CN210707966U - Air rudder and rocket - Google Patents
Air rudder and rocket Download PDFInfo
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- CN210707966U CN210707966U CN201920548127.5U CN201920548127U CN210707966U CN 210707966 U CN210707966 U CN 210707966U CN 201920548127 U CN201920548127 U CN 201920548127U CN 210707966 U CN210707966 U CN 210707966U
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- 230000003014 reinforcing effect Effects 0.000 claims description 16
- 229910000838 Al alloy Inorganic materials 0.000 claims description 13
- 230000004308 accommodation Effects 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 11
- 229910052782 aluminium Inorganic materials 0.000 description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 8
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- 229910052751 metal Inorganic materials 0.000 description 2
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- 230000004048 modification Effects 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- -1 silica phenolic aldehyde Chemical class 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000000377 silicon dioxide Substances 0.000 description 2
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
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- 238000011161 development Methods 0.000 description 1
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Abstract
The application discloses an air vane and a rocket. The air rudder comprises a rudder body and a rudder shaft used for being connected with a rocket body, wherein the rudder shaft is fixedly connected with the rudder body, and a first heat-proof layer is arranged on the rudder body. The problem that traditional air vane manufacturing process is complicated is solved in this application.
Description
Technical Field
The application relates to the field of aircraft tail end equipment, in particular to an air rudder and a rocket.
Background
When the carrier rocket flies in the atmosphere, attitude control is mainly carried out by the aid of the gas rudder and the air rudder, the air rudder is installed on the outer side of the tail section of the carrier rocket, when the air rudder and the carrier rocket rotate to form a certain angle, reaction force in a certain direction can be generated when high-speed airflow flows through the air rudder, so that the attitude of the carrier rocket is controlled, and the attitude of the carrier rocket can be controlled by controlling the angle of the control surface of the air rudder.
In the related art, the traditional air rudder is mostly manufactured by adopting a three-dimensional five-way woven C/SiC composite material.
In the course of implementing the present invention, the inventors found that there are at least the following problems in the related art:
in the related art, the conventional air vane manufacturing process is complicated.
Aiming at the problem that the traditional air rudder manufacturing process in the related art is complex, an effective solution is not provided at present.
SUMMERY OF THE UTILITY MODEL
The main purpose of this application is to provide an air vane and a rocket to solve the problem that the traditional air vane manufacturing process is complicated.
In order to achieve the above object, according to one aspect of the present application, there is provided an air rudder.
The air rudder according to the present application includes:
the rocket comprises a rudder body and a rudder shaft used for being connected with a rocket body;
the rudder shaft is fixedly connected with the rudder body, the first heat-proof layer is arranged on the rudder body, the rudder body is made of aluminum alloy, and the rudder shaft is made of stainless steel.
Further, the rudder body comprises a core and an air rudder leading edge;
the front edge of the air rudder is fixed on a core body, and the core body is fixedly connected with the rudder shaft.
Further, the core includes a receiving slot corresponding to the leading edge of the air vane, the leading edge of the air vane being secured in the receiving slot.
Furthermore, the core body also comprises a framework and a cover plate corresponding to the framework;
skeleton and apron fixed connection, the holding tank is located on the skeleton.
Furthermore, a plurality of reinforcing ribs are arranged on the framework.
Further, the plurality of reinforcing ribs may have a crotch shape.
Further, the material of the framework and the cover plate comprises aluminum alloy.
Furthermore, each reinforcing rib of the plurality of reinforcing ribs is provided with a vent hole.
Furthermore, the rudder shaft comprises a clamping part and a connecting part used for being connected with the rocket body, the first end of the clamping part is fixedly connected with the connecting part, the second end of the clamping part is fixedly connected with the framework, and a second heat-proof layer is arranged on the clamping part.
In order to achieve the above object, according to another aspect of the present application, there is provided a rocket.
A rocket according to the present application comprises:
the air rudder and the rocket body, the connecting part is connected with the rocket body.
In the embodiment of the application, a rudder body and a rudder shaft used for being connected with a rocket body are adopted, the rudder shaft is fixedly connected with the rudder body, and a first heat-proof layer is arranged on the rudder body. The problem that traditional air vane manufacturing process is complicated is solved in this application.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
FIG. 1 is an assembly schematic of an air vane according to an embodiment of the present application;
FIG. 2 is a schematic structural view of an air rudder backbone according to an embodiment of the present application;
FIG. 3 is a schematic structural view of an air rudder shaft according to an embodiment of the present application;
FIG. 4 is a schematic view of a configuration of a leading edge of an air vane according to an embodiment of the present application;
fig. 5 is a schematic view of an air rudder backbone according to an embodiment of the present application.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, 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 only partial 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.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "top", "bottom", "inner", "outer", "middle", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "disposed," "provided," "connected," and "nested" are to be construed broadly. For example, "connected" may be a fixed connection, a detachable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. 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 should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 and 4, the present application relates to an air rudder including: the rudder body 6 and be used for with rocket body's rudder axle 5 of being connected, rudder axle 5 and rudder body 6 fixed connection are equipped with first heat protection layer 1 on the rudder body 6, the material of rudder body 6 all includes the aluminum alloy, the material of rudder axle 5 includes the stainless steel.
