CN110341988A - A kind of radome fairing and aerospace craft - Google Patents
A kind of radome fairing and aerospace craft Download PDFInfo
- Publication number
- CN110341988A CN110341988A CN201910671698.2A CN201910671698A CN110341988A CN 110341988 A CN110341988 A CN 110341988A CN 201910671698 A CN201910671698 A CN 201910671698A CN 110341988 A CN110341988 A CN 110341988A
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- China
- Prior art keywords
- head
- radome fairing
- shield
- cover body
- purlin
- Prior art date
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- 238000000465 moulding Methods 0.000 claims abstract description 29
- 239000000463 material Substances 0.000 claims abstract description 22
- 238000003032 molecular docking Methods 0.000 claims description 32
- 239000011229 interlayer Substances 0.000 claims description 9
- 239000010410 layer Substances 0.000 claims description 8
- 229920006231 aramid fiber Polymers 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- 239000011347 resin Substances 0.000 claims description 7
- 229920002748 Basalt fiber Polymers 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 230000002787 reinforcement Effects 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 5
- 239000011159 matrix material Substances 0.000 claims description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 4
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 3
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims description 3
- 239000002657 fibrous material Substances 0.000 claims description 3
- 229910052863 mullite Inorganic materials 0.000 claims description 3
- 239000005011 phenolic resin Substances 0.000 claims description 3
- 229920001568 phenolic resin Polymers 0.000 claims description 3
- 229920003257 polycarbosilane Polymers 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 claims 1
- 239000000126 substance Substances 0.000 claims 1
- 230000001681 protective effect Effects 0.000 abstract description 5
- 230000004992 fission Effects 0.000 abstract description 4
- 238000002679 ablation Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 230000001151 other effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000001413 cellular effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Details Of Aerials (AREA)
Abstract
The embodiment of the present invention provides a kind of radome fairing and aerospace craft, wherein radome fairing includes: the head-shield for rectifying cover body and connecting with the rectification cover body；The rectification cover body is seperated with the head-shield to be formed, and the rectification cover body and the head-shield are made of different materials.In the solution of the present invention, radome fairing is released effectively molding internal stress on the basis of guaranteeing radome fairing overall stiffness, intensity, thermal protective performance and integral light using rectification cover body and the molding of head-shield fission, optimize radome fairing outer dimension, improves its whole assembly precision.
Description
Technical field
The present invention relates to dome technology field, a kind of radome fairing and aerospace craft are particularly related to.
Background technique
Radome fairing is for protecting satellite and other payload, to prevent satellite by aerodynamic force, Aerodynamic Heating and sound and vibration etc.
The influence of hostile environment is the important component of aerospace craft.Radome fairing is generally clampshell (two halves) structure, by holding
The composition such as head, inner cone section, cylindrical section, inverted cone segment and longitudinal and transverse direction separating mechanism.According to the difference of carrying duty, every kind of model
Carrier rocket all there is the radome fairings of one or more shapes, such as single star cover, double star cover, more star covers.Long March series is transported
For carrying rocket, also there is the satellite fairing of respective system.
The scheme of radome fairing molding at present is mostly aluminium alloy radome fairing, and entire radome fairing is integrally formed, that there are weight is larger,
The problems such as assembly precision is poor, the process-cycle is longer, poor heat resistance.
Summary of the invention
The present invention provides a kind of radome fairing and aerospace crafts.Radome fairing using rectification cover body and head-shield fission at
Type is released effectively molding internal stress on the basis of guaranteeing radome fairing overall stiffness, intensity, thermal protective performance and integral light, excellent
Change radome fairing outer dimension, improves its whole assembly precision.
In order to solve the above technical problems, the embodiment of the present invention provides following scheme:
A kind of radome fairing, be applied to aerospace craft, the radome fairing include: rectification cover body and with the radome fairing
The head-shield of ontology connection；The rectification cover body is seperated with the head-shield to be formed, and the rectification cover body and the head-shield are adopted
It is made of different materials.
Optionally, the rectification cover body include: lower end circumferential direction L shape end frame, it is two sides longitudinal direction L shape docking purlin, exterior skin, interior
Covering and the lightweight interlayer being set between the exterior skin and inside panel, two sides longitudinal direction L shape docking purlin and it is described under
End ring is connected to L shape end frame.
Optionally, the exterior skin and the inside panel are all made of in carbon fiber, basalt fibre and aramid fiber extremely
A kind of few material is made.
