CN202944563U - Wing body connecting layer type embedding structure of silicon substrate heat proof layer for hypersonic flight vehicle - Google Patents
Wing body connecting layer type embedding structure of silicon substrate heat proof layer for hypersonic flight vehicle Download PDFInfo
- Publication number
- CN202944563U CN202944563U CN 201220540192 CN201220540192U CN202944563U CN 202944563 U CN202944563 U CN 202944563U CN 201220540192 CN201220540192 CN 201220540192 CN 201220540192 U CN201220540192 U CN 201220540192U CN 202944563 U CN202944563 U CN 202944563U
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- wing
- heat shield
- heat proof
- proof layer
- cone body
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Abstract
The utility model belongs to a wing body connecting structure of a flight device, and in particular discloses a wing body connecting layer type embedding structure of a silicon substrate heat proof layer for a hypersonic flight vehicle. The structure comprises a wing heat proof layer, a wing metal structure, a metal framework and a cone heat proof layer. The wing heat proof layer is arranged outside the wing metal structure, the cone heat proof layer is arranged outside the metal framework, and the wing heat proof layer is arranged inside the cone heat proof layer. The connecting structure provided by the utility model can be used for preventing the wing front tip of the wing metal structure from warping to from a sharp stagnation point and overcoming the severe problem that the wing body connection which is not protected by the heat proof layer is directly invaded by hot air flows.
Description
Technical field
The utility model belongs to aircraft wings body connection structure, is specifically related to the silica-based heat shield wing of a kind of hypersonic aircraft body and connects the laminar embedded structure.
Background technology
Aircraft for a long time at close to space vehicle, compare with conventional aircraft its Aerodynamic Heating environment exist the hot-fluid peak value on the low side (approximately tradition reenter the formula bullet 1/5), in low hot-fluid longer duration (being more than 10 times of traditional bullet), always add the large characteristics of heat.
There was comparatively serious distortion in widely used silica-based heat shield under this environment in the past; if use traditional wing body connection structure, uncontrollable ablation, the wing body junction that this kind distortion may cause the wing paracone warpage of wing metal construction to form sharp-pointed stationary point is not subjected to the heat shield protection directly by serious problems such as thermal current invasion and attack.
Summary of the invention
The purpose of this utility model is to provide the silica-based heat shield wing of a kind of hypersonic aircraft body to connect the laminar embedded structure; this structure can prevent that the wing paracone warpage of wing metal construction from forming sharp-pointed stationary point, can prevent that wing body junction is due to the serious problems that not directly attacked by thermal current by the heat shield protection.
The technical matters that solves is: overcome existing wing body connection structure and can not be applicable to the silica-based heat shield horizontal tail of hypersonic aircraft and the situation that silica-based heat shield cone body is connected, propose a kind of silica-based heat shield wing body and connect the laminar embedded structure.
Realize the technical scheme of the utility model purpose: the silica-based heat shield wing of a kind of hypersonic aircraft body connects the laminar embedded structure, it comprises wing heat shield, wing metal construction, cone body metallic framework, cone body heat shield, wing metal construction is provided with wing heat shield outward, cone body metallic framework is provided with cone body heat shield outward, and wing heat shield is embedded in cone body heat shield.
The boss of described wing metal construction is positioned at the through hole of wing heat shield, cone body heat shield, and the boss of wing metal construction is captiveed joint with cone body metallic framework.
Captive joint by wing body tie bolt between described wing metal construction and cone body metallic framework.
The utility model compared with prior art beneficial effect is:
(1) the utility model adopts wing heat shield to be embedded in the interior laminar embedded structure of cone body heat shield, and actv. has avoided the wing paracone warpage of wing metal construction to form the uncontrollable ablation in sharp-pointed stationary point.
(2) the utility model actv. has avoided wing metal construction to connect embedded location directly by thermal current invasion and attack problem.
Description of drawings
Fig. 1 is that the silica-based heat shield wing of a kind of hypersonic aircraft provided by the utility model body connects the laminar embedded structure.
Fig. 2 is that the A-A of Fig. 1 is to cutaway view.
In figure: 1. wing heat shield, 2. wing metal construction, 3. cone body metallic framework, 4. cone body heat shield, 5. wing body tie bolt.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail.
As shown in Figure 1, aircraft wings metal construction 2 is muscle fine strain of millet covering unitized construction, and aircraft cone body metal construction 3 is the thin wall cone with reinforced rib.Wing heat shield 1 is the direct combination moulding on aircraft wings metal construction 2, cone body heat shield 4 direct combination moulding on cone body metallic framework 3.
As shown in Figure 1, wing heat shield 1 is embedded in cone body heat shield 4, and wing heat shield 1 and cone body heat shield 4 are silicon based fiber and strengthen resin matrix composite, and wing heat shield 1 is the variable-cross-section special shaped structure of class triangle along the axial section of cone body metallic framework 3.The size h that wing heat shield 1 is embedded in cone body heat shield 4 gets 5 ~ 10mm usually.