In this embodiment, the rudder body 6 is fixedly connected with the rudder shaft 5, the shape of the rudder body 6 includes an airfoil, the first heat-proof layer 1 is arranged on the rudder body 6, the material of the first heat-proof layer 1 includes W1-RT1045 biological cork, so that the main body part and the heat-proof part of the air rudder are separated, the rudder body 6 is made of metal and mainly includes aluminum alloy and the like, so that the manufacturing cost of the air rudder is low, the manufacturing process is simple, the first heat-proof layer 1 is directly sprayed on the rudder body 6, the two sides of the rudder body 6 are made of W1-RT1045 biological cork, and the material of the rudder shaft 5 includes stainless steel and the like, so that the air rudder reduces the generation period, reduces the production cost, and is convenient to assemble and disassemble when the characteristics of ablation resistance, high strength, light weight and the like are ensured.
Further, referring to fig. 1, the rudder body 6 includes a core and an air rudder front edge 4, the air rudder front edge 4 is fixed on the core, and the core is fixedly connected with the rudder shaft 5.
In this embodiment, rudder body 6 includes core and air vane leading edge 4, and the material of core includes the aluminum alloy, and the material of air vane leading edge 4 includes mould pressing high silica phenolic aldehyde, is equipped with the connecting portion corresponding with rudder axle 5 on the core, connecting portion and rudder axle 5 swing joint for air vane easy dismounting, it is with low costs.
Further, referring to fig. 1, 2 and 4, the core includes a receiving groove 33 corresponding to the air vane leading edge 4, and the air vane leading edge 4 is secured in the receiving groove 33.
In this embodiment, the core includes an accommodation groove 33 corresponding to the air vane leading edge 4, and the air vane leading edge 4 is fixed in the accommodation groove 33, so that the air vane is more heat-proof.
Further, referring to fig. 1, the core further includes a frame 3 and a cover plate 2 corresponding to the frame 3, the frame 3 is fixedly connected to the cover plate 2, and the accommodating groove 33 is formed in the frame 3.
In this embodiment, the core still includes skeleton 3 and the apron 2 that corresponds with skeleton 3, be equipped with corresponding screw hole on skeleton 3 and the apron 2, it is fixed with skeleton 3 and apron 2 through the screw, the 3 top surfaces of skeleton are corresponding with the shape of apron 2, the both sides face of skeleton 3 all includes an holding tank 33, air vane leading edge 4 includes bellying 42 and arc 41, bellying 42 and arc 41 fixed connection, be equipped with the screw hole on the bellying 42, be equipped with the screw hole corresponding with bellying 42 on the skeleton 3, pass bellying 42 and the last corresponding screw hole of skeleton 3 through the screw and make air vane leading edge 4 fix on skeleton 3, the material of air vane leading edge 4 includes mould pressing high silica phenolic aldehyde etc, the core is dismantled simply, with low costs and good with air vane leading edge 4 suitability.
Further, referring to fig. 1, 2 and 5, the frame 3 is provided with a plurality of reinforcing ribs.
In this embodiment, the frame 3 is provided with a plurality of reinforcing ribs, and in the structural design process, the overhanging surface of the structural body may be too large or the span may be too large, and under such a condition, the load that can be borne by the connecting surface of the structural body itself is limited, and then a reinforcing plate, commonly called a reinforcing rib, is added on the common vertical surface of the two combined bodies to increase the strength of the combining surface, so that the strength of the frame 3 is improved while the weight is reduced.
Further, referring to fig. 1, 2 and 5, the shape of the plurality of reinforcing bars includes a crotch shape.
In the embodiment, the plurality of reinforcing ribs are crotch-shaped, that is, the plurality of reinforcing ribs form a plurality of triangular regions connected with each other in the framework 3, and the triangular stability makes the air vane not easy to deform like a quadrangle, and the air vane has the characteristics of stability, firmness and pressure resistance, so that the air vane is ensured to have greater strength while the weight of the air vane is reduced.
Further, the material of the framework 3 and the cover plate 2 comprises aluminum alloy.