Optionally, the lightweight interlayer include in Polymethacrylimide PMI foam, aluminum honeycomb and aramid fiber paper honeycomb extremely
Few one kind.
Optionally, the rectification cover body lower loop is to L shape end frame and interior exterior skin integrated molding；Two sides longitudinal direction L shape
It docks purlin and uses separately formed, rear riveting.
Optionally, the rectification cover body is connect with the head-shield grafting or by longitudinal direction L shape docking purlin.
Optionally, the head-shield includes: matrix and reinforcement, described matrix using organic siliconresin, phenolic resin, can
At least one of ceramic resin and Polycarbosilane resin material are made, and the reinforcement uses mullite fiber, carbon fiber
It is made at least one of basalt fibre material.
Optionally, the rectification cover body includes the first half shell and the second half shell, first half shell and second
Half shell docks purlin connection by the longitudinal direction L shape.
Optionally, first half shell and the second half shell dock the junction of purlin with the longitudinal direction L shape, are equipped with first
Gasket.
Optionally, the head-shield includes the first half a head cover and the second half a head cover, the first half a head cover and second
Half a head cover is by closing cover docking purlin connection.
Optionally, the first half a head cover and the second half a head cover dock the junction of purlin with the head-shield, are equipped with the
Two gaskets.
Optionally, the radome fairing of aerospace craft further include: at least one of wind deflector and thermal protection layer, it is described to keep out the wind
Plate is mounted on the head-shield and rectification cover body, and the thermal protection layer is set to the radome fairing body outer surface.
The embodiment of the present invention also provides a kind of aerospace craft, including aircraft body and with the aircraft body
The radome fairing of connection, the radome fairing are radome fairing as described above.
Above scheme of the invention is include at least the following beneficial effects:
Above scheme of the invention, by the way that cover body molding seperated with head-shield, and the rectification cover body and institute will be rectified
It states head-shield to be made of different materials, then rectification cover body is connect with head-shield, form radome fairing；To guarantee radome fairing
On the basis of overall stiffness, intensity, thermal protective performance and integral light, it can be released effectively the molding internal stress of radome fairing, optimized
Radome fairing outer dimension improves its whole assembly precision.Meanwhile this radome fairing is directed to the flying ring of rocket flight process superelevation
Border, two rectification cover bodies (containing head-shield) half use wind deflector+gasket double-layer seal mode to realize heat seal between covering, both full
The reliability of foot rocket flight does not influence radome fairing separation again.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of aerospace craft radome fairing of the embodiment of the present invention；
Fig. 2 is the partial enlargement diagram that rectification cover body shown in FIG. 1 is connect with head-shield；
Fig. 3 is the diagrammatic cross-section of rectification cover body shown in FIG. 1；
Fig. 4 is the diagrammatic cross-section of head-shield shown in FIG. 1；
Fig. 5 be rectify cover body half shell with dock between purlin equipped with gasket schematic diagram；
Fig. 6 be head-shield half shell with dock between purlin equipped with gasket schematic diagram.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.
As shown in Figure 1, the embodiment of the present invention provides a kind of radome fairing, it is applied to aerospace craft, radome fairing includes: whole
Stream cover body 1 and the head-shield 2 being connect with the rectification cover body；The rectification cover body 1 is seperated with the head-shield 2 to be formed,
And the rectification cover body 1 and the head-shield 2 are made of different materials.
Embodiment of the invention, by the way that the molding seperated with head-shield 2 of cover body 1, and 1 He of rectification cover body will be rectified
The head-shield 2 is made of different materials, then rectification cover body 1 is connect with head-shield 2, forms radome fairing；So as to have
The effect release molding internal stress of radome fairing, optimizes radome fairing outer dimension, improves its whole assembly precision.
As shown in Fig. 2, the rectification cover body 1 includes: lower end circumferential direction L shape end frame in an alternative embodiment of the invention
15, L shape in two sides longitudinal direction is docked purlin 4, exterior skin 11, inside panel 13 and is set between the exterior skin 11 and inside panel 13
Lightweight interlayer 12, the two sides longitudinal direction L shape docking purlin 4 and lower end circumferential direction L shape end frame 15 connect.The lower end circumferential direction L shape
Hold frame 15 and interior exterior skin integrated molding；The two sides longitudinal direction L shape docking use of purlin 4 is separately formed, and rear riveting certainly may be used
To be connected using other connection types.
