CN114030589A - Light high-efficiency thermal-resistance air rudder - Google Patents
Light high-efficiency thermal-resistance air rudder Download PDFInfo
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- CN114030589A CN114030589A CN202111215643.4A CN202111215643A CN114030589A CN 114030589 A CN114030589 A CN 114030589A CN 202111215643 A CN202111215643 A CN 202111215643A CN 114030589 A CN114030589 A CN 114030589A
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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 application relates to the technical field of aerospace, in particular to a light high-efficiency thermal-resistance air rudder. The light high-efficiency thermal resistance air rudder comprises a rudder shaft, a rudder shaft and a heat exchanger, wherein the inside of the rudder shaft is of a hollow structure, and the rudder shaft is made of titanium alloy, high-temperature alloy or alloy steel; the rudder body is fixedly connected with a rudder shaft, a heat-proof layer and a rudder core are arranged in the rudder body, the heat-proof layer is made of fiber reinforced resin matrix composite materials and zirconia ceramics or alumina ceramics, the rudder core comprises a connecting plate and a rudder framework, the connecting plate is connected between the heat-proof layer and the rudder framework, the connecting plate is of an I-shaped structure with a hollow interior, and the rudder framework is formed by connecting a plurality of framework ribs. The application provides an air vane has the quality light, bears the weight of big, the reliability is high, the structure utilization ratio is high, the excellent characteristics of heat-proof quality.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a light high-efficiency thermal-resistance air rudder.
Background
The air rudder is an important component for controlling the flight direction and the attitude of the aircraft, is positioned at the tail of the aircraft, and changes the attitude of the aircraft by changing the airflow of a control surface. As aircraft flight speed and flight time increase, aerodynamic heat becomes more and more severe, causing air rudder temperature to rise and structural strength and stiffness to decrease. Therefore, the air rudder is generally required to have the characteristics of high temperature resistance, ablation resistance and thermal flutter resistance, and to have excellent high-temperature strength and rigidity.
Most air rudders are made of metal structures and generally comprise a rudder shaft, a rudder core (a framework rib and an I-shaped plate), a heat-proof layer and the like, wherein the rudder shaft and the rudder core are used for bearing bending moment and torque of the rudder, and the heat-proof layer is used for isolating and consuming aerodynamic heat. The air vane manufactured by the traditional process such as machining, casting and the like has the problems of large structural weight, large ineffective mass, low structural utilization rate, poor heat insulation performance and the like. Therefore, it is necessary to provide an air vane having light weight and excellent heat insulation performance.
Disclosure of Invention
The embodiment of the application provides a high-efficient thermal resistance air vane of light, and this air vane has the quality light, bears the weight of big, the reliability is high, structure utilization is high, the excellent characteristics of heat-proof quality.
The application provides a high-efficient thermal resistance air vane of light includes:
the inner part of the rudder shaft is of a hollow structure, and the rudder shaft is made of titanium alloy, high-temperature alloy or alloy steel;
the rudder body is fixedly connected with a rudder shaft, a heat-proof layer and a rudder core are arranged in the rudder body, the heat-proof layer is made of fiber reinforced resin matrix composite materials and zirconia ceramics or alumina ceramics, the rudder core comprises a connecting plate and a rudder framework, the connecting plate is connected between the heat-proof layer and the rudder framework, the connecting plate is of an I-shaped structure with a hollow interior, and the rudder framework is formed by connecting a plurality of framework ribs.
In some embodiments, the connection mode of the rudder body and the rudder shaft is welding, rivet connection or screw connection.
In some embodiments, the rudder body and the rudder shaft are integrally formed by casting or 3D printing.
In some embodiments, the rudder body is made of titanium alloy, high-temperature alloy, alloy steel or aluminum alloy.
In some embodiments, the surface of the framework rib is provided with a groove, the cross section of the framework rib is I-shaped, the invalid quality can be effectively reduced by adopting the I-shaped framework rib, and the bearing utilization rate of the structure is improved.
