CN204788078U - Hot seal structure of radome fairing end cap - Google Patents
Hot seal structure of radome fairing end cap Download PDFInfo
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- CN204788078U CN204788078U CN201520399215.5U CN201520399215U CN204788078U CN 204788078 U CN204788078 U CN 204788078U CN 201520399215 U CN201520399215 U CN 201520399215U CN 204788078 U CN204788078 U CN 204788078U
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- spherical crown
- end cap
- connection box
- deep bead
- crown housing
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Abstract
The utility model relates to a solid carrier rocket rocket body technical field, concretely relates to hot seal structure of radome fairing end cap, the problem that current structure can not satisfy the requirement of solid carrier rocket heat seal is solved to the purpose. Its characterized in that, it includes spherical crown casing, deep bead, prevents heat exchanger, rubber packing pad, bow -shaped connection box and end cap underframe, the deep bead is fixed on the surface of spherical crown casing, prevent that heat exchanger is located the both ends of deep bead, with spherical crown casing fixed connection, bow -shaped connection box setting on the internal surface of the spherical crown casing that corresponds with the deep bead, bow -shaped connection box respectively with spherical crown casing and deep bead fixed connection, rubber packing pad is located the inside of bow -shaped connection box, end cap underframe fixed connection is at the open position of spherical crown casing. Compare with the similar structure of rocket body in the past, the utility model has the advantages of, can satisfy the distinctive solid carrier rocket's of big external pressure, big thermal current load thermal force environmental requirement, the structure is simple relatively simultaneously, and technology realizability is strong.
Description
Technical field
The utility model relates to Solid Launch Vehicle rocket body structure technical field, is specifically related to a kind of radome fairing end cap heat seal structure.
Background technology
According to overall plan and the manufacture claim of Solid Launch Vehicle, the cowling shell end cap developed is at the head of Solid Launch Vehicle, it is subject to and harsh thermal environmental activity more complicated compared with other liquid rockets in flight course, is mainly subject to larger pneumatic Thermal Load.
On bullet rocket body structure, often adopt during distinguish radome fairing end cap designs in liquid rocket, but its heat-flux conditions stood generally all need not consider less than the heat seal design at 30%, the half cover interface place of this project the labyrinth type thermal protection struc ture design tackling larger hot-fluid load.The heat seal requirement of Solid Launch Vehicle can not be met according to existing structure.
Because this project is used for China's solid-rocket dome structure design, rocket bears very large bending load when flying, the locally concentrated forces load at bottom part of fairing separator tie point place is also considerably beyond the load magnitude of rocket and guided missile in the past, and the pneumatically loading hot-fluid load that structure stands is greater than other liquid rockets and strategic missile, further increases the difficulty of cowling design.
Utility model content
The purpose of this utility model solves existing structure can not meet the problem of Solid Launch Vehicle heat seal requirement, provides a kind ofly to go out can bear large external pressure, large hot-fluid load effect can ensure the radome fairing end cap heat seal structure of end cap heat seal performance.
The utility model is achieved in that
A kind of radome fairing end cap heat seal structure, comprises spherical crown housing, deep bead, heat shield, rubber gasket, arc connection box and end cap underframe; Deep bead is fixed on the outer surface of spherical crown housing; Heat shield is positioned at the two ends of deep bead, is fixedly connected with spherical crown housing; Arc connection box is arranged on the inner surface of the spherical crown housing corresponding with deep bead, and arc connection box is fixedly connected with deep bead with spherical crown housing respectively; Rubber gasket is positioned at the inside of arc connection box; End cap underframe is fixedly connected on the aperture position of spherical crown housing.
Spherical crown housing entirety as above is the segment structure of hollow, and opening, is divided into laterally zygomorphic two and half covers to the right; Radius of a ball SR is 441mm, and the distance of segment vertex position distance right-end openings is 320mm.
Deep bead entirety as above is circular arc tabular, and cross section is step, and the height of left part cross section is greater than the height of right part cross section; Deep bead is arranged on the connecting portion of upper and lower two and half covers of spherical crown housing, cover respectively and arc connection box is radial is connected with half below spherical crown housing; The thickness of deep bead is 10mm.
