CN107554812A - A kind of bonding machinery loading method of multi-layer combined thermal protection component - Google Patents
A kind of bonding machinery loading method of multi-layer combined thermal protection component Download PDFInfo
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- CN107554812A CN107554812A CN201710742893.0A CN201710742893A CN107554812A CN 107554812 A CN107554812 A CN 107554812A CN 201710742893 A CN201710742893 A CN 201710742893A CN 107554812 A CN107554812 A CN 107554812A
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- briquetting
- thermal protection
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention belongs to thermal protection technology field, and in particular to a kind of method of multi-layer combined thermal protection component bonding machinery loading.Using the physical characteristic of anti-heat-barrier material, by simulation calculation, effective area loading coefficient is obtained；According to the size of anti-heat insulating component and the requirement of effective bond area, the distribution of briquetting is designed；By simulation calculation, design meets the integrated loading device of intensity requirement；The integrated loading device of installation, implements to load, on-load pressure is detected by pressure sensor after anti-heat insulating component bonding by briquetting.The present invention implements effective, exercisable mechanical load method, can improve bonding effective area, ensure glue-joint strength, thinking has been opened up for hypersonic aircraft thermal protection technology according to anti-heat-barrier material physical characteristic, component adhesive strength demand.The process of this mechanical load has been subjected to flight test examination.
Description
Technical field
The invention belongs to thermal protection technology field, and in particular to a kind of multi-layer combined thermal protection component bonding machinery adds
The method of load.
Background technology
Hypersonic aircraft is to ensure bearing structure temperature control in admissible scope, it is necessary to be glued in outer surface
Take over control heat insulating component.In high-speed motion, component will be subjected to the multi-loads such as airflow scouring, vibration, thermal deformation, noise and make jointly
With, it is necessary to have reliable bonding strength.
With the development of domestic high technology, a kind of new multi-layer combined thermally protective materials are subjected to flight test
Examination.This kind of material surface is fiber reinforced ceramic panel, and centre is flexible aerogel material, is connected by staples
It is integral.In mould internal shaping, because stress release has certain deformation when placing naturally, at external force (≤0.1MPa)
Under can return to theoretical shape face.
In order to improve the bonding reliability of this kind of material, need to apply necessarily along component normal direction in place afterwards in component bonding
Loading force, improve the matching of bonding interface, promote merging for bonding interface and glue-line.In adhesive technology, vacuum load
Conventional splicing load mode, but changed the outfit for aircraft with the position of acute angle, component partial position, in cabin into
Part can not bear the position of vacuum load, need badly and seek a kind of effective mechanical load method, to overcome nature lower member
Deformation, make up aeroge under loading environment to loading the influence of uniformity, meeting the operability that is bonded loading, to ensure
Outer anti-hot component is reliably connected.
The content of the invention
It is an object of the invention to provide a kind of method of multi-layer combined thermal protection component bonding machinery loading, it is applicable
In the bonding of the local outer anti-heat insulating component of hypersonic aircraft, bonding strength meets product high-speed flight requirement.Particular technique
Scheme is as follows：
A kind of method of multi-layer combined thermal protection component bonding machinery loading, comprises the following steps：
1st, the machinery loading device framework of intensity requirement is met using the method design of finite element stimulation；
2nd, using the physical characteristic of multi-layer combined thermally protective materials, using the method for finite element stimulation to profile-followed
The mechanical load effect of briquetting is simulated；
3rd, according to the appearance and size of multi-layer combined thermal protection component and the requirement of effective bond area, profile-followed briquetting is designed
Distribution；
4th, depression bar loading effect is designed, depression bar is furnished with a spring, and loading force is produced by implementing compression to spring；
5th, combination installation machinery loading device；Machinery loading device includes framework, profile-followed briquetting and depression bar, and framework is with flying
Row device form fit, reserved screwed hole is connected with aircraft on framework, and reserved unthreaded hole is connected with depression bar, the inner mold of profile-followed briquetting
Face and combined type heat guard member form fit, the inner mold face of profile-followed briquetting bonds rubber or felts semi-rigid material, with pressure
Bar is connected integral by way of being spirally connected, and depression bar is connected with framework by gap, and a whole set of machinery loading device passes through
The mode being spirally connected is connected with aircraft；
6th, after multi-layer combined thermal protection component is bonded in place, loading force is produced by compressing the spring on depression bar, is driven
Profile-followed briquetting is moved to load thermal protection component.