In some embodiments, a through hole is formed in the middle of the groove, and the quality of the air rudder can be further reduced by forming the through hole in the middle of the groove.
In some embodiments, adjacent framework ribs are connected to form a triangular structure, and the framework ribs are arranged in a'm' -shaped manner to meet the distribution of a BP network. The triangular structure is favorable for the stable structure of the air rudder, and the rigidity and the vibration resistance are improved.
In some embodiments, the thickness of the skeleton rib is gradually reduced along the direction far away from the rudder shaft, and the skeleton ribs with different thicknesses are adopted to facilitate the reduction of the mass of the air rudder and improve the structural utilization efficiency.
In some embodiments, the thickness of the skeletal ribs gradually decreases from 10mm to 2 mm.
In some embodiments, the fiber reinforced resin based composite material is composed of a fiber weave woven from quartz fibers, carbon fibers, basalt fibers, boron fibers, alumina fibers, silicon carbide fibers, or silicon nitride fibers, and a resin that is a phenolic resin or a polyimide resin.
In some embodiments, the connection plate and the rudder skeleton are made of titanium alloy, high-temperature alloy, alloy steel or aluminum alloy.
In some embodiments, the surface of the connecting plate and the outer side of the rudder shaft are sprayed with thermal insulation coatings. In some preferred embodiments, the thermal barrier coating is a zirconia ceramic thermal barrier coating.
In some embodiments, an S-shaped pipe is arranged inside the rudder shaft, the number of the S-shaped pipe is 3-8, and water or fuel oil can be injected into the S-shaped pipe to reduce the temperature of the rudder shaft.
In some embodiments, the rudder skeleton is manufactured by machining, casting or 3D printing.
In some embodiments, the connection mode of the connection plate and the rudder skeleton is welding, rivet connection or screw connection.
In some embodiments, the connecting plate and the rudder skeleton are integrally formed by 3D printing.
The beneficial effect that technical scheme that this application provided brought includes: the air vane provided by the application adopts the fiber reinforced resin matrix composite material, the zirconia ceramic or the alumina ceramic as the material of the heat-proof layer, not only can ablation be prevented, but also the air vane has better heat-proof and heat-insulating properties, and the vane core is effectively protected from being ablated by high temperature; this application adopts hollow I shape connecting plate to connect heat protection layer and rudder skeleton, not only can separate the transfer of rudder face aerodynamic heat effectively, can alleviate the air vane quality moreover.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a lightweight, efficient, and thermal resistance air rudder provided in embodiment 1 of the present application;
fig. 2 is a schematic transverse cross-sectional view of a rudder shaft of an air rudder provided in embodiment 1 of the present application;
fig. 3 is a cross-sectional view of a skeletal rib of an air rudder according to embodiment 1 of the present application;
fig. 4 is a schematic structural view of a skeleton rib of an air rudder provided in embodiment 1 of the present application;
fig. 5 is a schematic structural view of a skeleton rib of an air rudder according to another direction provided in embodiment 1 of the present application.
In the figure: 1. a rudder shaft; 11. a pipeline; 2. a rudder body; 21. a heat shield layer; 22. a rudder core; 221. a connecting plate; 222. a rudder skeleton; 2221. framework ribs; 2222. a groove; 2223. and a through hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. 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 application.
Example 1:
the embodiment 1 of the application provides a high-efficient thermal resistance air vane of light, and this air vane has the quality light, bears the weight of big, the reliability is high, the structure utilization rate is high, the excellent characteristics of heat-proof quality.
Fig. 1 is a schematic structural diagram of a lightweight, efficient and heat-resistant air rudder provided in embodiment 1 of the present application, and referring to fig. 1, the air rudder includes a rudder shaft 1 and a rudder body 2.
