Fault simulated analysis method for afterburning cycle rocket engine

A rocket engine and fault simulation technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as complexity, product structure damage, and heavy workload.

Inactive Publication Date: 2013-05-22
NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The afterburning cycle engine is the main power device of my country's new generation of launch vehicles. Its system is more complex than the conventional engine in service, with more types and quantities of components. There are dozens of detection parameters during the test run. If the oxygen system fails, the consequences are often products. severe structural damage
In the past, the failure analysis work was completed entirely by the designer's experience and product decomposition and inspection. The workload was very heavy, and it was greatly affected by the designer's personal experience.

Method used

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  • Fault simulated analysis method for afterburning cycle rocket engine
  • Fault simulated analysis method for afterburning cycle rocket engine
  • Fault simulated analysis method for afterburning cycle rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0193] 1. According to the specific system composition of the engine (see figure 1 ) and component characteristics, and establish a mathematical model for the steady-state operation of the engine.

[0194] A pump static mathematical model:

[0195] (1) lift

[0196] Δp = a · n 2 · ρ + b · n · q m + c · q m 2 ρ - - - ( 1 )

[0197] In the formula: Δp—head;

[0198] a, b, c—head characteristic parameters (obtained through hydraulic test);

[0199] n,q m , ρ—speed, medium flow and density.

[0200] (2) Power

[0201] P = A · n ...

Embodiment 2

[0320] Typical failure mode simulation, effect characteristic analysis

[0321] 1. According to the specific system composition of the engine (see figure 1 ) and component characteristics, and establish a mathematical model for the steady-state operation of the engine.

[0322] 2. The failure mode effect table is obtained by simulating and analyzing the effect characteristics of the following typical failure modes, see Table 1 for details.

[0323] Table 1 Failure mode effect table

[0324]

[0325] The fault sensitivity of the parameter is defined as:

[0326] f ( x ) 1 Δa % > 1 % 0 - 1 % ≤ ...

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PUM

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Abstract

The invention relates to a fault simulated analysis method for an afterburning cycle rocket engine. The fault simulated analysis method comprises the following steps: (1) according to the system composition and characteristics of components of the afterburning cycle rocket engine, a model is constructed through the theories of hydromechanics, pneumodynamics and thermodynamics; (2) a fault feature equation is embedded in the model; (3) an equation set generated in the steps is solved through the linearized Newton iteration method, so that a simulated result is obtained; and (4) according to the thermal parameter characteristics, faults possibly occurring in the process of heat run of the engine or the flying state of the engine are pre-judged before a test through the statistical parameters obtained in advance, or the faults are positioned after the test compared with the parameter variation trend actually measured after the process of heat run of the engine or the flying process of the engine. The fault simulated analysis method for the afterburning cycle rocket engine overcomes the defects in the prior art, and greatly improves the efficiency and accuracy of fault analysis.

Description

technical field [0001] The invention relates to a fault simulation analysis method of a supplementary combustion cycle rocket engine. Background technique [0002] The afterburning cycle engine is the main power device of my country's new generation of launch vehicles. Its system is more complex than the conventional engine in service, with more types and quantities of components. There are dozens of detection parameters during the test run. If the oxygen system fails, the consequences are often products. Severe structural damage. In the past, the failure analysis work was completed entirely by the designer's experience and product disassembly and inspection. The workload was very heavy, and it was greatly affected by the designer's personal experience. The invention can greatly improve the efficiency and accuracy of fault location. Contents of the invention [0003] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 刘站国徐浩海马红宇党锋刚杨永强王海燕宋春
Owner NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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