CN113022842B - High-temperature-resistant high-bearing foldable air rudder - Google Patents
High-temperature-resistant high-bearing foldable air rudder Download PDFInfo
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- CN113022842B CN113022842B CN202110324936.XA CN202110324936A CN113022842B CN 113022842 B CN113022842 B CN 113022842B CN 202110324936 A CN202110324936 A CN 202110324936A CN 113022842 B CN113022842 B CN 113022842B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a high-temperature-resistant high-bearing foldable air rudder which comprises a rudder surface and a rudder shaft, and is characterized in that: the control surface comprises a fixed control surface, a movable control surface, a front edge and a heat-proof sleeve, the fixed control surface is fixed on the control shaft, the movable control surface is rotatably connected with the fixed control surface through a rotating shaft, the heat-proof sleeve is arranged on the movable control surface, and the front edge is arranged in the movable control surface; and heat-proof coatings are also arranged on the movable control surface and the fixed control surface. The foldable air rudder can meet the requirements of high-Mach aircraft on pneumatic and thermal loads, and provides support for improving the operational efficiency of the aircraft, so that the foldable air rudder has high popularization value and commercial value.
Description
Technical Field
The invention relates to the technical field of air rudders, in particular to a high-temperature-resistant high-bearing foldable air rudder.
Background
In order to improve the operational efficiency of the weapon platform, realize carrying more missiles as far as possible in a limited space and meet the flight mobility requirements of the missiles, the scheme of adopting supersonic speed to unfold the foldable air rudder is a necessary choice. In addition, the research of aircrafts in China has fully entered the super-sonic age.
As a key component for flight attitude adjustment, foldable air rudders are subjected to their severe aerodynamic and thermal loads during hypersonic flight. How to improve the adaptability of control surface to super high temperature environment through optimizing collapsible air vane structural design scheme, promote bearing capacity under the collapsible air vane thermodynamic coupling condition, reinforcing control surface rigidity intensity avoids fluttering in order to satisfy the transmission demand of big airspace supersonic speed is the key problem that awaits a moment to be solved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the high-temperature-resistant high-bearing-capacity foldable air rudder is provided to solve the problems that the conventional air rudder has general bearing capacity, general rudder surface strength and poor high-temperature-resistant performance.
The technical scheme adopted by the invention is as follows: the utility model provides a collapsible air rudder is born to high temperature resistant height, includes rudder face and rudder axle, its characterized in that: the control surface comprises a fixed control surface, a movable control surface, a front edge and a heat-proof sleeve, the fixed control surface is fixed on the control shaft, the movable control surface is rotatably connected with the fixed control surface through a rotating shaft, the heat-proof sleeve is arranged on the movable control surface, and the front edge is arranged in the movable control surface; and heat-proof coatings are also arranged on the movable control surface and the fixed control surface.
As a preferred scheme, the movable rudder surface comprises a metal framework, the metal framework is a reinforcing rib structure with a hollow inner part, and the reinforcing rib structure is favorable for reducing the weight of the foldable air rudder and enhancing the rigidity of the foldable air rudder.
As a preferable scheme, the heat-proof sleeve is a high-silica phenolic short-cut composite material, and the overall heat-proof performance of the air rudder can be greatly improved by adopting the high-silica phenolic short-cut composite material as the heat-proof sleeve.
As a preferable scheme, the high-silica phenolic short-cut composite material heat-proof sleeve is formed by filling the high-silica phenolic short-cut composite material on the movable rudder surface and curing the high-silica phenolic short-cut composite material after prepressing, and the foldable air rudder surface cannot be completely filled with the high-silica phenolic short-cut composite material due to the fact that folding needs high matching precision, so that the high-silica phenolic short-cut composite material heat-proof sleeve and the heat-proof coating are combined, and the high-temperature resistance of the foldable air rudder is improved.
Preferably, the front edge is fixed inside the fixed control surface in a riveting mode, the front edge can be detached through riveting installation, and the installation strength is high.
Preferably, the front edge is made of a C/SiC composite material, and the thermal environment of the front end of the air rudder changes frequently and the temperature is relatively high, so that the C/SiC composite material front edge is installed at the position of the front edge of the foldable air rudder to adapt to the thermal environment with a complex front edge, and the heat resistance of the whole air rudder is further improved.
Preferably, the heat-proof coating is arranged on the outer surface of the movable control surface which is not covered by the heat-proof sleeve and the rotating shaft, and the fixed control surface also has a part which is not covered by the heat-proof sleeve, so that the heat-proof coating is sprayed on the part which is protected by the heat-proof sleeve, the whole heat-proof performance can be enhanced, the deformation of the part which is not covered by the heat-proof sleeve due to high temperature can be prevented, the heat-proof coating is also sprayed on the rotating shaft, and the problem that high-temperature high-speed airflow flows into a folding gap when the rotating shaft is partially folded and unfolded in the rotating process can be fully prevented.
Preferably, the heat-proof coating is a zirconium oxide coating or a coating formed by combining zirconium oxide and a high-radiation coating, and the control surface can be effectively subjected to heat protection by adopting the zirconium oxide coating or the coating formed by combining zirconium oxide and the high-radiation coating.
