CN108804813A - A kind of space precise tracking reliability estimation method - Google Patents
A kind of space precise tracking reliability estimation method Download PDFInfo
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- CN108804813A CN108804813A CN201810581542.0A CN201810581542A CN108804813A CN 108804813 A CN108804813 A CN 108804813A CN 201810581542 A CN201810581542 A CN 201810581542A CN 108804813 A CN108804813 A CN 108804813A
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Abstract
The invention discloses a kind of space precise tracking reliability estimation methods, include the following steps：Step 1: proposing a kind of space precise tracking design scheme；Step 2: identifying engine reliability weak link；Step 3: carrying out special reliability test for engine weak link；Step 4: the reliability to weak link is assessed；Step 5: carrying out engine whole aircraft reliability verifies work, engine reliability verification is dissolved into engine design verification test and environmental acceptance test；Step 6: assessing engine reliability.The present invention has the following advantages：1) reliability test number and engine sample number are reduced；2) it reduces rocket engine reliability test and verifies cost；3) shorten the rocket engine lead time；4) low-carbon emission reduction, it is environmentally protective.
Description
Technical field
The present invention relates to spacecraft propulsion system technical field more particularly to a kind of space precise tracking reliability assessments
Method.
Background technology
Space precise tracking is the heart of the spacecrafts such as carrier rocket Upper Stage, satellite, and becoming rail posture adjustment for spacecraft carries
For power, generally have the function of sway in both directions, repeatedly start, can be long-term in-orbit etc..The reliability of engine is directly related to boat
The success or failure that its device emits, flies.
Engine inherent reliability designs, but it is also what production guarantee and verification experimental verification came out, it is necessary to
Engine could be fully exposed in design, technique and raw material selection etc. by enough test period and test number (TN)
Defect and weak link, and raising reliability is achieved the purpose that by sustained improvement.
Technology status at home and abroad is made a general survey of, space precise tracking reliability assessment mostly uses more increment engine reliability heat
The method of test run accumulation.Though the method for more increment engine reliability heat run accumulations is conducive to space precise tracking reliability
The adequacy and authenticity of verification, but have the following deficiencies：1) experimentation cost is high；2) test period is very long；3) it is easily introduced low
Level quality problems；4) a large amount of propellant combustion increases air carbon emission, is unfavorable for atmospheric environment protection, is pushed away for conventional
Into agent, a large amount of toxic gases are will produce.
Invention content
To solve the above problems, the present invention proposes a kind of space precise tracking reliability estimation method, can be used for
Space precise tracking reliability index verification, identifies weak link, and direction, reliability assessment are provided for engine product improvement
Risk tradeoff when as a result can be also used for that model is supported to select product.
The present invention is realized especially by following technical scheme：
A kind of space precise tracking reliability estimation method, includes the following steps：
Step 1, according to model mission requirements and engine product feature, propose a kind of space precise tracking design side
Case；
Step 2 identifies engine reliability weak link, and the mainly link including easy break-down, test is not exclusively covered
The link of lid, the link potential dangerous to compositions such as quality and performances；
Step 3 carries out special reliability test for engine weak link, designs engine weak link testpieces,
Detailed engine weak link test method is formulated, specific engine weak link special project reliability test is carried out, if hair
Motivation weak link special project reliability test can not propose a kind of space precise tracking again by verification, palpus return to step 1
Design scheme；
Step 4 assesses the reliability of weak link, selects suitable Reliability Evaluation Model, and it is suitable to determine
Characteristic quantities provide the engine weak link reliability assessment of corresponding confidence level as a result, examining with the test data of step 3
The factors such as experiment funds and test period are considered, if assessed reliability result is more than 0.9999, you can think engine weakness ring
Fully examination verification, engine weak link reliability reach 1 to section；
Step 5 carries out the verification work of engine whole aircraft reliability, and engine design side is dissolved into engine reliability verification
In case verification test and environmental acceptance test, to reduce test number (TN) and test sample number, the experiment of space precise tracking to the greatest extent
Verification is an incremental process, and engine whole aircraft reliability verification process includes design scheme ground run, design side
Ground run after the high blank test of case, identification grade dynamic environmental test, high blank test, reliability after identification grade dynamic environmental test
Vehicle, batch sampling observation test run are interviewed, if the test run of engine whole aircraft reliability can not again be proposed a kind of by verification, palpus return to step 1
Space precise tracking design scheme；
Step 6 assesses engine reliability, selects Weibull distribution model, selected shape parameter, with engine
Cumulative activation number is main characteristic quantity, is provided in conjunction with the test data of step 5 using cumulative operation time as secondary feature amount
The engine reliability assessment result of corresponding confidence level.
