CN112361894B - Air rudder for rocket - Google Patents
Air rudder for rocket Download PDFInfo
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- CN112361894B CN112361894B CN202011083441.4A CN202011083441A CN112361894B CN 112361894 B CN112361894 B CN 112361894B CN 202011083441 A CN202011083441 A CN 202011083441A CN 112361894 B CN112361894 B CN 112361894B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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Abstract
The embodiment of the application provides an air rudder for a rocket, which comprises: the inner part of the lower side of the upper rudder plate is provided with an upper rudder plate rib; the inner part of the upper side of the lower rudder plate is provided with a lower rudder plate rib; the lower side of the upper rudder plate and the upper side of the lower rudder plate are combined and fixed into a whole; the upper rudder plate rib is formed by cutting the inside of the lower side of the rigid upper side plate, the lower rudder plate rib is formed by cutting the inside of the upper side of the rigid lower side plate, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are skins of the air rudder. The technical problems that the weight of the air rudder is not easy to control and the manufacturing processes are multiple are solved.
Description
Technical Field
The application relates to the technical field of rockets, in particular to an air rudder for a rocket.
Background
The air rudder is an important actuating execution device of a carrier rocket control system, and the good dynamic characteristic indexes of the air rudder put high requirements on the structural design of the air rudder. The traditional design of air vane adopts casting net muscle and covering assembly moulding scheme more, and casting net muscle uses the mould casting to form, just so leads to the weight of casting net muscle to be difficult to control, and the assembly between casting net muscle and the covering forms through the welding, and the welding spot is many. This results in an air vane whose weight is not easily controlled and whose manufacturing process is complicated.
Therefore, the weight of the air vane is not easy to control and the manufacturing process is too many, which is a technical problem that those skilled in the art are urgently in need of solving.
The above information disclosed in the background section is only for enhancement of understanding of the background of the present application and therefore it may contain information that does not form the prior art that is known to those of ordinary skill in the art.
Disclosure of Invention
The embodiment of the application provides an air vane for a rocket, and aims to solve the technical problems that the weight of the air vane is not easy to control and the number of manufacturing processes is large.
The embodiment of the application provides an air vane for rocket, includes:
the inner part of the lower side of the upper rudder plate is provided with an upper rudder plate rib;
the inner part of the upper side of the lower rudder plate is provided with a lower rudder plate rib; the lower side of the upper rudder plate and the upper side of the lower rudder plate are combined and fixed into a whole;
the upper rudder plate rib is formed by cutting the inside of the lower side of the rigid upper side plate, the lower rudder plate rib is formed by cutting the inside of the upper side of the rigid lower side plate, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are skins of the air rudder.
Due to the adoption of the technical scheme, the embodiment of the application has the following technical effects:
the air rudder is formed by oppositely fixing an upper rudder plate and a lower rudder plate, wherein a part of the lower side of a rigid upper side plate is cut off by cutting and an uncut part forms an upper rudder plate rib, a part of the upper side of a rigid lower side plate is cut off by cutting and an uncut part forms a lower rudder plate rib, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are not cut to be used as skins of the air rudder. Thus, the air rudder comprises an upper rudder plate and a lower rudder plate which are vertically combined, the upper side of the upper rudder plate and the lower side of the lower rudder plate are used as skins of the air rudder, and the upper rudder plate rib and the lower rudder plate rib are used for strengthening the strength of the air rudder. The upper rudder plate and the lower rudder plate are formed in a cutting mode in machining, the machining process is simple, and the weight of the air rudder can be well controlled.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a schematic view of an air vane for a rocket according to an embodiment of the present disclosure;
FIG. 2 is an exploded view of the air rudder for rockets shown in FIG. 1;
FIG. 3 is a schematic view of an exposed counterweight of the air rudder for rockets shown in FIG. 1;
fig. 4 is a sectional view a-a shown in fig. 3.