Referring to fig. 2, the inside of the rudder shaft 1 is a hollow structure, 3 to 8S-shaped pipelines 11 are arranged inside the rudder shaft 1, the temperature of the rudder shaft 1 can be reduced by injecting water or fuel oil into the S-shaped pipelines 11, and a zirconia ceramic thermal insulation coating is sprayed on the outer side of the rudder shaft 1, in this embodiment, the rudder shaft 1 is made of titanium alloy.
The rudder body 2 is connected above the rudder shaft 1 by laser welding or brazing, in this embodiment, the rudder body 2 is made of titanium alloy.
The heat-proof layer 21 and the rudder core 22 are arranged in the rudder body 2, the heat-proof layer 21 is made of fiber reinforced resin matrix composite materials, the fiber reinforced resin matrix composite materials are made of fiber woven bodies and resin, the fiber woven bodies are woven by quartz fibers, the resin is phenolic resin, the fiber reinforced resin matrix composite materials can resist ablation and have good heat-proof performance, and the rudder core 22 is protected from being ablated at high temperature; the rudder core 22 is composed of a connecting plate 221 and a rudder skeleton 222, the connecting plate 221 is connected between the heat-proof layer 21 and the rudder skeleton 222, the connecting plate 221 is of an I-shaped structure with a hollow interior and has the function of heat transfer resistance, and a zirconia ceramic heat-insulating coating is sprayed on the surface of the connecting plate 221; referring to fig. 3, 4 and 5, the rudder skeleton 222 is formed by connecting a plurality of skeleton ribs 2221, adjacent skeleton ribs 2221 are connected to form a triangular structure, grooves 2222 are formed in the surfaces of the skeleton ribs 2221, through holes 2223 are formed in the middles of the grooves 2222, the cross sections of the skeleton ribs 2221 are i-shaped, the thickness of the skeleton ribs 2221 is gradually reduced from 10mm to 2mm along the direction far away from the rudder shaft 1, the skeleton ribs 2221 reduce the weight according to the pneumatic load, and the ineffective load can be effectively reduced; in this embodiment, the rudder skeleton 222 is cast, the connection plate 221 and the rudder skeleton 222 are integrally formed by 3D printing, and the skeleton rib 2221 and the connection plate 221 are made of titanium alloy.
In this embodiment, the connecting plate 221 is designed to be a hollow i-shaped structure, and the through hole 2223 is formed in the middle of the frame rib 2221, so that the excess mass can be effectively reduced, the weight of the air rudder is reduced, the structural utilization efficiency is improved, and compared with the conventional air rudder, the mass is reduced by 70%.
In this embodiment, the rudder frame 222, the connection plate 221, and the rudder shaft 1 may be integrally formed, so as to ensure structural integrity and reliability of the aircraft in the flight process.
Example 2:
the embodiment 2 of the application provides a high-efficient thermal resistance air vane of light, and this air vane has the quality light, bears the weight of big, the reliability is high, the structure utilization rate is high, the excellent characteristics of heat-proof quality.
The inside of the rudder shaft 1 is of a hollow structure, 3-8S-shaped pipelines 11 are arranged inside the rudder shaft 1, the temperature of the rudder shaft 1 can be reduced by injecting water or fuel oil into the S-shaped pipelines 11, and a zirconia ceramic heat insulation coating is sprayed on the outer side of the rudder shaft 1.
The rudder body 2 is connected above the rudder shaft 1 through a screw, and in the embodiment, the rudder body 2 is made of titanium alloy.