Compared with the prior art, the invention has the beneficial effects that: the high-temperature-resistant high-bearing foldable air rudder provided by the invention adopts a mode of combining the front edge of a C/SiC composite material, the heat-proof sleeve of a high-silica phenolic aldehyde chopped composite material and the heat-proof coating, so that the air rudder can bear the thermal load and the aerodynamic load above the flight speed of Mach 9, and the foldable air rudder can keep an excellent aerodynamic shape in a high-Mach number flight environment. The air rudder has the advantages of simple structure, different protection of each part, excellent heat resistance and better structural rigidity. The traditional single heat-proof sleeve structure or the zirconia coating structure can only adapt to a high-temperature environment of 1200 ℃, and the heat-proof structure provided by the invention can meet the high-temperature environment of 2600 ℃, so that the effect is obviously improved, and the heat-proof structure has higher commercial value and popularization value.
Drawings
FIG. 1 is a structural view of a high temperature resistant high load bearing foldable air rudder of the present invention;
FIG. 2 is a structural view of the high temperature resistant, high load bearing foldable air rudder of the present invention with the heat shroud skin and the heat shroud coating removed;
FIG. 3 is a cross-sectional view of a high temperature resistant, high load bearing foldable air vane of the present invention;
wherein: 1. a control surface is fixed; 2. a movable rudder surface; 3. a heat-proof sleeve; 4. a leading edge; 5. a heat resistant coating; 6. a rudder shaft; 7. a rotating shaft.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The above and further features and advantages of the present invention are described in more detail below with reference to the accompanying drawings.
As shown in fig. 1 and fig. 2, fig. 1 is a structural view of the high temperature resistant high load-bearing foldable air rudder, and fig. 2 is a structural view of the high temperature resistant high load-bearing foldable air rudder with the high silica phenolic chopped composite heat shield jacket skin and the heat shield coating removed. The high-temperature-resistant high-bearing foldable air rudder comprises a fixed rudder surface 1, a movable rudder surface 2, a heat-proof sleeve 3, a front edge 4, a heat-proof coating 5, a rudder shaft 6 and a rotating shaft 7. The fixed control surface 1 is fixed on the control shaft 6, so that the connection between the foldable air rudder and the aircraft is realized. Move rudder face metal framework 2 and decide rudder face 1 and link to each other through the pivot, heat-proof cover 3 passes through the inside high silica of packing of metal framework of moving rudder face 2 is chopped the combined material pre-compaction and it forms to move the metal framework surface of rudder face 2 and pack the short combined material solidification back of high silica, the leading edge 4 that the C/SiC combined material made is installed in the complicated hot environment of front edge of air rudder is in order to adapt to on the 4 positions of leading edge of collapsible air rudder, the 5 spraying of heat protection coating is in decide rudder face 1 and move rudder face 2 not add the surface of heat-proof cover 3 protects deciding rudder face 1 and moving rudder face 2.
In order to reduce the weight of the foldable air rudder, reduce the thickness of the air rudder and reduce the flight resistance of the air rudder during flight, the metal framework 2 of the movable rudder surface adopts a hollow rib beam structure, as shown in fig. 2. In addition, the strength and rigidity of the foldable air rudder can be ensured by adopting the metal framework 2 of the movable rudder surface so as to adapt to the aerodynamic load of high Mach number flight and inhibit the flutter in the flight process. The rib beam structure provided by the invention can be adjusted according to the flight environment requirement, and is not limited to the rib beam structure shown by the invention.
As shown in fig. 2 and fig. 3, the high silica phenolic short-cut composite material is filled in the blank position of the metal framework of the movable control surface 2, the blank position is put into a die for prepressing and trimming, then the high silica phenolic short-cut composite material is filled on the outer surface of the metal framework of the movable control surface 2 and then is cured and formed to form the heat-proof sleeve 3 made of the high silica phenolic short-cut composite material, the heat-proof coating 5 is sprayed on the outer surface of the metal framework of the movable control surface 2 which is not filled with the high silica phenolic short-cut composite material, the front edge position adopts a mortise and tenon structure to connect the control surface with the front edge 4 of the C/SiC composite material to form the heat-proof structure of the metal framework of the movable control surface 2, and the metal framework of the movable control surface 2 can adapt to the high-mach-number flight load and the heat load of the aircraft.
The surface of the fixed control surface 1 is sprayed with a heat-proof coating 5, and the front edge position adopts a mortise and tenon joint structure to connect the control surface with the front edge 4 of the C/SiC composite material, so that the heat-proof structure of the fixed control surface is formed.
In order to ensure the reliability of the foldable air rudder in the unfolding and folding process, the position of a rotating shaft (shown in figure 1) needs higher precision, and because a folding gap exists between the metal frameworks of the fixed control surface 1 and the movable control surface 2 of the foldable air rudder, high-speed airflow enters the gap, the connection parts of the metal frameworks of the fixed control surface 1 and the movable control surface 2 through the rotating shaft 7 need heat-proof treatment. The high-silica phenolic short-cut composite material heat-proof sleeve is difficult to meet the folding precision requirement of the position of the rotating shaft, so that the invention provides a heat-proof structural form combining the high-silica phenolic short-cut composite material heat-proof sleeve 3 and the heat-proof coating 5, and the heat-proof coating is sprayed on the rotating shaft, thereby meeting the heat-proof requirement of the foldable air rudder and the reliability requirements of folding and unfolding, and ensuring the reliability of the service process of the foldable air rudder.