As depicted in figs. 1 and 2, two boss of wing metal construction 2 pass two through holes of wing heat shield 1 separately, and are embedded in bottom the connection boss of wing metal construction 2 in cone body heat shield 4, cone body metal construction 3.Cone body heat shield 4 covers on cone body metal construction, and wing body tie bolt 5 is fixed together wing metal construction 2, cone body metal construction 3, thereby wing heat shield 1, cone body heat shield 4 are fastened between wing metal construction 2 and cone body metal construction 3.
As depicted in figs. 1 and 2, wing metal construction 2 is connected with cone body metallic framework 3, and wing heat shield 1, cone body heat shield 4 are fastened between wing metal construction 2 and cone body metal construction 3, the bearing capacity to wing integral body can either be provided, the wing paracone warpage that can prevent wing metal construction 2 is arranged simultaneously.
As shown in Figure 1, the damascene structures that is connected to of wing heat shield 1 and cone body heat shield 4, this damascene structures can ensure that in the aircraft flight situation, high-enthalpy flow can't be attacked connecting portion, blocks simultaneously the passage that air-flow enters capable device cabin body.This damascene structures guaranteed in the wing paracone of low hot-fluid, long-time environment bottom wing metal construction 2 can not form sharp-pointed stationary point because of distortion; Guaranteed simultaneously when reaching of wing metal construction 2 bored 4 contraction of body heat shield, wing heat shield 1 can directly not attacked by thermal current with the embedded location of cone body heat shield 4.
The above has done detailed description to the utility model in conjunction with the accompanying drawings and embodiments, but the utility model is not limited to above-described embodiment, in the ken that those of ordinary skills possess, can also make various variations under the prerequisite that does not break away from the utility model aim.The content that is not described in detail in the utility model all can adopt prior art.
Claims (3)
1. the silica-based heat shield wing of a hypersonic aircraft body connects the laminar embedded structure, it is characterized in that: it comprises wing heat shield (1), wing metal construction (2), cone body metallic framework (3), cone body heat shield (4), the outer wing heat shield (1) that is provided with of wing metal construction (2), the outer cone body heat shield (4) that is provided with of cone body metallic framework (3), wing heat shield (1) is embedded in cone body heat shield (4).
2. the silica-based heat shield wing of a kind of hypersonic aircraft according to claim 1 body connects the laminar embedded structure, it is characterized in that: the boss of described wing metal construction (2) is positioned at the through hole of wing heat shield (1), cone body heat shield (4), and the boss of wing metal construction (2) is captiveed joint with cone body metallic framework (3).
3. the silica-based heat shield wing of a kind of hypersonic aircraft according to claim 1 body connects the laminar embedded structure, it is characterized in that: described wing metal construction (2) is captiveed joint by wing body tie bolt (5) with boring between body metallic framework (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220540192 CN202944563U (en) | 2012-10-22 | 2012-10-22 | Wing body connecting layer type embedding structure of silicon substrate heat proof layer for hypersonic flight vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220540192 CN202944563U (en) | 2012-10-22 | 2012-10-22 | Wing body connecting layer type embedding structure of silicon substrate heat proof layer for hypersonic flight vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202944563U true CN202944563U (en) | 2013-05-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220540192 Expired - Lifetime CN202944563U (en) | 2012-10-22 | 2012-10-22 | Wing body connecting layer type embedding structure of silicon substrate heat proof layer for hypersonic flight vehicle |
Country Status (1)
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| CN (1) | CN202944563U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173053A (en) * | 2015-09-21 | 2015-12-23 | 北京临近空间飞行器系统工程研究所 | Connection structure for all carbon-carbon composite material wing |
| CN107031812A (en) * | 2017-03-30 | 2017-08-11 | 北京临近空间飞行器系统工程研究所 | It is a kind of to meet aerodynamic arrangement's design method that hypersonic big angle of attack horizontal stroke is laterally controlled |
| CN107380395A (en) * | 2017-06-28 | 2017-11-24 | 湖北航天技术研究院总体设计所 | A kind of anti-heat-insulation integrative wing attachment structure |
-
2012
- 2012-10-22 CN CN 201220540192 patent/CN202944563U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173053A (en) * | 2015-09-21 | 2015-12-23 | 北京临近空间飞行器系统工程研究所 | Connection structure for all carbon-carbon composite material wing |
| CN105173053B (en) * | 2015-09-21 | 2017-05-17 | 北京临近空间飞行器系统工程研究所 | Connection structure for all carbon-carbon composite material wing |
| CN107031812A (en) * | 2017-03-30 | 2017-08-11 | 北京临近空间飞行器系统工程研究所 | It is a kind of to meet aerodynamic arrangement's design method that hypersonic big angle of attack horizontal stroke is laterally controlled |
| CN107031812B (en) * | 2017-03-30 | 2019-08-09 | 北京临近空间飞行器系统工程研究所 | A kind of aerodynamic arrangement's design method for meeting hypersonic big angle of attack cross and laterally controlling |
| CN107380395A (en) * | 2017-06-28 | 2017-11-24 | 湖北航天技术研究院总体设计所 | A kind of anti-heat-insulation integrative wing attachment structure |
| CN107380395B (en) * | 2017-06-28 | 2020-05-19 | 湖北航天技术研究院总体设计所 | Prevent thermal-insulated integration wing connection structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130522 |