Heat shield as above is overall has the rectangular plate-like structure at " R " angle for root, and the right-end openings of spherical crown housing is stretched out at " R " angle of root; Heat shield covers radial connection with half below spherical crown housing; Heat shield has two, arranges along spherical crown housing axisymmetrical; The thickness of heat shield is 10mm.
Arc connection box entirety as above is arc tabular, and cross section is " L " shape; Arc connection box has two, and the joint face along upper and lower two and half covers of spherical crown housing is symmetrical arranged; The arc connection box of top and above spherical crown housing half covers radial connection; The arc connection box of below covers with half below spherical crown housing respectively and the bottom radial direction of deep bead is connected; Arc connection box cross section is of a size of 30 × 40mm, and wall thickness is 5mm.
Rubber gasket as above is fixedly connected on the upper surface of the arc connection box of below, is compressed by the arc connection box of the arc connection box of top and below; The thickness of rubber gasket is 5 ~ 6mm.
End cap underframe entirety as above is annular, and cross section is " L " shape; The left part of end cap underframe is fixed on the right-hand member of spherical crown housing; The wall thickness of end cap underframe is 5mm.
Spherical crown housing as above, deep bead and heat shield all adopt high silicone/phenolic resin resin bed pressing glass steel material to make; Arc connection box and end cap underframe all adopt 2A14 material to make.
The beneficial effects of the utility model are:
The utility model comprises spherical crown housing, deep bead, heat shield, rubber gasket, arc connection box and end cap underframe.Compared with rocket body similar structures in the past, the utility model has the advantage of, can meet the thermal force environmental requirement of distinctive Solid Launch Vehicle of large external pressure, large hot-fluid load, structure is relatively simple simultaneously, and technique realizability is strong.Hot bearing test verification experimental verification radome fairing end cap meets overall anti-protective hot and heat sealability instructions for use, and radome fairing localized heat safeguard structure successfully reaches its development object.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of radome fairing end cap heat seal structure of the present utility model;
Fig. 2 be a kind of radome fairing end cap heat seal structure of the present utility model watch sectional view attentively.
Wherein: 1. spherical crown housing, 2. deep bead, 3. heat shield, 4 rubber gaskets, 5. arc connection box, 6. end cap underframe.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described further.
As depicted in figs. 1 and 2, a kind of radome fairing end cap heat seal structure, comprises spherical crown housing 1, deep bead 2, heat shield 3, rubber gasket 4, arc connection box 5 and end cap underframe 6.Deep bead 2 is fixed on the outer surface of spherical crown housing 1.Heat shield 3 is positioned at the two ends of deep bead 2, is fixedly connected with spherical crown housing 1.Arc connection box 5 is arranged on the inner surface of the spherical crown housing 1 corresponding with deep bead 2, and arc connection box 5 is fixedly connected with deep bead with spherical crown housing 1 respectively.Rubber gasket 4 is positioned at the inside of arc connection box 5.End cap underframe 6 is fixedly connected on the aperture position of spherical crown housing 1.
Spherical crown housing 1 entirety is the segment structure of hollow, and opening, is divided into laterally zygomorphic two and half covers to the right.Radius of a ball SR is 441mm, and the distance of segment vertex position distance right-end openings is 320mm.Spherical crown housing 1 pair of rocket entirety plays rectified action.
Deep bead 2 entirety is circular arc tabular, and cross section is step, and the height of left part cross section is greater than the height of right part cross section.Deep bead 2 is arranged on the connecting portion that spherical crown housing about 1 two and half covers, and cover respectively and arc connection box 5 is radial is connected with half below spherical crown housing 1.The thickness of deep bead 2 is 10mm.Deep bead 2 is inner for preventing the high-temperature gas produced when rocket flight from entering spherical crown housing 1, and deep bead 2 adopts step labyrinth structure with the connecting portion of spherical crown housing 1, has good heat seal effect.
Heat shield 3 is overall has the rectangular plate-like structure at " R " angle for root, and the right-end openings of spherical crown housing 1 is stretched out at " R " angle of root.Heat shield 3 covers radial connection with half below spherical crown housing 1.Heat shield 3 has two, arranges along spherical crown housing 1 axisymmetrical.The thickness of heat shield 3 is 10mm.Heat shield 3 rectified actions.
