Solid engine charging low-temperature stress equivalent acceleration test method

A solid engine and accelerated test technology, which is applied in the direction of engine testing, machine/structural component testing, measuring devices, etc., can solve the problems of not meeting the special requirements for model storage and long test periods, etc.

Active Publication Date: 2019-07-12
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the evaluation of the structural integrity of the solid motor charge in the natural storage state, the test cycle required for life determination and life extension is very long, and it does not meet the special requirements for model storage, nor does it meet the needs of military use and industrial production departments, so there is an urgent need for a Rapid Test Evaluation Method

Method used

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  • Solid engine charging low-temperature stress equivalent acceleration test method
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  • Solid engine charging low-temperature stress equivalent acceleration test method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047] The low temperature stress equivalent accelerated test of a NEPE propellant Φ200mm circular tube engine charge (hereinafter referred to as "Type I NEPE charge"), the specific steps are as follows:

[0048] (1) 600 dumbbell-shaped samples of a certain NEPE propellant and 3 rounds of Type I NEPE charges were prepared, wherein the length of Type I NEPE charges was 700mm, the depth of both ends was 20mm, the inner diameter was 20mm, and the outer diameter was 200mm , The shell thickness is 5mm.

[0049] (2) Under the conditions of temperature 20°C±5°C and humidity ≤55%RH., the constant strain fracture test was carried out using NEPE propellant standard dumbbell samples, and the constant strain levels were: 80%, 75%, 70%, 65% %, 60%, and 5 samples under each strain level, the relaxation fracture time of the high strain region of the sample is obtained, see Table 2.

[0050] (3) Use a standard dumbbell-shaped sample of a NEPE propellant, with an aging temperature of 60°C, 3 ...

Embodiment 2

[0075] The low temperature stress equivalent accelerated test of a NEPE propellant Φ200*1100mm star hole type engine charge (hereinafter referred to as "Type II NEPE charge"), the specific steps are as follows:

[0076] (1) Prepared 3 rounds of Type II NEPE charges, the charges are star-shaped, with an inner diameter of 30mm and a length of 1100mm. The structure is as follows image 3 shown.

[0077] (2) Since the NEPE propellant formula adopted by type I NEPE charge and II type NEPE charge is the same, so the NEPE propellant relaxation and fracture time model in this example is the same as that in Example 1, see in Example 1 Formula (11).

[0078] (3) One round of Type II NEPE charge was used to conduct a progressive cooling test. When the charge reached temperature equilibrium at each temperature, its structural integrity was judged by CT flaw detection, and then the ultimate failure temperature of the charge was determined. The test results See Table 5. The test results ...

Embodiment 3

[0086] The low temperature stress equivalent accelerated test of a HTPB propellant Φ200mm circular tube motor charge (hereinafter referred to as "HTPB charge"), the specific steps are as follows:

[0087] (1) 600 dumbbell-shaped samples of a HTPB propellant and 3 rounds of HTPB charges were prepared, wherein the length of the HTPB charges was 600mm, the depth of both ends was 20mm, the inner diameter was 20mm, the outer diameter was 200mm, and the shell thickness is 5mm.

[0088] (2) Under the conditions of temperature 20°C±5°C and humidity ≤55%RH., the constant strain fracture test was carried out using the HTPB propellant standard dumbbell-shaped sample, and the constant strain levels were: 15%, 20%, 25% and 30% %, 5 samples under each strain level, the relaxation fracture time of the high strain region of the sample is obtained, see Table 6.

[0089] (3) Use a standard dumbbell-shaped sample of HTPB propellant, aging temperature 50°C, 3 constant strain levels: 5%, 10%, 15%...

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Abstract

The invention provides a solid engine charge low-temperature stress equivalent acceleration test method, which is based on a time-temperature damage equivalent principle and adopts a test method combining fixed strain fracture and thermal coupling accelerated aging. A solid propellant relaxation failure time model in a wide strain area is obtained; the low-temperature stress acceleration coefficient and the equivalent acceleration test time of charging are calculated in combination with lasting strain of a dangerous part under the long-term storage / low-temperature stress acceleration state, and the equivalent relationship between the long-term storage and the low-temperature stress acceleration state is determined; a test is carried out according to the determined test temperature and time; and the structural integrity of the solid engine charge in a long-term storage state is evaluated according to the structural integrity of the solid engine charge after the test. The method realizesrapid determination and evaluation of the structural integrity of the solid engine in a long-term storage state, is applied to solid engine charging service life evaluation, service life determination and service life prolongation, and can save a lot of test funds and time.

Description

technical field [0001] The present invention generally relates to the technical field of solid motors, in particular to a solid motor charge low temperature stress equivalent accelerated test method. Background technique [0002] The solid motor charge is cast from the casing, heat insulation layer, liner and solid propellant, and is the main power system of the missile weapon. Solid propellant is a mixture of polymer matrix and solid particle filler, and its mechanical properties depend on temperature, time and loading history. During the long-term storage process, the solid propellant on the inner surface of the solid motor charge is in a state of permanent strain, and there is a possibility of relaxation and fracture. Therefore, the study on the failure of the propellant under the permanent strain state is important for the evaluation of the structural integrity of the solid motor charge, Life assessment, life determination and life extension are of great significance. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00
CPCG01M15/00
Inventor 张峰涛彭松沙宝林池旭辉杨根赵程远曹蓉
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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