In this embodiment, the materials of the framework 3 and the cover plate 2 include aluminum alloy, which is a non-ferrous metal structural material most widely used in the industry, and has been widely used in the aviation, aerospace, automobile, mechanical manufacturing, ship and chemical industries, the rapid development of industrial economy has increased demand for aluminum alloy welded structural members, the density of pure aluminum is small (ρ is 2.7g/cm3), the melting point is about 1/3 of iron, the melting point is low (660 ℃), and aluminum is a face-centered cubic structure, so the aluminum has high plasticity (δ is 32-40%, ψ is 70-90%), the aluminum is easy to process, various profiles and plates can be made, the corrosion resistance is good, but the strength of pure aluminum is low, the σ b value in an annealing state is about 8kgf 2, so the aluminum is not suitable for structural materials, and through long-term production practices and scientific experiments, people gradually add alloy elements and apply heat treatment to strengthen aluminum, therefore, a series of aluminum alloys are obtained, the alloy formed by adding certain elements has higher strength while keeping the advantages of light weight of pure aluminum and the like, and the sigma b values can respectively reach 24-60 kgf/mm 2. Therefore, the specific strength (the ratio sigma b/rho of the strength to the specific gravity) of the steel plate is superior to that of a plurality of alloy steels, so that the steel plate becomes an ideal structural material and is widely applied to the aspects of mechanical manufacture, transportation machinery, power machinery, aviation industry and the like, the airframe, the skin, the air compressor and the like of an airplane are usually made of aluminum alloy to reduce the self weight, and the aluminum alloy is adopted to replace the welding of steel plate materials, so that the structural weight can be reduced by more than 50%.
Further, referring to fig. 2, each of the plurality of ribs is provided with a vent hole.
In this embodiment, each of the plurality of reinforcing ribs is provided with a vent hole, the side of the specific reinforcing rib is provided with a vent hole, each reinforcing rib comprises at least one vent hole to reduce the pressure difference between the inner cavity of the air rudder and the outer surface of the rocket and reduce the risk of damaging the air rudder cover plate 2, the air rudder further comprises a sensor, a connecting wire of the sensor can penetrate through the vent holes to arrange the sensor inside the air rudder, the sensor is a detection device which can sense the measured information and convert the sensed information into an electric signal or other required information to be output according to a certain rule so as to meet the requirements of information transmission, processing, storage, display, recording, control and the like,
further, referring to fig. 1 and 3, the rudder shaft 5 includes a clamping portion and a connecting portion for connecting with the rocket body, a first end of the clamping portion is fixedly connected with the connecting portion, a second end of the clamping portion is fixedly connected with the framework 3, and a second heat-proof layer is arranged on the clamping portion.
In this embodiment, the rudder shaft 5 includes a clamping portion and a connecting portion for connecting with a rocket body, the clamping portion is provided with a groove corresponding to the air rudder skeleton 3, two sections of the clamping portion are respectively provided with one, two or three screw holes, the screw holes are uniformly distributed on the clamping portion, the air rudder skeleton 3 is also provided with screw holes corresponding to the screw holes on the clamping portion, the screw holes respectively penetrate through the clamping portion and the corresponding screw holes on the air rudder skeleton 3, so that the rudder body 6 and the rudder shaft 5 are fixed, the part on the air rudder skeleton 3 corresponding to the groove on the clamping portion is a connecting plate, the outer surface of the clamping portion is sprayed with a second heat-proof layer, the material of the second heat-proof layer includes W1-RT1045 biological cork, and the thickness of the second heat-proof layer corresponds to the thickness of the first heat-proof layer rudder 1, so as to enhance the heat-proof capability of the air.
Based on the same technical concept, the embodiment of the present application further provides a rocket, which refers to fig. 1 and 3, and includes: the air rudder and the rocket body, the connecting part is connected with the rocket body.
In this embodiment, the connecting portion is a hollow sleeve, a limiting hole is formed in the side wall of the sleeve, the limiting hole is formed at a position close to one end connected with the rocket body, and the other end of the sleeve is fixed to one side face of the clamping portion, so that the air rudder rotating angle is changed under the driving of the rocket body internal mechanism, and the purpose of changing the flight direction of the rocket is achieved.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. An air vane, comprising: a rudder body (6) and a rudder shaft (5) used for connecting with the rocket body;
the rudder shaft (5) is fixedly connected with the rudder body (6), a first heat-proof layer (1) is arranged on the rudder body (6), the rudder body (6) is made of aluminum alloy, and the rudder shaft (5) is made of stainless steel.
2. Air rudder according to claim 1, characterised in that the rudder body (6) comprises a core and an air rudder leading edge (4);
the air rudder front edge (4) is fixed on the core body, and the core body is fixedly connected with the rudder shaft (5).