Compared with prior art, the present invention has the advantages that：
1) reliability test number and engine sample number are reduced；2) reduce rocket engine reliability test verification at
This；3) shorten the rocket engine lead time；4) low-carbon emission reduction, it is environmentally protective.
Expansion of the present invention is strong, can be used for space precise tracking reliability assessment, and other kinds of rocket is sent out
Motivation reliability assessment also has certain reference.
Description of the drawings
Fig. 1 is a kind of operational flowchart of space precise tracking reliability estimation method of the embodiment of the present invention；
Fig. 2 is a kind of space precise tracking structural schematic diagram；
Fig. 3 is a kind of ejector filler header weld testpieces structural schematic diagram of space precise tracking.
Specific implementation mode
With reference to specific embodiment, the present invention is described in detail.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be noted that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection domain.
As shown in Figure 1, being a kind of space precise tracking reliability estimation method, packet an embodiment of the present invention provides Fig. 1
Include following steps
Step 1, a kind of space precise tracking of design.Referring to Fig. 2, engine includes mainly thrust chamber, valve and waves
Mechanism, thrust chamber include mainly ejector filler head, re-generatively cooled body portion and jet pipe extended segment, and wabbler mechanism includes mainly installation branch
Frame waves component.
Step 2 identifies engine reliability weak link.When engine is switched on, propellant filling leads to ejector filler head
Portion's weld seam one-way bearing pressure, multiple start operating performance may cause ejector filler header weld fatigue failure, the failure of ejector filler header weld
Oxidant and fuel can be caused to contact, ejector filler header weld is to the potential dangerous ring of the compositions such as engine quality and performance
Section.
Step 3 carries out special reliability test for engine weak link.It is welded according to engine product ejector filler head
Welding line structure size and the welding technique requirement of seam, the completely the same ejector filler header weld testpieces of design welding structure, ginseng
See Fig. 3.Pressure cycling test is carried out using 3 sets of ejector filler header weld testpieces, the ozzle on testpieces is connect with hydraulic pressure platform,
Pressure rises to 4.2MPa, and removal pressure after pressurize 5s recycles 333 times, interval time 5s, after hydraulic test, has no examination
Part is tested to there is deformation or destroy.
Step 4 assesses the reliability of weak link.Using Weibull distribution model, selected shape parameter m is
3.0, confidence level 0.7, according to 20 indexs of engine cumulative activation number, assessment weld seam one-way bearing pressure structural reliability is
0.99991, ejector filler header weld Structural Reliability Evaluation result is more than 0.9999, you can thinks that the weak link is fully examined
Card is veritified, ejector filler header weld structural reliability reaches 1.
Step 5 carries out the verification work of engine whole aircraft reliability.Successively carry out design scheme ground run, design scheme
Ground run after high blank test, identification grade dynamic environmental test, high blank test, reliability ground after identification grade dynamic environmental test
Test run, batch sampling observation test run.It is counted according to engine whole aircraft reliability test situation, engine reliability increment totally 7, engine
Cumulative operation time 20140s, engine cumulative activation number 590 times, refers to table 1.