The heat-proof layer 21 and the rudder core 22 are arranged in the rudder body 2, the heat-proof layer 21 is made of fiber reinforced resin matrix composite materials, the fiber reinforced resin matrix composite materials are made of fiber woven bodies and resin, the fiber woven bodies are woven by carbon fibers, the resin is phenolic resin, the fiber reinforced resin matrix composite materials can resist ablation and have good heat-proof performance, and the rudder core 22 is protected from being ablated at high temperature; the rudder core 22 is composed of a connecting plate 221 and a rudder skeleton 222, the connecting plate 221 is connected between the heat-proof layer 21 and the rudder skeleton 222, the connecting plate 221 is of an I-shaped structure with a hollow interior and has the function of heat transfer resistance, and a zirconia ceramic heat-insulating coating is sprayed on the surface of the connecting plate 221; the rudder framework 222 is formed by connecting a plurality of framework ribs 2221, the adjacent framework ribs 2221 are connected to form a triangular structure, grooves 2222 are formed in the surfaces of the framework ribs 2221, through holes 2223 are formed in the middles of the grooves 2222, the cross sections of the framework ribs 2221 are in an I shape, the thickness of the framework ribs 2221 is gradually reduced from 10mm to 2mm along the direction far away from the rudder shaft 1, the framework ribs 2221 reduce the weight according to the pneumatic load, and the invalid load can be effectively reduced; in this embodiment, the rudder skeleton 222 is cast, the connection plate 221 and the rudder skeleton 222 are integrally formed by 3D printing, and the skeleton rib 2221 and the connection plate 221 are made of titanium alloy.
In this embodiment, the connecting plate 221 is designed to be a hollow i-shaped structure, and the through hole 2223 is formed in the middle of the frame rib 2221, so that the excess mass can be effectively reduced, the weight of the air rudder is reduced, the structural utilization efficiency is improved, and compared with the conventional air rudder, the mass is reduced by 70%.
Example 3:
the embodiment 3 of the application provides a high-efficient thermal resistance air vane of light, and this air vane has the quality light, bears the weight of big, the reliability is high, the structure utilization rate is high, the excellent characteristics of heat-proof quality.
Embodiment 3 provides a schematic view of an air rudder referring to fig. 1 to 5, embodiment 3 provides an air rudder including a rudder shaft 1 and a rudder body 2.
The inside of the rudder shaft 1 is of a hollow structure, 3-8S-shaped pipelines 11 are arranged inside the rudder shaft 1, the temperature of the rudder shaft 1 can be reduced by injecting water or fuel oil into the S-shaped pipelines 11, and a zirconia ceramic heat insulation coating is sprayed on the outer side of the rudder shaft 1, wherein in the embodiment, the rudder shaft 1 is made of high-temperature alloy.
The rudder body 2 is connected above the rudder shaft 1 by casting molding, in this embodiment, the rudder body 2 is made of titanium alloy.
The heat-proof layer 21 and the rudder core 22 are arranged in the rudder body 2, the heat-proof layer 21 is made of zirconia ceramics, and the zirconia ceramics not only can resist ablation, but also has good heat-proof performance, and can protect the rudder core 22 from being ablated by high temperature; the rudder core 22 is composed of a connecting plate 221 and a rudder skeleton 222, the connecting plate 221 is connected between the heat-proof layer 21 and the rudder skeleton 222, the connecting plate 221 is of an I-shaped structure with a hollow interior and has the function of heat transfer resistance, and a zirconia ceramic heat-insulating coating is sprayed on the surface of the connecting plate 221; the rudder framework 222 is formed by connecting a plurality of framework ribs 2221, the adjacent framework ribs 2221 are connected to form a triangular structure, grooves 2222 are formed in the surfaces of the framework ribs 2221, through holes 2223 are formed in the middles of the grooves 2222, the cross sections of the framework ribs 2221 are in an I shape, the thickness of the framework ribs 2221 is gradually reduced from 10mm to 2mm along the direction far away from the rudder shaft 1, the framework ribs 2221 reduce the weight according to the pneumatic load, and the invalid load can be effectively reduced; in this embodiment, the rudder skeleton 222 is cast, the connection plate 221 and the rudder skeleton 222 are connected by screws, and the skeleton rib 2221 and the connection plate 221 are made of titanium alloy.
