CN210526883U - Gas rudder, gas rudder connecting assembly and rocket - Google Patents
Gas rudder, gas rudder connecting assembly and rocket Download PDFInfo
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- CN210526883U CN210526883U CN201920555171.9U CN201920555171U CN210526883U CN 210526883 U CN210526883 U CN 210526883U CN 201920555171 U CN201920555171 U CN 201920555171U CN 210526883 U CN210526883 U CN 210526883U
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Abstract
The application discloses gas vane, gas vane coupling assembling and rocket. Wherein this gas rudder includes: the rudder body, tiller and be used for with rocket body coupling's rudder key, the first terminal surface of tiller is the ladder terminal surface, the rudder key-type connection is in the ladder terminal surface top of tiller, the top of ladder terminal surface is less than the bottom, the ladder terminal surface of tiller with rocket body laminating, the second terminal surface of tiller with the rudder body coupling. The application solves the problem that the connection gap between the gas rudder and the rocket body has poor heat-proof effect.
Description
Technical Field
The application relates to the field of rocket equipment, in particular to a gas rudder, a gas rudder connecting assembly and a rocket.
Background
The gas rudders are used as control surfaces of spacecrafts such as ballistic missiles, air-defense missiles, air-air missiles, solid rockets and the like, are positioned behind an engine at the tail part of the spacecrafts, are provided with respective control mechanisms, when the gas rudders rotate in a certain direction by a certain angle, part of gas sprayed out of the spray pipe changes the direction, and the reaction force generated by the sprayed gas can assist the control surfaces to adjust the flight attitude and the flight direction.
In the related technology, high temperature resistant alloy materials are mostly adopted to meet the requirements of high temperature resistance, heat flow scouring resistance and thermal shock resistance of the control surface, such as graphite, tungsten copper infiltration and other materials.
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, because the gas rudder needs to be fixed on the rocket body, the heat-proof effect of a connecting gap between the gas rudder and the rocket body is poor.
Aiming at the problem that the heat-proof effect of a connecting gap between a gas rudder and a rocket body is poor in the related art, an effective solution is not provided at present.
SUMMERY OF THE UTILITY MODEL
The main aim at of this application provides a gas rudder, gas rudder coupling assembling and rocket to solve the relatively poor problem of joint gap heat-proof effect between gas rudder and the rocket body.
In order to achieve the above object, in a first aspect, an embodiment of the present application provides a gas rudder, including:
the rocket comprises a rudder body, a rudder handle and a rudder key for connecting with a rocket body;
the first end face of the tiller is a step end face, the rudder key is connected to the top of the step end face of the tiller, the top of the step end face is smaller than the bottom of the tiller, the step end face of the tiller is attached to the rocket body, and the second end face of the tiller is connected with the tiller body.
Furthermore, the ladder terminal surface includes a plurality of terminal surfaces, and every terminal surface shape in a plurality of terminal surfaces is circular, and a plurality of terminal surfaces dwindle gradually to rudder key direction along the rudder body.
Further, the plurality of end surfaces includes three end surfaces.
Further, the rudder body comprises a rudder surface and a guard plate;
the second end surface of the tiller is fixedly connected with the first end surface of the guard plate, and the second end surface of the guard plate is fixedly connected with the control surface.
Further, the rudder stock and the rudder surface are integrally constructed.
Further, the shape of the control surface includes an airfoil.
Further, the rudder key includes the key body and at least one keyway that is used for being connected with the rocket body, the key body and the first terminal surface fixed connection of tiller, and at least one keyway all sets up on the key body.
The second aspect, this application still provides a gas rudder coupling assembling, including rudder axle and gas rudder, rudder axle and rudder key-type connection.
In a third aspect, the application further provides a rocket, which comprises a rocket body and a gas rudder, wherein the gas rudder comprises a rudder key fixed on the rocket body.
Furthermore, the rocket body is provided with an accommodating groove corresponding to the step end face, and the accommodating groove is attached to the step end face.