Description of reference numerals:
100 upper rudder plate, 130 upper rudder shaft interface,
200 lower rudder plate, 210 lower rudder plate ribs, 221 lower leading edge, 222 lower tip chord, 223 lower trailing edge,
224 lower root chord, 230 lower rudder shaft interface, 241 lower rudder plate transverse rib, 242 lower rudder plate radial rib,
251 lower edge screw holes, 252 lower edge bolts,
300 skin, 400 counterweight.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
Example one
FIG. 1 is a schematic view of an air vane for a rocket according to an embodiment of the present disclosure; FIG. 2 is an exploded view of the air vane for the rocket shown in FIG. 1; FIG. 3 is a schematic view of an exposed counterweight of the air rudder for rockets shown in FIG. 1; fig. 4 is a sectional view a-a shown in fig. 3. As shown in fig. 1, 2, 3 and 4, an air rudder for a rocket according to an embodiment of the present application includes:
an upper rudder plate 100 having an upper rudder plate rib inside a lower side thereof;
a lower rudder plate 200 having a lower rudder plate rib 210 inside of an upper side thereof; the lower side of the upper rudder plate 100 and the upper side of the lower rudder plate 200 are folded and fixed into a whole;
the upper rudder plate 100 is formed by cutting the inside of the lower side of the rigid upper side plate, the lower rudder plate 200 is formed by cutting the inside of the upper side of the rigid lower side plate, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are skins 300 of the air rudder.
The air rudder for the rocket is formed by oppositely fixing an upper rudder plate and a lower rudder plate, wherein a part of the lower side of a rigid upper side plate is cut off by cutting and the uncut part forms an upper rudder plate rib, a part of the upper side of a rigid lower side plate is cut off by cutting and the uncut part forms a lower rudder plate rib, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are not cut to serve as skins of the air rudder. Thus, the air rudder comprises an upper rudder plate and a lower rudder plate which are vertically combined, the upper side of the upper rudder plate and the lower side of the lower rudder plate are used as skins of the air rudder, and the upper rudder plate rib and the lower rudder plate rib are used for strengthening the strength of the air rudder. The upper rudder plate and the lower rudder plate are formed by adopting a cutting mode in machining, the machining process is simple, and the weight of the air rudder can be well controlled.
The weight of the air rudder can be well controlled, and the air rudder can be suitable for the development direction of a light air rudder; and the machining process has strong operability, short production period and low cost, so that the cost of the air rudder can be controlled to be lower, and the air rudder is suitable for batch production.
In practice, as shown in fig. 1, 2 and 3, the upper side of the upper rudder plate 100 is a right trapezoid, and the lower side of the lower rudder plate 200 is a right trapezoid;
the lower rudder plate 200 has a lower front edge 221 protruding upwards at the bevel edge, and the upper rudder plate 100 has an upper front edge at the bevel edge; wherein, the outward side of the lower front edge 221 is arc-shaped, and the inward side of the lower front edge 221 is a right angle;
the upper front edge is located at a right angle on the inward side of the lower front edge, and the lower front edge 221 is shielded by the upper front edge to prevent wind from entering the air rudder from the joint of the lower rudder plate 200 and the upper rudder plate 100.
Thus, the lower front edge is upwardly convex and the upper front edge is located at a right angle to the side of the lower front edge facing inwards, i.e. the lower front edge covers the upper front edge and prevents wind from entering the air rudder at the joint of the lower rudder plate and the upper rudder plate.
In implementation, as shown in fig. 1, 2 and 3, the lower bottom edge of the upper rudder plate is provided with an upper rudder shaft interface 130;
a lower rudder shaft interface 230 is arranged at the lower bottom edge of the lower rudder plate, and the upper rudder shaft interface 130 and the lower rudder shaft interface 230 are involuted to form a rudder shaft interface;
the rudder shaft interface is used for being fixed with a rudder shaft of the rocket.
The upper rudder shaft interface and the lower rudder shaft interface are involuted to form a rudder shaft interface for fixing the rudder shafts of the air rudder and the rocket.
In an implementation, the upper rudder plate ribs comprise a plurality of upper rudder plate transverse ribs and a plurality of radial upper rudder plate radial ribs;
the upper rudder plate radiating ribs are arranged at intervals in a mode of being parallel to the lower bottom of the right trapezoid, and extend towards the inside of the upper rudder plate by taking the upper rudder shaft interface as the center.
The strength of the upper rudder plate can be enhanced by the transverse upper rudder plate ribs and the radiation upper rudder plate ribs, the upper rudder shaft interface is used for bearing the force applied by the rudder shaft of the rocket, and the radiation upper rudder plate ribs taking the upper rudder shaft interface as the center can quickly and uniformly transfer the force applied by the upper rudder shaft interface to the radiation upper rudder plate ribs.