Optionally, carbon fiber, basalt fibre and aramid fiber can be used in the exterior skin 11 and the inside panel 13
At least one of equal organic/inorganics fiber material is made.
Optionally, the lightweight interlayer includes in PMI (Polymethacrylimide) foam, aluminum honeycomb and aramid fiber paper honeycomb
It is at least one.
In the embodiment of the invention, exterior skin 11 and the inside panel 13 use organic/inorganic fibrous material, are guaranteeing
While resistance to ablation, the weight of radome fairing can be mitigated significantly, further, rectify the exterior skin 11 of cover body 1 and described interior
The structure that lightweight interlayer 12 is used between covering 13, further mitigates the weight of radome fairing, and lightweight interlayer 12 here is using light
Material, such as PMI foam, aluminum honeycomb or aramid fiber paper honeycomb further mitigate the weight of radome fairing in this way.
Again as shown in Fig. 2, in an alternative embodiment of the invention, the rectification cover body 1 and 2 grafting of head-shield or
Longitudinal L shape by rectifying cover body 1 docks purlin connection.Specifically, it is described rectification cover body 1 exterior skin 11 with head-shield 2
, there is one section of closing in area 10 in junction, and head-shield 2 is inserted into closing in area 10.Here, rectification cover body 1 and head-shield 2 use longitudinal direction L
The modes such as shape docking purlin docking or interface grafting are attached, and are reduced joint face, are further mitigated the weight of radome fairing,
Here longitudinal L shape docking purlin can be integrally formed or seperated molding, riveting after longitudinal L shape docking purlin fission molding.
Optionally, the head-shield 2 includes: matrix and reinforcement, described matrix using organic siliconresin, phenolic resin,
Can at least one of ceramic resin and Polycarbosilane resin material be made, the reinforcement use mullite fiber, carbon fiber
At least one of the organic/inorganics fiber such as peacekeeping basalt fibre material is made.In this way, head-shield 2 uses resistance to ablation material system
Make, improve the thermal protective performance on radome fairing top, and further mitigates the weight of radome fairing.
As shown in figure 3, in an alternative embodiment of the invention, the rectification cover body 1 includes the first half shell 111 and the
Two half shells 112, first half shell 111 and the second half shell 112 are docked purlin 4 by the longitudinal direction L shape and are connected.It is optional
, first half shell 111 and the second half shell 112 are Nian Jie with longitudinal direction L shape docking purlin 4.Here the first half covers
Body 111 and the second half shell 112 are " Ω " shape, two quadrant radome fairings (i.e. the first half shell 111 and the second half shell
112) interface is docked using longitudinal direction L shape docking purlin 4, and docking is accurate and reliable, improves the dimensional stability of radome fairing
And merging precision.In addition, rectification cover body 1 is cone column integral structure, and using the composite construction of covering and interlayer, through co-curing
Molding, while guaranteeing resistance to ablation, alleviates the weight of radome fairing.
As shown in figure 5, in an alternative embodiment of the invention, the first half shell 111 and the second half shell 112 with it is described
The junction of longitudinal L shape docking purlin 4, is equipped with the first gasket 6, so as to realize vibration damping, noise reduction, solar heat protection and other effects.
Here, the rectification cover body 1 can be integrally formed, i.e. the first half shell 111 and the second half shell 112 and institute
It states longitudinal L shape docking purlin 4 to be integrally formed, obtains rectification cover body 1；
Assembly weight can be reduced in the direct laying forming of " Ω " shape die surface, the molding mode by being integrally formed, but easily
Cover is caused to deform, and more demanding to operator.
Certainly, the first half shell 111 and the second half shell 112 and longitudinal direction L shape docking purlin 4 can also it is seperated at
Type；Fission molding can first form rectification cover body in " Ω " shape mold, then in docking purlin mold molding docking purlin, finally carry out
Whole assembly, the molding mode is easy to operate, deflection easy to control, of less demanding to operator, but due to the introducing of fitting surface,
Increase part-structure weight.
In a kind of optional implementation, the section thickness of the first gasket with dock purlin flatness and rectification cover body ruler
It is very little related, such as 2 to 5mm.
