CN107554812B - Bonding mechanical loading method of multilayer combined type thermal protection component - Google Patents
Bonding mechanical loading method of multilayer combined type thermal protection component Download PDFInfo
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- CN107554812B CN107554812B CN201710742893.0A CN201710742893A CN107554812B CN 107554812 B CN107554812 B CN 107554812B CN 201710742893 A CN201710742893 A CN 201710742893A CN 107554812 B CN107554812 B CN 107554812B
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Abstract
The invention belongs to the technical field of thermal protection, and particularly relates to a mechanical loading method for bonding a multi-layer composite thermal protection component. Obtaining an effective area loading coefficient by utilizing the physical characteristics of the heat-proof material and through simulation calculation; designing the distribution of the pressing blocks according to the size of the heat-insulation preventing component and the requirement of the effective bonding area; designing an integrated loading device meeting the strength requirement through simulation calculation; and installing an integrated loading device, loading by a pressing block after the heat-insulation preventing component is bonded, and detecting loading pressure by a pressure sensor. According to the physical characteristics of the heat-insulating material and the requirement of the bonding strength of the component, the effective and operable mechanical loading method is implemented, the bonding effective area can be increased, the bonding strength is ensured, and the idea is developed for the thermal protection technology of the hypersonic aircraft. This mechanical loading process has been subjected to flight test examinations.
Description
Technical Field
The invention belongs to the technical field of thermal protection, and particularly relates to a mechanical loading method for bonding a multi-layer composite thermal protection component.
Background
In order to ensure that the temperature of the bearing structure is controlled within an allowable range, the hypersonic aerocraft needs to be adhered with an anti-heat insulation component on the outer surface. In high-speed movement, the components are subjected to the combined action of multiple loads such as air flow scouring, vibration, thermal deformation, noise and the like, and must have reliable connection strength.
With the development of advanced technology in China, a novel multilayer composite thermal protection material is subjected to flight test examination. The surface layer of the material is a fiber reinforced ceramic panel, the middle part of the material is a flexible aerogel material, and the fiber reinforced ceramic panel and the aerogel material are connected into a whole through sewing fibers. The material is formed in a die, and can be restored to a theoretical shape under an external force (less than or equal to 0.1MPa) because of certain deformation caused by stress release when naturally placed.
In order to improve the bonding reliability of the materials, a certain loading force needs to be applied along the normal direction of the member after the member is bonded in place, so that the matching performance of the bonding interface is improved, and the fusion of the bonding interface and the glue layer is promoted. In the gluing process, vacuum loading is a common gluing loading mode, but for the part of an aircraft with an acute angle, the part of a component which is partially replaced and the part of a component which cannot bear the vacuum loading, an effective mechanical loading method is needed to overcome the deformation of the component in a natural state, make up the influence of aerogel on the loading uniformity under a loading condition, meet the operability of gluing loading and ensure the reliable connection of the external heat-proof component.
Disclosure of Invention
The invention aims to provide a mechanical loading method for bonding a multilayer composite thermal protection component, which is suitable for bonding a local external thermal insulation component of a hypersonic aircraft, and the connection strength of the component meets the requirement of high-speed flight of a product. The specific technical scheme is as follows:
a method for bonding mechanical loading of a multi-layer composite thermal protection component comprises the following steps:
1. designing a mechanical loading device frame meeting the strength requirement by adopting a finite element simulation calculation method;
2. simulating the mechanical loading effect of the conformal pressing block by using the physical characteristics of the multilayer composite thermal protection material and adopting a finite element simulation calculation method;
3. designing the distribution of the conformal pressing blocks according to the requirements of the overall dimension and the effective bonding area of the multilayer composite thermal protection component;
4. designing a loading effect of a compression rod, wherein the compression rod is provided with a spring, and a loading force is generated by compressing the spring;
5. assembling and installing a mechanical loading device; the mechanical loading device comprises a frame, a conformal pressing block and a pressing rod, wherein the frame is matched with the aircraft in shape, a reserved threaded hole in the frame is connected with the aircraft, a reserved unthreaded hole is connected with the pressing rod, the inner profile of the conformal pressing block is matched with the shape of the multilayer composite thermal protection member, the inner profile of the conformal pressing block is bonded with a rubber or felt semi-rigid material and is connected with the pressing rod into a whole in a screw connection mode, the pressing rod is connected with the frame in a clearance fit mode, and the whole mechanical loading device is connected with the aircraft in a screw connection mode;
6. after the multilayer composite thermal protection component is bonded in place, the spring on the compression pressure rod is compressed to generate a loading force, and the shape following pressing block is driven to load the multilayer composite thermal protection component.
Advantageous effects
Reliable bonding of the outer heat-insulation preventing component of the hypersonic aircraft is one of key technologies for ensuring normal operation of the hypersonic aircraft, an effective and operable mechanical loading method is implemented according to the physical characteristics of the heat-insulation preventing material and the bonding strength requirement of the component, the bonding effective area can be increased, the bonding strength is ensured, and the idea is developed for the thermal protection technology of the hypersonic aircraft. This mechanical loading process has been subjected to flight test examinations.
Drawings
The invention has 2 figures in total
FIG. 1 is a schematic view of a mechanical loading apparatus;
FIG. 2 is a schematic diagram of the distribution of conformal compacts;
1-frame, 2-conformal pressing block, 3-pressing rod and 4-threaded hole;
Detailed Description
The invention is further described with reference to the following figures and specific examples.