Arc connection box 5 entirety is arc tabular, and cross section is " L " shape.Arc connection box 5 has two, and the joint face covered along spherical crown housing about 1 two and half is symmetrical arranged.The arc connection box 5 of top and above spherical crown housing 1 half covers radial connection; The arc connection box 5 of below covers with half below spherical crown housing 1 respectively and the bottom radial direction of deep bead 2 is connected.Arc connection box 5 cross section is of a size of 30 × 40mm, and wall thickness is 5mm.Arc connection box 5, for playing a supportive role to spherical crown housing 1, increases structural strength simultaneously.
Rubber gasket 4 is fixedly connected on the upper surface of the arc connection box 5 of below, is compressed by the arc connection box 5 of the arc connection box 5 of top and below.The thickness of rubber gasket 4 is 5 ~ 6mm.Rubber gasket 4, for closing the space between two arc connection boxes 5, plays the effect of solar heat protection and sealing.
End cap underframe 6 entirety is annular, and cross section is " L " shape.The left part of end cap underframe 6 is fixed on the right-hand member of spherical crown housing 1.The wall thickness of end cap underframe 6 is 5mm.End cap underframe 6 is for strengthening the circumferential strength of spherical crown housing 1.
In the present embodiment, the high silicone/phenolic resin resin bed pressing glass steel material that spherical crown housing 1, deep bead 2 and heat shield 3 all adopt solar heat protection effective is made; Arc connection box 5 and end cap underframe 6 all adopt 2A14 material to make, and when ensureing structural strength, at utmost reduce the overall weight of structure.
The utility model comprises spherical crown housing 1, deep bead 2, heat shield 3, rubber gasket 4, arc connection box 5 and end cap underframe 6.Compared with rocket body similar structures in the past, the utility model has the advantage of.Can meet the thermal force environmental requirement of large external pressure, the greatly distinctive Solid Launch Vehicle of hot-fluid load, structure is relatively simple simultaneously, and technique realizability is strong.
Have passed through engineering and finite element stimulation in radome fairing end cap and heat seal structure development process, experienced by the examination of hot bearing test and wind tunnel test and be finally applied in Solid Launch Vehicle type product.
Ground experiment demonstrates end cap thermal protective performance and meets design objective requirement, and verification experimental verification effect is as follows:
A) its anti-thermal effect is verified by the hot bearing test of radome fairing.It is about 170 DEG C that test records end cap inwall maximum temperature, and structural strength and rigidity meet instructions for use at such a temperature.End cap overall thermal protection effect is better, meets design requirement.
B) by the heat seal effect of the hot bearing test verifying end head cap of radome fairing.Do not find in process of the test and after off-test to form leakage path at end cap half cover joint, demonstrate the validity of heat seal measure.
Hot bearing test verification experimental verification radome fairing end cap meets overall anti-protective hot and heat sealability instructions for use, and radome fairing localized heat safeguard structure successfully reaches its development object.
Claims (8)
1. a radome fairing end cap heat seal structure, is characterized in that: it comprises spherical crown housing (1), deep bead (2), heat shield (3), rubber gasket (4), arc connection box (5) and end cap underframe (6); Deep bead (2) is fixed on the outer surface of spherical crown housing (1); Heat shield (3) is positioned at the two ends of deep bead (2), is fixedly connected with spherical crown housing (1); Arc connection box (5) is arranged on the inner surface of the spherical crown housing (1) corresponding with deep bead (2), and arc connection box (5) is fixedly connected with deep bead with spherical crown housing (1) respectively; Rubber gasket (4) is positioned at the inside of arc connection box (5); End cap underframe (6) is fixedly connected on the aperture position of spherical crown housing (1).
2. radome fairing end cap heat seal structure according to claim 1, is characterized in that: described spherical crown housing (1) entirety is the segment structure of hollow, and opening, is divided into laterally zygomorphic two and half covers to the right; Radius of a ball SR is 441mm, and the distance of segment vertex position distance right-end openings is 320mm.
3. radome fairing end cap heat seal structure according to claim 2, is characterized in that: described deep bead (2) entirety is circular arc tabular, and cross section is step, and the height of left part cross section is greater than the height of right part cross section; Deep bead (2) is arranged on the connecting portion of upper and lower two and half covers of spherical crown housing (1), cover respectively and arc connection box (5) is radial is connected with half of spherical crown housing (1) below; The thickness of deep bead (2) is 10mm.