Beneficial effect
Outside hypersonic aircraft the reliable bonding of anti-heat insulating component be ensure aircraft normal work key technology it
One, according to anti-heat-barrier material physical characteristic, component adhesive strength demand, implement effective, exercisable mechanical load method,
Bonding effective area can be improved, ensure glue-joint strength, thinking has been opened up for hypersonic aircraft thermal protection technology.It is this
The process of mechanical load has been subjected to flight test examination.
Brief description of the drawings
The present invention shares 2 secondary accompanying drawings
Fig. 1 is machinery loading device schematic diagram
Fig. 2 is profile-followed briquetting distribution schematic diagram；
1- frameworks, the profile-followed briquettings of 2-, 3- depression bars, 4- screwed holes；
Embodiment
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.
Embodiment 1
Certain member profile size is 150mm × 200mm, compression strength 0.2MPa, can be reached under the conditions of 0.07MPa
To theoretical profile, bonding effective area is not less than 60%, and its mechanical load technological process is as follows：
(1 design machinery loading device framework 1
The intensity of framework 1 is calculated using the method for finite element stimulation, frame material 20#Steel, surrender pole
Limit 245Mpa, modulus of elasticity 206Gpa, Poisson's ratio 0.3.According to calculating, the structure of framework 1 for meeting intensity requirement is designed.
(2) the mechanical load effect of profile-followed briquetting 2 is simulated using the method for finite element stimulation
Material parameter used is as follows in emulation：Stretch modulus is 4-6GPa, preferably 5.23GPa in panel material face, is drawn
Stretch Poisson's ratio 0.2-0.4, preferably 0.31；Modulus of compressibility is 70-130MPa, preferably 105MPa in aerogel material face, face internal pressure
Contracting Poisson's ratio 0.04-0.08, preferably 0.06；Adhesive material modulus of elasticity is 0.5-1.5MPa, preferably 1MPa, Poisson's ratio
0.3-0.7, preferably 0.5.
Apply mechanical load power on profile-followed briquetting 2, the size of loading force is multiplied by according to the area of profile-followed briquetting 2
0.2MPa is determined, by calculating, region of the pressure more than 0.07MPa is about 1.3 times of briquetting area.
(3) according to effective area loading coefficient, the distribution of profile-followed briquetting 2 is designed
As shown in figure 1, it is 60mm × 90mm to design the profile-followed size of briquetting 2, profile-followed briquetting lateral separation L1 is 120mm, with
When shape briquetting fore-and-aft distance L2 is 110mm, effective load-carrying area coefficient that component on-load pressure can reach 0.07MPa reaches
65%, meet the requirement that bonding effective area is not less than 60%.
(4) depression bar loading effect is designed
Depression bar 3 is furnished with a spring, and loading force is produced by implementing compression to spring, select the rated load of spring for
400-500N, rigidity 20-30N/mm, free height 45-55mm, the decrement using preceding demarcation spring are corresponding with loading force
Relation.
(5) combination installation machinery loading device
Machinery loading device includes framework 1, profile-followed briquetting 2 and depression bar 3, framework 1 and aircraft form fit, on framework
Reserved screwed hole 4 is connected with aircraft, and reserved unthreaded hole is connected with depression bar 3, and inner mold face and the combined type heat of profile-followed briquetting 2 protect
Member profile matches, and the inner mold face of profile-followed briquetting 2 bonds rubber or felts semi-rigid material, passes through the side that is spirally connected with depression bar 3
Formula connection is integral, and depression bar 3 is connected with framework 1 by gap, and clearance control adds in 0.05-0.15mm, a whole set of machinery
Carry to put and be connected by way of being spirally connected with aircraft；
(6) load
After multi-layer combined thermal protection component is bonded in place, loading force, driving are produced by compressing the spring on depression bar 3
Profile-followed briquetting 2 loads to thermal protection component.Record force value and judged by measuring the decrement of spring.