Under the high-Mach flight condition of the aircraft, the front edge of the foldable air rudder is obviously pneumatically heated, the temperature of the front edge can reach more than 2000 ℃, and the traditional heat-proof means is difficult to meet. Therefore, the front edge of the invention adopts the front edge 4 made of the C/SiC composite material, the front edge 4 of the C/SiC composite material, the high-silica phenolic short-cut composite material heat-proof sleeve 1 and the heat-proof coating 5 are combined to form the heat-proof structure shown in figure 1, and the traditional single heat-proof sleeve structure or zirconia coating structure can only adapt to the high-temperature environment of 1200 ℃.
The foregoing is merely a preferred embodiment of the invention, which is intended to be illustrative and not limiting. It will be understood by those skilled in the art that various changes, modifications and equivalents may be made therein without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (3)
1. The utility model provides a high temperature resistant high collapsible air rudder that bears, includes rudder face and rudder axle, its characterized in that: the control surface includes decide the control surface, moves control surface, leading edge and heat-proof cover, decide the control surface and fix on the steering spindle, just move between control surface and the deciding control surface through a pivot swivelling joint, the heat-proof cover sets up on moving the control surface, the leading edge sets up in moving the control surface, it includes a metal framework to move the control surface, just metal framework is inside hollow strengthening rib structure, and the short combined material of high silica phenolic aldehyde fills in the blank position of moving control surface metal framework, puts into the mould and pre-compaction is repaiied, and the short combined material of high silica phenolic aldehyde fills the postcure shaping at the metal framework surface of moving the control surface afterwards, forms the heat-proof cover of the short combined material of high silica, the leading edge is made for C SiC combined material, still be provided with the heat-proof coating on moving control surface and deciding the control surface, the heat-proof coating sets up on moving the surface and the pivot that the control surface was not covered by the heat-proof cover.
2. The high temperature and high load bearing foldable air rudder as claimed in claim 1, wherein: the front edge is fixed inside the fixed control surface in a riveting mode.
3. The high temperature and high load bearing foldable air rudder as claimed in claim 1, wherein: the heat-proof coating is a zirconium oxide coating or a coating formed by combining zirconium oxide and a high-radiation coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110324936.XA CN113022842B (en) | 2021-03-26 | 2021-03-26 | High-temperature-resistant high-bearing foldable air rudder |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110324936.XA CN113022842B (en) | 2021-03-26 | 2021-03-26 | High-temperature-resistant high-bearing foldable air rudder |
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| CN113022842A CN113022842A (en) | 2021-06-25 |
| CN113022842B true CN113022842B (en) | 2023-03-17 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113720217B (en) * | 2021-07-23 | 2023-04-14 | 河北汉光重工有限责任公司 | Be applied to thermal-insulated folding rudder of hypersonic flight |
| CN117521290A (en) * | 2023-11-21 | 2024-02-06 | 西安现代控制技术研究所 | Low-resistance non-ablative hypersonic folded rudder calculation method and structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108995792B (en) * | 2018-07-30 | 2020-04-24 | 上海机电工程研究所 | Air rudder with composite material structure |
| US11293729B2 (en) * | 2019-01-31 | 2022-04-05 | Saab Ab | Rudder control assembly for a missile |
| CN210707966U (en) * | 2019-04-22 | 2020-06-09 | 北京零壹空间技术研究院有限公司 | Air rudder and rocket |
| CN110877712A (en) * | 2019-12-02 | 2020-03-13 | 北京电子工程总体研究所 | Folding clearance adjusting device of folding control surface |
| CN110901885B (en) * | 2019-12-23 | 2021-11-30 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN112361894B (en) * | 2020-10-12 | 2022-05-31 | 中国运载火箭技术研究院 | Air rudder for rocket |
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Effective date of registration: 20220810 Address after: 315336 No. 8, Lane 422, Xingci 1st Road, Hangzhou Bay New Area, Ningbo City, Zhejiang Province Applicant after: Ningbo Zhongke Xianglong Lightweight Technology Co.,Ltd. Address before: 315201, No. 519, Zhuang Avenue, Zhenhai District, Zhejiang, Ningbo Applicant before: NINGBO INSTITUTE OF MATERIALS TECHNOLOGY & ENGINEERING, CHINESE ACADEMY OF SCIENCES |
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Denomination of invention: A high-temperature resistant and high load-bearing foldable air rudder Effective date of registration: 20230814 Granted publication date: 20230317 Pledgee: Zhejiang Tailong Commercial Bank Co.,Ltd. Ningbo Hangzhou Bay New Area Sub branch Pledgor: Ningbo Zhongke Xianglong Lightweight Technology Co.,Ltd. Registration number: Y2023980051979 |