In this embodiment, the connecting plate 221 is designed to be a hollow i-shaped structure, and the through hole 2223 is formed in the middle of the frame rib 2221, so that the excess mass can be effectively reduced, the weight of the air rudder is reduced, the structural utilization efficiency is improved, and compared with the conventional air rudder, the mass is reduced by 70%.
Example 4:
the embodiment 4 of the application provides a high-efficient thermal resistance air vane of light, and this air vane has the quality light, bears the weight of big, the reliability is high, the structure utilization rate is high, the excellent characteristics of heat-proof quality.
Embodiment 4 provides a schematic view of an air rudder referring to fig. 1 to 5, embodiment 4 provides an air rudder including a rudder shaft 1 and a rudder body 2.
The inside of the rudder shaft 1 is of a hollow structure, 3-8S-shaped pipelines 11 are arranged inside the rudder shaft 1, the temperature of the rudder shaft 1 can be reduced by injecting water or fuel oil into the S-shaped pipelines 11, and a zirconia ceramic heat insulation coating is sprayed on the outer side of the rudder shaft 1.
The rudder body 2 is connected above the rudder shaft 1 through rivets, in the embodiment, the rudder body 2 is made of aluminum alloy.
The heat-proof layer 21 and the rudder core 22 are arranged in the rudder body 2, the heat-proof layer 21 is made of fiber reinforced resin matrix composite materials, the fiber reinforced resin matrix composite materials are made of fiber woven bodies and resin, the fiber woven bodies are woven by silicon carbide fibers, the resin is polyimide resin, the fiber reinforced resin matrix composite materials can resist ablation and have good heat-proof performance, and the rudder core 22 is protected from being ablated at high temperature; the rudder core 22 is composed of a connecting plate 221 and a rudder skeleton 222, the connecting plate 221 is connected between the heat-proof layer 21 and the rudder skeleton 222, the connecting plate 221 is of an I-shaped structure with a hollow interior and has the function of heat transfer resistance, and a zirconia ceramic heat-insulating coating is sprayed on the surface of the connecting plate 221; the rudder framework 222 is formed by connecting a plurality of framework ribs 2221, the adjacent framework ribs 2221 are connected to form a triangular structure, grooves 2222 are formed in the surfaces of the framework ribs 2221, through holes 2223 are formed in the middles of the grooves 2222, the cross sections of the framework ribs 2221 are in an I shape, the thickness of the framework ribs 2221 is gradually reduced from 10mm to 2mm along the direction far away from the rudder shaft 1, the framework ribs 2221 reduce the weight according to the pneumatic load, and the invalid load can be effectively reduced; in this embodiment, the rudder skeleton 222 is cast, the connection plate 221 and the rudder skeleton 222 are integrally formed by 3D printing, and the skeleton rib 2221 and the connection plate 221 are made of aluminum alloy.
In this embodiment, the connecting plate 221 is designed to be a hollow i-shaped structure, and the through hole 2223 is formed in the middle of the frame rib 2221, so that the excess mass can be effectively reduced, the weight of the air rudder is reduced, the structural utilization efficiency is improved, and compared with the conventional air rudder, the mass is reduced by 70%.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A lightweight, high efficiency, thermal resistance air vane, comprising:
the rudder shaft (1) is of a hollow structure, and the rudder shaft (1) is made of titanium alloy, high-temperature alloy or alloy steel;
rudder body (2), rudder body (2) and rudder axle (1) fixed connection, set up heat protection layer (21) and rudder core (22) in rudder body (2), heat protection layer (21) comprises fiber reinforcement resin matrix combined material, zirconia pottery or alumina ceramics, rudder core (22) are including connecting plate (221) and rudder skeleton (222), connecting plate (221) are connected between heat protection layer (21) and rudder skeleton (222), connecting plate (221) are inside hollow I shape structure, rudder skeleton (222) comprise a plurality of skeleton muscle (2221) interconnect.