In practice, as shown in fig. 2, the lower rudder plate fins comprise a plurality of lower rudder plate transverse fins 241 and a plurality of radial lower rudder plate radial fins 242;
the lower rudder plate transverse ribs 241 are arranged at intervals in a manner of being parallel to the lower bottom of the right trapezoid, and each lower rudder plate radiating rib 242 extends into the lower rudder plate by taking the lower rudder shaft connector 230 as a center.
The strength of the lower rudder plate can be enhanced by the lower rudder plate transverse ribs and the lower rudder plate radiation ribs, the lower rudder shaft interface is used for bearing the action of force exerted by the rudder shaft of the rocket, and the lower rudder plate radiation ribs taking the lower rudder shaft interface as the center can quickly and uniformly transmit the action of force exerted by the lower rudder shaft interface to the lower rudder plate radiation ribs.
In the implementation, in the crossed position of the transverse ribs of the upper rudder plate and the radiation ribs of the upper rudder plate, one part is provided with an upper middle screw hole, and the other part is pre-embedded with an upper middle bolt;
one part of the cross positions of the transverse ribs of the lower rudder plate and the radiation ribs of the lower rudder plate is provided with lower middle screw holes, and the other part of the cross positions is embedded with lower middle bolts;
the upper middle screw hole is matched and fixed with the lower middle bolt, and the upper middle bolt is matched and fixed with the lower middle bolt.
Therefore, the upper middle screw hole is matched and fixed with the lower middle bolt, and the upper middle bolt is matched and fixed with the lower middle bolt, so that the upper rudder plate and the lower rudder plate are stably fixed, and the stability of the air rudder is good.
In the implementation, the upper bottom, the right-angle side and the lower bottom of the lower side of the upper rudder plate are sequentially provided with an upper tip chord, an upper rear edge and an upper root chord; the inner side of the upper front edge, the upper tip chord, the upper rear edge and the upper root chord are respectively provided with an upper edge screw hole and an upper edge bolt;
as shown in fig. 2, the upper bottom, the right-angle side and the lower bottom of the upper side of the lower rudder plate are sequentially provided with a lower tip chord 222, a lower rear edge 223 and a lower root chord 224; wherein the lower leading edge 221, the lower tip string, the lower trailing edge, and the lower root string are each provided with a lower edge screw hole 251 and a lower edge bolt 252 pre-embedded therein;
the upper edge screw hole is matched and fixed with the lower edge bolt 252, and the upper edge bolt is matched and fixed with the lower edge screw hole.
The upper bottom, the right-angle side and the uncut part of the lower bottom of the upper rudder plate form an upper tip chord, an upper rear edge and an upper root chord; the upper bottom, the right-angle side and the uncut part of the lower bottom of the upper side of the lower rudder plate form a lower tip chord, a lower rear edge and a lower root chord, so that the periphery of the air rudder is not an open opening structure but a relatively closed structure, and the requirements of the air rudder are met; the upper edge screw hole with the lower limb bolt cooperatees fixedly, the upper edge bolt with the lower limb screw hole cooperatees fixedly for the installation of air vane is more firm, and the air vane wholeness is good.
In practice, as shown in fig. 2 and 3, the air rudder further includes a weight 400, which is disposed in a space enclosed by the upper rudder plate and the lower rudder plate for adjusting the center of gravity of the air rudder.
According to the design of the whole rocket, the air rudder has the requirements of weight range and gravity center position, and the air rudder can be controlled in the requirements of weight range and the gravity center can be controlled in the requirements of gravity center position by adjusting the weight and the position of the balancing weight.
Specifically, the counterweight is machined from a high-density alloy material.
In the implementation, the upper rudder plate is an aluminum alloy upper rudder plate, and the lower rudder plate is an aluminum alloy lower rudder plate;
the thickness of the upper rudder plate rib and the lower rudder plate rib is 5 mm;
the thickness of the upper root chord and the lower root chord is 7 millimeters;
the upper tip chord and the lower tip chord are 7 millimeters thick;
the thickness of the upper leading edge is 30 millimeters;
the thickness of the skin is 2.5 mm.
By the choice of material and the thickness of the various parts of the upper rudder plate, control of weight and strength can be achieved.
Specifically, the upper rudder plate is an upper rudder plate made of 2A14 aluminum alloy, and the lower rudder plate is a lower rudder plate made of 2A14 aluminum alloy; the 2A14 aluminum alloy is a hard aluminum alloy material, has main chemical components of zinc, iron, magnesium, aluminum and the like, and has good machinability, and good electrical resistivity, spot welding performance and seam welding performance.