As shown in figure 4, in an alternative embodiment of the invention, the head-shield 2 includes the first half a head cover 221 and the second half
Head-shield body 222, the first half a head cover 221 and the second half a head cover 222 dock purlin 3 by head-shield and connect.Optionally, described
First half a head cover 221 and the second half a head cover 222 are Nian Jie with head-shield docking purlin 3.Here the first half a head cover 221 and
Two half a head covers 222 are " Ω " shape, and the interface of the first half a head cover 221 and the second half a head cover 222 uses head-shield pair
The docking of purlin 3 is connect, docking is accurate and reliable, improves the dimensional stability and merging precision of radome fairing.In addition, the head-shield 1 of resistance to ablation
For pyramidal structure, resistance is reduced, and uses the pressurized curing molding of ablation resistant material, thermal protective performance is good.The embodiment of the present invention
In, head-shield 2 is variable thickness, and from top, thickness successively successively decreases axially downward.
As shown in fig. 6, in an alternative embodiment of the invention, the first half a head cover 221 and the second half a head cover 222 and head
The junction of cover docking purlin 3, is equipped with the second gasket 7, so as to realize vibration damping, noise reduction, solar heat protection and other effects.
Here, the head-shield 2 can be integrally formed, i.e. the first half a head cover 221 and the second half a head cover 222 and head-shield pair
The integrated molding of purlin 3 is connect, head-shield 2 is obtained；
Assembly weight can be reduced in the direct laying forming of " Ω " shape die surface, the molding mode by being integrally formed, but easily
Cover is caused to deform, and more demanding to operator.
Certainly, the first half a head cover 221 and the second half a head cover 222 can also seperated moldings with head-shield docking purlin 3；It is seperated
Molding can first form rectification cover body in " Ω " shape mold, then in docking purlin mold molding docking purlin, finally carry out whole dress
To match, the molding mode is easy to operate, deflection easy to control, and it is of less demanding to operator, but due to the introducing of fitting surface, it increases
Part-structure weight.
In a kind of optional implementation, the section thickness of the second gasket 7 with dock purlin flatness and rectification cover body
Size is related, such as 2 to 5mm.
In the above embodiment of the present invention, rectifies cover body 1 and different docking purlin docking is respectively adopted in head-shield 2, improve
The dimensional stability and merging precision of radome fairing.
Again as shown in Figure 1, in an alternative embodiment of the invention, the radome fairing of aerospace craft can also include: to keep out the wind
Plate 5, the wind deflector 5 are mounted on the head-shield 2 and rectification cover body 1, specifically, may be mounted at the head-shield 2 and whole
In the first half shell for flowing cover body 1.Wind deflector 5 is assembled on head-shield 2 and rectification cover body 1, wind deflector 5 uses ablation resistant material
Pressurized curing molding, to reduce the flow perturbation inside radome fairing.In the embodiment of the present invention, the first gasket 6 and
Second gasket 7 can be used heat-barrier material and be made, and in the case where wind deflector failure, can play heat-blocking action.
Again as shown in Fig. 2, in an alternative embodiment of the invention, the radome fairing of aerospace craft can also include: setting
Thermal protection layer 14 in rectification 1 outer surface of cover body.Here, thermal protection layer 14 can stick on rectification cover body 1
Outer surface, thermal protection layer 14 use the pressurized curing molding of ablation resistant material, form effective protection to rectification cover body 1.
The embodiment of the present invention also provides a kind of aerospace craft, including aircraft body and with the aircraft body
The radome fairing of connection, the radome fairing are radome fairing described in Fig. 1 to Fig. 4 as above.All implementations in above-described embodiment
Suitable for the embodiment, it can also reach identical technical effect.Here aircraft body can be the space flight such as satellite and fly
Row device.
The above embodiment of the present invention, by will rectify cover body it is seperated with head-shield molding, and the rectification cover body with
The head-shield is made of different materials, then rectification cover body is connect with head-shield, forms radome fairing；So as to effectively release
Molding internal stress is put, radome fairing outer dimension is optimized, improves its whole assembly precision.Using covering sandwich, further subtract
Light radome fairing overall weight.Head-shield is made using resistance to ablation material, the anti-heat problem on radome fairing top had both been improved, and had also mitigated
The overall weight of radome fairing.
The above embodiment of the present invention, rectification cover body are compound using high-modules carbon fibre and high temperature toughened resin base with head-shield
Material and light weight cellular sandwich, realize Li Re and shock proof effect, realize structure light wt to greatest extent.The present invention
Radome fairing be Feng Kamen complex curvatures shape high rigidity radome fairing, realized the inexpensive purpose quickly manufactured.In addition,
The flight environment of vehicle high in face of rocket flight process radome fairing separates demand with cover is thrown, using the thermosealed Redundancy Design of two pass,
Meet the highly reliable requirement of rocket flight process radome fairing, and meets separation function.