Step 6 assesses engine reliability.Using Weibull distribution model, selected shape parameter m is 3.0, is set
Reliability is 0.7, with engine cumulative activation number 20 times for main characteristic quantity, using cumulative operation time 800s as secondary feature
Amount provides reliability assessment as a result, assessing engine reliable by engine cumulative activation number in conjunction with the test data of step 5
Degree is 0.9981, is 0.9957 by cumulative operation time assessment engine reliable degree.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (1)
1. a kind of space precise tracking reliability estimation method, which is characterized in that this method comprises the following steps：
Step 1, according to model mission requirements and engine product feature, propose a kind of space precise tracking design scheme；
Step 2 identifies engine reliability weak link, including the link of easy break-down, the link of the endless all standing of test,
Potential dangerous link is constituted to quality and performance；
Step 3 carries out special reliability test for engine weak link, designs engine weak link testpieces, formulates
Detailed engine weak link test method carries out specific engine weak link special project reliability test, if engine
Weak link special project reliability test can not propose a kind of space precise tracking design again by verification, palpus return to step 1
Scheme；
Step 4 assesses the reliability of weak link, selects suitable Reliability Evaluation Model, determines suitable reliable
Property characteristic quantity, if with the test data of step 3 provide corresponding confidence level engine weak link reliability assessment as a result, assessment
Reliability result is more than 0.9999, you can thinking engine weak link, fully examination verification, engine weak link are reliable
Degree reaches 1；
Step 5 carries out the verification work of engine whole aircraft reliability, and engine reliability verification is dissolved into engine design and is tested
In confirmatory test and environmental acceptance test, to reduce test number (TN) and test sample number, space precise tracking verification experimental verification to the greatest extent
It is an incremental process, engine whole aircraft reliability verification process includes design scheme ground run, design scheme height
High blank test, reliability ground examination after ground run, identification grade dynamic environmental test after blank test, identification grade dynamic environmental test
Vehicle, batch sampling observation test run, if the test run of engine whole aircraft reliability can not propose a kind of space again by verification, palpus return to step 1
Precise tracking design scheme；
Step 6 assesses engine reliability, selects Weibull distribution model, selected shape parameter accumulative with engine
Work times are main characteristic quantity, and correspondence is provided in conjunction with the test data of step 5 using cumulative operation time as secondary feature amount
The engine reliability assessment result of confidence level.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810581542.0A CN108804813B (en) | 2018-06-07 | 2018-06-07 | Reliability assessment method for space rail-controlled engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810581542.0A CN108804813B (en) | 2018-06-07 | 2018-06-07 | Reliability assessment method for space rail-controlled engine |
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| CN108804813A true CN108804813A (en) | 2018-11-13 |
| CN108804813B CN108804813B (en) | 2022-07-26 |
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Cited By (4)
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| CN109582692A (en) * | 2018-11-15 | 2019-04-05 | 北京宇航系统工程研究所 | A kind of carrier rocket test data interpretation method and system based on formalized description |
| CN109839267A (en) * | 2019-03-12 | 2019-06-04 | 北京宇航系统工程研究所 | A kind of valve storage period appraisal procedure |
| CN112182782A (en) * | 2020-11-02 | 2021-01-05 | 中国运载火箭技术研究院 | Carrier rocket environment adaptability analysis method, system, terminal and medium |
| CN112883497A (en) * | 2021-03-22 | 2021-06-01 | 中国人民解放军国防科技大学 | Aerospace valve reliability assessment method based on multi-source information fusion |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112182782A (en) * | 2020-11-02 | 2021-01-05 | 中国运载火箭技术研究院 | Carrier rocket environment adaptability analysis method, system, terminal and medium |
| CN112182782B (en) * | 2020-11-02 | 2024-05-10 | 中国运载火箭技术研究院 | Carrier rocket environment adaptability analysis method, system, terminal and medium |
| CN112883497A (en) * | 2021-03-22 | 2021-06-01 | 中国人民解放军国防科技大学 | Aerospace valve reliability assessment method based on multi-source information fusion |
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| CN108804813B (en) | 2022-07-26 |
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