In an implementation, the upper rudder plate is an integrated upper rudder plate, and the lower rudder plate is an integrated lower rudder plate.
The upper rudder plate and the lower rudder plate are integrated, so that the integrity of the upper rudder plate and the lower rudder plate is good, and the rigidity and the strength of the upper rudder plate and the lower rudder plate are high.
Therefore, the air rudder of the embodiment of the application is integrally in a skin reinforced structure, the lower bottoms of the upper rudder plate and the lower rudder plate are positions where the action of force is exerted by the rudder shaft of the rocket and fixed with the rudder shaft of the rocket, the lower bottoms of the upper rudder plate and the lower rudder plate are directly connected with the skin to form an integrated structure, and the skin is a main force bearing structure for bearing the force exerted by the rudder shaft of the rocket; the bevel edges of the upper rudder plate and the lower rudder plate are windward sides, the bevel edges of the upper rudder plate and the lower rudder plate are directly connected with the skin into an integrated structure, and the skin is a main bearing structure for bearing the force of outside wind.
In practice, a lightweight thermal barrier coating is applied to the outwardly facing surface of the air vane. The air rudder has a small weight while playing a role of heat insulation.
In the description of the present application and the embodiments thereof, it is to be understood that the terms "top", "bottom", "height", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely 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 be operated, and thus, should not be construed as limiting the present application.
In this application and its embodiments, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," "secured," and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integral to; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In this application and its embodiments, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise the first and second features being in direct contact, or may comprise the first and second features being in contact, not directly, but via another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly above and obliquely above the second feature, or simply meaning that the first feature is at a lesser level than the second feature.
The above disclosure provides many different embodiments or examples for implementing different structures of the application. The components and arrangements of specific examples are described above to simplify the present disclosure. Of course, they are merely examples and are not intended to limit the present application. Further, the present application may repeat reference numerals and/or reference letters in the various examples for simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or arrangements discussed. In addition, examples of various specific processes and materials are provided herein, but one of ordinary skill in the art may recognize applications of other processes and/or use of other materials.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (9)
1. An air rudder for rockets, comprising:
the inner part of the lower side of the upper rudder plate is provided with an upper rudder plate rib;
the inner part of the upper side of the lower rudder plate is provided with a lower rudder plate rib; the lower side of the upper rudder plate and the upper side of the lower rudder plate are combined and fixed into a whole;
the upper rudder plate rib is formed by cutting the inside of the lower side of the rigid upper side plate, the lower rudder plate rib is formed by cutting the inside of the upper side of the rigid lower side plate, and the upper side of the upper rudder plate and the lower side of the lower rudder plate are skins of the air rudder;
the upper side of the upper rudder plate is in a right trapezoid shape, and the lower side of the lower rudder plate is in a right trapezoid shape;
the bevel edge of the lower rudder plate is provided with a lower front edge protruding upwards, and the bevel edge of the upper rudder plate is an upper front edge; the side, facing outwards, of the lower front edge is arc-shaped, and the side, facing inwards, of the lower front edge is a right angle;
the upper front edge is positioned at a right angle of the inward side of the lower front edge, and the lower front edge shields the upper front edge to prevent wind from entering the air rudder from the joint of the lower rudder plate and the upper rudder plate.
2. The air rudder of claim 1, wherein the lower bottom edge of the upper rudder plate is provided with an upper rudder shaft interface;
a lower rudder shaft interface is arranged on the lower bottom edge of the lower rudder plate, and the upper rudder shaft interface and the lower rudder shaft interface are involuted to form a rudder shaft interface;
the rudder shaft interface is used for being fixed with a rudder shaft of the rocket.
3. The air rudder of claim 2, wherein the upper rudder plate ribs include a plurality of upper rudder plate transverse ribs and a plurality of radial upper rudder plate radiating ribs;
the upper rudder plate transverse ribs are arranged at intervals in a mode of being parallel to the lower bottom of the right trapezoid, and the upper rudder plate radiation ribs extend into the upper rudder plate by taking the upper rudder shaft connector as a center.
4. The air rudder of claim 3, wherein the lower rudder plate ribs include a plurality of lower rudder plate transverse ribs and a plurality of radial lower rudder plate radiating ribs;
the lower rudder plate transverse ribs are arranged at intervals in a mode of being parallel to the lower bottom of the right trapezoid, and the lower rudder plate radiation ribs extend into the lower rudder plate by taking the lower rudder shaft connector as a center.