The above is a preferred embodiment of the present invention, it is noted that for those skilled in the art
For, without departing from the principles of the present invention, it can also make several improvements and retouch, these improvements and modifications
It should be regarded as protection scope of the present invention.
Claims (13)
1. a kind of radome fairing, be applied to aerospace craft, which is characterized in that the radome fairing include: rectification cover body and with
The head-shield of the rectification cover body connection；Rectification cover body molding seperated with the head-shield, and the rectification cover body with
The head-shield is made of different materials.
2. radome fairing according to claim 1, which is characterized in that the rectification cover body includes: lower end circumferential direction L shape end
Frame, two sides longitudinal direction L shape docking purlin, exterior skin, inside panel and the lightweight interlayer being set between the exterior skin and inside panel,
Two sides longitudinal direction L shape docking purlin is connected with lower end circumferential direction L shape end frame.
3. radome fairing according to claim 2, which is characterized in that the exterior skin and the inside panel are all made of carbon fiber
At least one of dimension, basalt fibre and aramid fiber material is made.
4. radome fairing according to claim 2, which is characterized in that the lightweight interlayer includes Polymethacrylimide
At least one of PMI foam, aluminum honeycomb and aramid fiber paper honeycomb.
5. radome fairing according to claim 2, which is characterized in that the lower end circumferential direction L shape end frame and interior exterior skin one
Chemical conversion type；Two sides longitudinal direction L shape docks purlin and uses separately formed, rear riveting.
6. radome fairing according to claim 2, which is characterized in that the rectification cover body and the head-shield grafting are logical
Cross longitudinal direction L shape docking purlin connection.
7. radome fairing according to claim 1, which is characterized in that the head-shield includes: matrix and reinforcement, the base
Body using organic siliconresin, phenolic resin, can at least one of ceramic resin and Polycarbosilane resin material be made, it is described
Reinforcement is made of at least one of mullite fiber, carbon fiber and basalt fibre material.
8. radome fairing according to claim 1, which is characterized in that the rectification cover body includes the first half shell and second
Half shell, first half shell and the second half shell are docked purlin by the longitudinal direction L shape and are connected.
9. radome fairing according to claim 8, which is characterized in that first half shell and the second half shell are indulged with described
To the junction of L shape docking purlin, it is equipped with the first gasket.
10. radome fairing according to claim 1, which is characterized in that the head-shield includes the first half a head cover and the second half
Head-shield body, the first half a head cover and the second half a head cover dock purlin connection by head-shield.
11. radome fairing according to claim 10, which is characterized in that the first half a head cover and the second half a head cover with
The junction of head-shield docking purlin, is equipped with the second gasket.
12. radome fairing according to claim 1, which is characterized in that further include: at least the one of wind deflector and thermal protection layer
A, the wind deflector is mounted on the head-shield and rectification cover body, and the thermal protection layer is set to the rectification cover body
Outer surface.
13. a kind of aerospace craft exists including aircraft body and the radome fairing connecting with the aircraft body, feature
In the radome fairing is such as the described in any item radome fairings of claim 1 to 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910671698.2A CN110341988A (en) | 2019-07-24 | 2019-07-24 | A kind of radome fairing and aerospace craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910671698.2A CN110341988A (en) | 2019-07-24 | 2019-07-24 | A kind of radome fairing and aerospace craft |
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| CN110341988A true CN110341988A (en) | 2019-10-18 |
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| CN201910671698.2A Pending CN110341988A (en) | 2019-07-24 | 2019-07-24 | A kind of radome fairing and aerospace craft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112876200A (en) * | 2021-02-03 | 2021-06-01 | 孚莱孚(上海)新材料有限公司 | Low-density aerogel/melamine foam composite material and application thereof |
| CN113932145A (en) * | 2021-10-25 | 2022-01-14 | 山东大学 | On-vehicle LNG gas cylinder of lightweight large capacity combined material |
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| CN210653691U (en) * | 2019-07-24 | 2020-06-02 | 天津爱思达航天科技有限公司 | Fairing and aerospace craft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112876200A (en) * | 2021-02-03 | 2021-06-01 | 孚莱孚(上海)新材料有限公司 | Low-density aerogel/melamine foam composite material and application thereof |
| CN113932145A (en) * | 2021-10-25 | 2022-01-14 | 山东大学 | On-vehicle LNG gas cylinder of lightweight large capacity combined material |
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