4. radome fairing end cap heat seal structure according to claim 3, it is characterized in that: described heat shield (3) is overall has the rectangular plate-like structure at " R " angle for root, and the right-end openings of spherical crown housing (1) is stretched out at " R " angle of root; Heat shield (3) covers radial connection with half of spherical crown housing (1) below; Heat shield (3) has two, arranges along spherical crown housing (1) axisymmetrical; The thickness of heat shield (3) is 10mm.
5. radome fairing end cap heat seal structure according to claim 4, is characterized in that: described arc connection box (5) entirety is arc tabular, and cross section is " L " shape; Arc connection box (5) has two, and the joint face along upper and lower two and half covers of spherical crown housing (1) is symmetrical arranged; The arc connection box (5) of top covers radial connection with half of spherical crown housing (1) top; The arc connection box (5) of below covers with half of spherical crown housing (1) below respectively and the bottom radial direction of deep bead (2) is connected; Arc connection box (5) cross section is of a size of 30 × 40mm, and wall thickness is 5mm.
6. radome fairing end cap heat seal structure according to claim 5, it is characterized in that: described rubber gasket (4) is fixedly connected on the upper surface of the arc connection box (5) of below, compressed by the arc connection box (5) of the arc connection box (5) of top and below; The thickness of rubber gasket (4) is 5 ~ 6mm.
7. radome fairing end cap heat seal structure according to claim 6, is characterized in that: described end cap underframe (6) entirety is annular, and cross section is " L " shape; The left part of end cap underframe (6) is fixed on the right-hand member of spherical crown housing (1); The wall thickness of end cap underframe (6) is 5mm.
8. radome fairing end cap heat seal structure according to claim 1, is characterized in that: described spherical crown housing (1), deep bead (2) and heat shield (3) all adopt high silicone/phenolic resin resin bed pressing glass steel material to make; Arc connection box (5) and end cap underframe (6) all adopt 2A14 material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520399215.5U CN204788078U (en) | 2015-06-10 | 2015-06-10 | Hot seal structure of radome fairing end cap |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520399215.5U CN204788078U (en) | 2015-06-10 | 2015-06-10 | Hot seal structure of radome fairing end cap |
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| CN204788078U true CN204788078U (en) | 2015-11-18 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468846A (en) * | 2015-11-24 | 2016-04-06 | 北京宇航系统工程研究所 | Method for determining bottom heat flow of rocket by radiation form factor |
| CN110104224A (en) * | 2019-04-22 | 2019-08-09 | 北京零壹空间技术研究院有限公司 | Blocking component, radome fairing and aircraft |
| CN110341988A (en) * | 2019-07-24 | 2019-10-18 | 天津爱思达航天科技有限公司 | A kind of radome fairing and aerospace craft |
| CN110676799A (en) * | 2019-08-27 | 2020-01-10 | 江西洪都航空工业集团有限责任公司 | Sealing structure of cabin section cable fairing |
-
2015
- 2015-06-10 CN CN201520399215.5U patent/CN204788078U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468846A (en) * | 2015-11-24 | 2016-04-06 | 北京宇航系统工程研究所 | Method for determining bottom heat flow of rocket by radiation form factor |
| CN105468846B (en) * | 2015-11-24 | 2019-01-11 | 北京宇航系统工程研究所 | A method of rocket bottom hot-fluid is determined using RADIATION ANGLE COEFFICIENT |
| CN110104224A (en) * | 2019-04-22 | 2019-08-09 | 北京零壹空间技术研究院有限公司 | Blocking component, radome fairing and aircraft |
| CN110104224B (en) * | 2019-04-22 | 2021-07-30 | 北京零壹空间技术研究院有限公司 | Plugging assembly, fairing and aircraft |
| CN110341988A (en) * | 2019-07-24 | 2019-10-18 | 天津爱思达航天科技有限公司 | A kind of radome fairing and aerospace craft |
| CN110676799A (en) * | 2019-08-27 | 2020-01-10 | 江西洪都航空工业集团有限责任公司 | Sealing structure of cabin section cable fairing |
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