comprises the following steps: (1) constructing a part model; dividing a part model for engine simulation computation into a model type and a simulation instance; (2) constructing a system simulation model; adding the model type established in the first step to a simulation system to achieve instantiation of the model type so as to generate a model instance; (3) generating an executable code through a model text; and (4) performing system simulation computation; firstly, loading a DLL (Dynamic Link Library) file with the executable code saved therein, which is generated by the model text in the third step; performing simulation computation of a corresponding algorithmic logic in the model; reading data from a data exchanging area at the beginning of the computation and transmitting the data to an operable code; and saving a simulation result into the data exchanging area after the computation is finished. The above steps are circulated until the simulation computation is finished.

Description

technical field [0001] The invention is mainly used in the field of liquid rocket engine performance simulation technology. Background technique [0002] Liquid rocket engine simulation is mainly used to simulate the working process of the engine, predict the performance of the engine, and provide a theoretical basis for the design and optimization of the engine. In order to improve the efficiency of the development of liquid rocket engine components and system simulation, reduce the difficulty of development work, and liberate researchers from complicated computer programming and code debugging, many simulation software with good versatility have been developed. [0003] At present, the modular simulation that is widely used in engineering in China is the engine transient process modular modeling and simulation software (LRETMMSS) developed by Liu Kun of the National University of Defense Technology. The software is written in C++ language and has a visual interface. The so...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 段娜朱子环周磊耿卫国管理陈锋张伟周文怡尚宇宋绪勇方俊雅李琪琪冯斌李山峰杨懿
Owner BEIJING INST OF AEROSPACE TESTING TECH
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