2. The air rudder with light weight, high efficiency and heat resistance as claimed in claim 1, wherein the surface of the framework rib (2221) is provided with a groove (2222) with an i-shaped cross section.
3. The air rudder with light weight, high efficiency and heat resistance as claimed in claim 2, wherein the middle of the groove (2222) is provided with a through hole (2223).
4. The air rudder with light weight and high efficient heat resistance as claimed in claim 1, wherein the adjacent framework ribs (2221) are connected to form a triangular structure.
5. The lightweight, efficient thermal resistance air rudder according to claim 1, characterized in that the thickness of the skeleton rib (2221) is gradually reduced in a direction away from the rudder shaft (1).
6. The lightweight, efficient thermal resistance air rudder of claim 5, wherein the thickness of the skeletal ribs (2221) is gradually reduced from 10mm to 2 mm.
7. The lightweight, efficient thermal resistance air rudder of claim 1, wherein the fiber reinforced resin based composite material is comprised of a fiber weave woven from quartz fibers, carbon fibers, basalt fibers, boron fibers, alumina fibers, silicon carbide fibers or silicon nitride fibers and a resin that is a phenolic resin or a polyimide resin.
8. The air rudder with light weight and high efficient heat resistance as claimed in claim 1, wherein the connection plate (221) and the rudder skeleton (222) are made of titanium alloy, high temperature alloy, alloy steel or aluminum alloy.
9. The air rudder with light weight, high efficiency and heat resistance as claimed in claim 1 is characterized in that the outside of the rudder shaft (1) is provided with a heat insulating coating.
10. The air rudder with light weight, high efficiency and heat resistance as claimed in claim 1 is characterized in that an S-shaped pipe (11) is arranged inside the rudder shaft (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111215643.4A CN114030589B (en) | 2021-10-19 | 2021-10-19 | Light high-efficiency thermal resistance air rudder |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111215643.4A CN114030589B (en) | 2021-10-19 | 2021-10-19 | Light high-efficiency thermal resistance air rudder |
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| CN114030589A true CN114030589A (en) | 2022-02-11 |
| CN114030589B CN114030589B (en) | 2023-07-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117548998A (en) * | 2023-11-21 | 2024-02-13 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
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| US6419189B1 (en) * | 2000-11-01 | 2002-07-16 | The Boeing Company | Hot ruddervator apparatus and method for an aerospacecraft |
| CN202368786U (en) * | 2011-10-27 | 2012-08-08 | 北京临近空间飞行器系统工程研究所 | Trailing edge rudder adapting to complex force/thermal environment |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
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| CN108995792A (en) * | 2018-07-30 | 2018-12-14 | 上海机电工程研究所 | The airvane of composite structure |
| CN111071430A (en) * | 2019-12-26 | 2020-04-28 | 湖北航天技术研究院总体设计所 | Switching structure and rudder of composite material rudder of high-speed aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6419189B1 (en) * | 2000-11-01 | 2002-07-16 | The Boeing Company | Hot ruddervator apparatus and method for an aerospacecraft |
| CN202368786U (en) * | 2011-10-27 | 2012-08-08 | 北京临近空间飞行器系统工程研究所 | Trailing edge rudder adapting to complex force/thermal environment |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
| CN108672935A (en) * | 2018-07-25 | 2018-10-19 | 北京航星机器制造有限公司 | A kind of large size, thin walled weak rigid titanium alloy rudder wing structure method for laser welding |
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| CN111071430A (en) * | 2019-12-26 | 2020-04-28 | 湖北航天技术研究院总体设计所 | Switching structure and rudder of composite material rudder of high-speed aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117548998A (en) * | 2023-11-21 | 2024-02-13 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
| CN117548998B (en) * | 2023-11-21 | 2024-05-07 | 华钛空天(北京)技术有限责任公司 | Preparation method, device, equipment and medium for thin-wall cavity rudder |
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| Publication number | Publication date |
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| CN114030589B (en) | 2023-07-21 |
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