Claims (3)
- A kind of 1. method of multi-layer combined thermal protection component bonding machinery loading, it is characterised in that comprise the following steps：1) the machinery loading device framework (1) of intensity requirement is met using the method design of finite element stimulation；2) using the physical characteristic of multi-layer combined thermally protective materials, using the method for finite element stimulation to profile-followed briquetting (2) mechanical load effect is simulated；3) according to the appearance and size of multi-layer combined thermal protection component and the requirement of effective bond area, profile-followed briquetting (2) is designed Distribution；4) depression bar (3) loading effect is designed, depression bar (3) is furnished with a spring, and loading force is produced by implementing compression to spring；5) combination installation machinery loading device；Machinery loading device includes framework (1), profile-followed briquetting (2) and depression bar (3), framework (1) with aircraft form fit, reserved screwed hole (4) is connected with aircraft on framework, is reserved unthreaded hole and is connected with depression bar (3), with The inner mold face of shape briquetting (2) and combined type heat guard member form fit, the inner mold face of profile-followed briquetting (2) bond rubber or felt Class semi-rigid material, is connected integral with depression bar (3) by way of being spirally connected, and depression bar (3) is coordinated with framework (1) by gap Connection, a whole set of machinery loading device are connected by way of being spirally connected with aircraft；6) after multi-layer combined thermal protection component is bonded in place, loading force, driving are produced by compressing the spring on depression bar (3) Profile-followed briquetting (2) loads to thermal protection component.
- 2. the method for multi-layer combined thermal protection component bonding machinery loading according to claim 1, it is characterised in that institute Stating material parameter used in being emulated in step 2) is：Stretch modulus is 4-6GPa in panel material face, stretching Poisson's ratio 0.2- 0.4, modulus of compressibility is 70-130Mpa in aerogel material face, and Poisson's ratio 0.04-0.08, adhesive material elasticity are compressed in face Modulus is 0.5-1.5MPa, Poisson's ratio 0.3-0.7.
- 3. the method for multi-layer combined thermal protection component bonding machinery loading according to claim 1, it is characterised in that institute The size for stating loading force in step 4) is multiplied by 0.2MPa determinations according to the area of profile-followed briquetting (2).
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| CN201710742893.0A CN107554812B (en) | 2017-08-25 | 2017-08-25 | Bonding mechanical loading method of multilayer combined type thermal protection component |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109290982A (en) * | 2018-11-23 | 2019-02-01 | 宁波智能制造技术研究院有限公司 | A kind of master-slave mode circumference special-shaped shell body protective materials assembly tooling |
| CN110723307A (en) * | 2019-09-30 | 2020-01-24 | 北京星航机电装备有限公司 | Arch-shaped clamp for bonding and loading heat insulation tile for offline replacement and installation of aircraft |
| CN111751272A (en) * | 2020-07-03 | 2020-10-09 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| CN114393906A (en) * | 2021-12-15 | 2022-04-26 | 北京星航机电装备有限公司 | Titanium alloy oil tank thermal insulation layer integrated bonding loading device and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109290982A (en) * | 2018-11-23 | 2019-02-01 | 宁波智能制造技术研究院有限公司 | A kind of master-slave mode circumference special-shaped shell body protective materials assembly tooling |
| CN110723307A (en) * | 2019-09-30 | 2020-01-24 | 北京星航机电装备有限公司 | Arch-shaped clamp for bonding and loading heat insulation tile for offline replacement and installation of aircraft |
| CN110723307B (en) * | 2019-09-30 | 2020-12-22 | 北京星航机电装备有限公司 | Arch-shaped clamp for bonding and loading heat insulation tile for offline replacement and installation of aircraft |
| CN111751272A (en) * | 2020-07-03 | 2020-10-09 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| CN111751272B (en) * | 2020-07-03 | 2021-09-07 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| US11733210B2 (en) | 2020-07-03 | 2023-08-22 | Beijing Institute Of Technology | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| CN114393906A (en) * | 2021-12-15 | 2022-04-26 | 北京星航机电装备有限公司 | Titanium alloy oil tank thermal insulation layer integrated bonding loading device and method |
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| CN107554812B (en) | 2020-02-21 |
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