3. An air rudder according to claim 2, characterised in that the core comprises an accommodation groove (33) corresponding to the air rudder leading edge (4), the air rudder leading edge (4) being fixed in the accommodation groove (33).
4. An air rudder according to claim 3, characterised in that the core further comprises a skeleton (3) and a cover plate (2) corresponding to the skeleton (3);
skeleton (3) with apron (2) fixed connection, holding tank (33) are located on skeleton (3).
5. Air rudder according to claim 4, characterised in that the frame (3) is provided with a number of stiffening ribs (32).
6. An air rudder according to claim 5, characterised in that the shape of the plurality of reinforcing ribs (32) comprises a crotch shape.
7. Air rudder according to claim 6, characterised in that the material of the skeleton (3) and the cover plate (2) comprises an aluminium alloy.
8. The air rudder of claim 6, wherein each of the plurality of reinforcing ribs (32) has a vent hole (31) formed therein.
9. The air rudder according to claim 4, wherein the rudder shaft (5) includes a clamping portion (51) and a connecting portion (52) for connecting with a rocket body, a first end of the clamping portion (51) is fixedly connected with the connecting portion (52), a second end of the clamping portion (51) is fixedly connected with the frame (3), and a second heat-proof layer is provided on the clamping portion (51).
10. A rocket comprising an air rudder and a rocket body according to claim 9, said connecting portion (52) being connected to said rocket body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920548127.5U CN210707966U (en) | 2019-04-22 | 2019-04-22 | Air rudder and rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920548127.5U CN210707966U (en) | 2019-04-22 | 2019-04-22 | Air rudder and rocket |
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| CN210707966U true CN210707966U (en) | 2020-06-09 |
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| CN201920548127.5U Active CN210707966U (en) | 2019-04-22 | 2019-04-22 | Air rudder and rocket |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203421A (en) * | 2019-05-21 | 2019-09-06 | 重庆零壹空间航天科技有限公司 | Empennage and aircraft comprising the empennage |
| CN112361894A (en) * | 2020-10-12 | 2021-02-12 | 中国运载火箭技术研究院 | Air rudder for rocket |
| CN113022842A (en) * | 2021-03-26 | 2021-06-25 | 中国科学院宁波材料技术与工程研究所 | High-temperature-resistant high-bearing foldable air rudder |
| CN114801252A (en) * | 2022-06-30 | 2022-07-29 | 天津爱思达新材料科技有限公司 | Zero-ablation air rudder with multilayer heat-proof structure and preparation method and device thereof |
| CN115108054A (en) * | 2022-08-16 | 2022-09-27 | 北京凌空天行科技有限责任公司 | A lightweight air rudder for rockets |
| CN115523806A (en) * | 2022-09-28 | 2022-12-27 | 北京宇航系统工程研究所 | Resistance rudder and hanging cable recovery integrated mechanism and recovery method |
| CN116101517A (en) * | 2023-01-06 | 2023-05-12 | 湖北航天技术研究院总体设计所 | Heat-resistant bearing integrated air rudder thermal resistance structure |
-
2019
- 2019-04-22 CN CN201920548127.5U patent/CN210707966U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203421A (en) * | 2019-05-21 | 2019-09-06 | 重庆零壹空间航天科技有限公司 | Empennage and aircraft comprising the empennage |
| CN112361894A (en) * | 2020-10-12 | 2021-02-12 | 中国运载火箭技术研究院 | Air rudder for rocket |
| CN113022842A (en) * | 2021-03-26 | 2021-06-25 | 中国科学院宁波材料技术与工程研究所 | High-temperature-resistant high-bearing foldable air rudder |
| CN114801252A (en) * | 2022-06-30 | 2022-07-29 | 天津爱思达新材料科技有限公司 | Zero-ablation air rudder with multilayer heat-proof structure and preparation method and device thereof |
| CN115108054A (en) * | 2022-08-16 | 2022-09-27 | 北京凌空天行科技有限责任公司 | A lightweight air rudder for rockets |
| CN115523806A (en) * | 2022-09-28 | 2022-12-27 | 北京宇航系统工程研究所 | Resistance rudder and hanging cable recovery integrated mechanism and recovery method |
| CN116101517A (en) * | 2023-01-06 | 2023-05-12 | 湖北航天技术研究院总体设计所 | Heat-resistant bearing integrated air rudder thermal resistance structure |
| CN116101517B (en) * | 2023-01-06 | 2025-07-22 | 湖北航天技术研究院总体设计所 | Heat-resistant bearing integrated air rudder thermal resistance structure |
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