Example 1
The external dimension of a certain component is 150mm multiplied by 200mm, the compressive strength is 0.2MPa, the component can reach the theoretical external shape under the condition of 0.07MPa, the bonding effective area is not less than 60 percent, and the mechanical loading process flow is as follows:
(1 design mechanical loading device frame 1
Calculating the strength of the frame 1 by adopting a finite element simulation calculation method, wherein the frame material is 20#Steel, yield limit 245Mpa, elastic modulus 206Gpa, poisson's ratio 0.3. According to calculation, a frame 1 structure meeting the strength requirement is designed.
(2) Simulating the mechanical loading effect of the conformal pressure block 2 by adopting a finite element simulation calculation method
The material parameters used in the simulation were as follows: the in-plane tensile modulus of the panel material is 4-6GPa, preferably 5.23GPa, and the tensile Poisson ratio is 0.2-0.4, preferably 0.31; the in-plane compression modulus of the aerogel material is 70-130MPa, preferably 105MPa, and the in-plane compression Poisson ratio is 0.04-0.08, preferably 0.06; the elastic modulus of the adhesive material is 0.5-1.5MPa, preferably 1MPa, and the Poisson ratio is 0.3-0.7, preferably 0.5.
And applying mechanical loading force on the briquette 2, wherein the magnitude of the loading force is determined by multiplying the area of the briquette 2 by 0.2MPa, and the area with the pressure of more than 0.07MPa is about 1.3 times of the area of the briquette through calculation.
(3) Designing the distribution of the conformal briquetting 2 according to the effective area loading coefficient
As shown in figure 1, when the size of the conformal briquetting 2 is designed to be 60mm multiplied by 90mm, the transverse distance L1 of the conformal briquetting is 120mm, and the longitudinal distance L2 of the conformal briquetting is 110mm, the effective loading area coefficient of the member loading pressure which can reach 0.07MPa reaches 65%, and the requirement that the bonding effective area is not less than 60% is met.
(4) Design compression bar loading effect
The compression rod 3 is provided with a spring, the spring is compressed to generate loading force, the rated load of the spring is 400-500N, the rigidity is 20-30N/mm, the free height is 45-55mm, and the corresponding relation between the compression amount of the spring and the loading force is calibrated before use.
(5) Combined installation mechanical loading device
The mechanical loading device comprises a frame 1, a conformal pressing block 2 and a pressing rod 3, wherein the frame 1 is matched with the appearance of the aircraft, a reserved threaded hole 4 in the frame is connected with the aircraft, a reserved unthreaded hole is connected with the pressing rod 3, the inner profile of the conformal pressing block 2 is matched with the appearance of the multilayer composite thermal protection member, the inner profile of the conformal pressing block 2 is bonded with a rubber or felt semi-rigid material and is connected with the pressing rod 3 into a whole in a screw connection mode, the pressing rod 3 is connected with the frame 1 in a clearance fit mode, the clearance is controlled to be 0.05-0.15mm, and the whole mechanical loading device is connected with the aircraft in a screw connection mode;
(6) loading
After the multilayer composite thermal protection component is bonded in place, the spring on the compression pressure rod 3 is compressed to generate a loading force, and the shape following pressing block 2 is driven to load the multilayer composite thermal protection component. The recorded force value is determined by measuring the amount of compression of the spring.
Claims (3)
1. A method for bonding and mechanically loading a multi-layer composite thermal protection component is characterized by comprising the following steps:
1) designing a mechanical loading device frame (1) meeting the strength requirement by adopting a finite element simulation calculation method;
2) simulating the mechanical loading effect of the conformal pressing block (2) by using the physical characteristics of the multilayer composite thermal protection material and adopting a finite element simulation calculation method;
3) designing the distribution of the conformal pressing blocks (2) according to the overall dimension and the effective bonding area requirements of the multilayer composite thermal protection component;
4) designing the loading effect of the pressure lever (3), wherein the pressure lever (3) is provided with a spring, and the spring is compressed to generate loading force;
5) assembling and installing a mechanical loading device; the mechanical loading device comprises a frame (1), a conformal pressing block (2) and a pressing rod (3), wherein the frame (1) is matched with the appearance of the aircraft, a reserved threaded hole (4) in the frame is connected with the aircraft, a reserved unthreaded hole is connected with the pressing rod (3), the inner profile surface of the conformal pressing block (2) is matched with the appearance of the multilayer composite heat protection component, the inner profile surface of the conformal pressing block (2) is bonded with a rubber or felt semi-rigid material and is connected with the pressing rod (3) into a whole in a threaded manner, the pressing rod (3) is connected with the frame (1) in a clearance fit manner, and the whole set of mechanical loading device is connected with the aircraft in a threaded manner;
6) after the multilayer composite thermal protection component is bonded in place, a spring on the compression pressure rod (3) generates a loading force to drive the shape following pressing block (2) to load the multilayer composite thermal protection component.
2. The method for bonding mechanical loads to a multi-layer composite thermal protection member according to claim 1, wherein the material parameters used in the simulation in step 2) are: the in-plane tensile modulus of the panel material is 4-6GPa, the tensile Poisson ratio is 0.2-0.4, the in-plane compressive modulus of the aerogel material is 70-130MPa, the in-plane compressive Poisson ratio is 0.04-0.08, the elastic modulus of the adhesive material is 0.5-1.5MPa, and the Poisson ratio is 0.3-0.7.
3. The method for bonding mechanical loading of a multilayer composite thermal protection member according to claim 1, wherein the magnitude of the loading force in the step 4) is determined by multiplying the area of the conformal compact (2) by 0.2 MPa.
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| 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 |
| 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 |
| 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 |
| 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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| CN103287568B (en) * | 2013-05-27 | 2015-08-05 | 北京玻钢院复合材料有限公司 | A kind of high-speed aircraft anti-heat insulation structural of large area interlayer and forming method thereof |
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