5. The air rudder of claim 4, wherein one part of the positions where the upper rudder plate transverse ribs and the upper rudder plate radiating ribs intersect are provided with upper middle screw holes, and the other part is embedded with upper middle bolts;
one part of the cross positions of the transverse ribs of the lower rudder plate and the radiation ribs of the lower rudder plate is provided with lower middle screw holes, and the other part of the cross positions is embedded with lower middle bolts;
the upper middle screw hole is matched and fixed with the lower middle bolt, and the upper middle bolt is matched and fixed with the lower middle bolt.
6. The air rudder of claim 5, wherein the upper bottom, the right-angle sides and the lower bottom of the lower side of the upper rudder plate are provided with an upper tip chord, an upper rear edge and an upper root chord in sequence; the inner side of the upper front edge, the upper tip chord, the upper rear edge and the upper root chord are respectively provided with an upper edge screw hole and an upper edge bolt;
the upper bottom, the right-angle side and the lower bottom on the upper side of the lower rudder plate are sequentially provided with a lower tip chord, a lower rear edge and a lower root chord; the lower front edge, the lower tip string, the lower rear edge and the lower root string are respectively provided with a lower edge screw hole and a lower edge bolt embedded in the lower edge screw hole;
the upper edge screw hole is matched and fixed with the lower edge bolt, and the upper edge bolt is matched and fixed with the lower edge screw hole.
7. The air rudder of claim 6, further comprising a weight block disposed in a space enclosed by the upper rudder plate and the lower rudder plate for adjusting a center of gravity of the air rudder.
8. The air rudder of claim 7, wherein the upper rudder plate is an aluminum alloy upper rudder plate and the lower rudder plate is an aluminum alloy lower rudder plate;
the thickness of the upper rudder plate rib and the lower rudder plate rib is 5 mm;
the thickness of the upper root chord and the lower root chord is 7 millimeters;
the upper tip chord and the lower tip chord are 7 millimeters thick;
the thickness of the upper leading edge is 30 mm;
the thickness of the skin is 2.5 mm.
9. The air rudder of claim 7, wherein the upper rudder plate is a one-piece upper rudder plate and the lower rudder plate is a one-piece lower rudder plate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011083441.4A CN112361894B (en) | 2020-10-12 | 2020-10-12 | Air rudder for rocket |
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| CN202011083441.4A CN112361894B (en) | 2020-10-12 | 2020-10-12 | Air rudder for rocket |
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| CN113022842B (en) * | 2021-03-26 | 2023-03-17 | 宁波中科祥龙轻量化科技有限公司 | High-temperature-resistant high-bearing foldable air rudder |
| CN113324443B (en) * | 2021-04-22 | 2023-03-17 | 上海机电工程研究所 | Pneumatic device of edge strip rudder with tip turbulence assembly |
| CN114180028B (en) * | 2021-12-09 | 2024-06-11 | 北京星航机电装备有限公司 | Assembly for preparing hollow grid-structure wing rudder and preparation method of wing rudder |
| CN114136156B (en) * | 2021-12-09 | 2024-04-26 | 北京星航机电装备有限公司 | Preparation method of wing rudder with hollow grid structure |
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| CN101920392A (en) * | 2010-07-16 | 2010-12-22 | 沈阳飞机工业（集团）有限公司 | Mechanically-machining rib/diffusion connecting process for titanium alloy rudders and wing members |
| CN102825427B (en) * | 2012-08-19 | 2015-04-22 | 什邡市明日宇航工业股份有限公司 | Manufacturing method for diffusion welding of aircraft rudder assembly |
| DE102015005135A1 (en) * | 2015-04-22 | 2016-10-27 | Diehl Bgt Defence Gmbh & Co. Kg | Missile rudder system |
| CN107602142B (en) * | 2017-08-09 | 2020-01-03 | 湖北航天技术研究院总体设计所 | Preparation method of integrated integral composite material air rudder |
| CN108995792B (en) * | 2018-07-30 | 2020-04-24 | 上海机电工程研究所 | Air rudder with composite material structure |
| CN109332998B (en) * | 2018-09-13 | 2020-01-21 | 湖北三江航天红阳机电有限公司 | Manufacturing method of integrated empennage with double-layer skin of ultra-long thin-wall aluminum alloy sandwich grid rib |
| 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 |
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