In the gas rudder, gas rudder coupling assembling and rocket that this application embodiment provided, this gas rudder includes: the first end face of the rudder stock is a stepped end face, the rudder stock is connected to the top of the stepped end face of the rudder stock, the top of the stepped end face is smaller than the bottom of the stepped end face, the stepped end face of the rudder stock is attached to the rocket body, and the second end face of the rudder stock is connected with the rudder body. The application solves the problem that the connection gap between the gas rudder and the rocket body has poor heat-proof effect.
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 a schematic structural view of a gas vane 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, the present application relates to a gas vane comprising: the rudder body 1, the rudder stock 4 and a rudder key 7 used for connecting with the rocket body; the first end face of the rudder stock 4 is a step end face, the rudder key 7 is connected to the top of the step end face of the rudder stock 4, the top of the step end face is smaller than the bottom, the step end face of the rudder stock 4 is attached to a rocket body, and the second end face of the rudder stock 4 is connected with the rudder body 1.
In this embodiment, the gas rudder comprises a rudder body 1, a rudder stock 4 and a rudder key 7 for connecting with a rocket body, the rudder body 1 is made of graphite, tungsten impregnated copper and the like, the rudder body 1 is fixedly connected with the rudder stock 4, the rudder stock 4 is fixed in the middle of one end surface of the rudder body 1, so that the heat-proof effect is good, the rudder stock 4 is fixedly connected with the rudder key 7, the rudder key 7 is connected in the middle of one side surface of the rudder stock 4, the rudder key 7 is connected with the rocket body, the rudder key 7 is driven by the rocket body to rotate so as to change the angle of the rudder body 1, the first end surface of the rudder stock 4 is a step end surface, the rudder key 7 is connected with the top of the step end surface of the rudder stock 4, the top of the step end surface is smaller than the bottom, the step end surface is of a multilayer cylinder structure, the multilayer cylinder is a straight cylinder, the straight cylinder is also called a right cylinder and a cylinder, and can be seen as a geometric body formed by, the rudder key 7 is fixedly connected to the middle of the top of the stepped end face of the rudder stock 4, the diameter of the end face of the top of the stepped end face is smaller than that of the end face of the bottom of the stepped end face, the stepped end face of the rudder stock 4 is attached to and attached to the rocket body, the distance between the end faces is the same, the second end face of the rudder stock 4 is connected with the rudder body 1, and the second end face of the rudder stock 4 is fixedly connected with the rudder body 1.
Further, referring to fig. 1, the stepped end surface includes a plurality of end surfaces, each of the plurality of end surfaces is circular, and the plurality of end surfaces are gradually reduced toward the rudder key 7 along the rudder body 1.
In this embodiment, the ladder terminal surface includes a plurality of terminal surfaces, and the distance between a plurality of terminal surfaces equals, and the shape of every terminal surface is circular in a plurality of terminal surfaces, and the diameter of each circular terminal surface varies, and a plurality of terminal surfaces reduce to the terminal surface diameter of rudder key 7 direction along rudder body 1 gradually for the distance that the heat current passes through increases, and the turning point increases, makes the heat protection effect between gas rudder and the rocket body better.
Further, referring to fig. 1, the plurality of end surfaces includes three end surfaces.
In this embodiment, a plurality of terminal surfaces contain three terminal surface, and three terminal surface makes the heat protection effectual, and the cost is lower.
Further, referring to fig. 1, the rudder body 1 includes a rudder surface 2 and a fender 3;
the second end surface of the tiller 4 is fixedly connected with the first end surface of the guard plate 3, and the second end surface of the guard plate 3 is fixedly connected with the control surface 2.
In this embodiment, rudder body 1 includes rudder face 2 and backplate 3, the material of rudder face 2 includes graphite etc, the direction change that the engine nozzle internal spun gas passes through 2 redirecting of rudder face makes the rocket, 3 both sides of backplate are circular-arc face that sets up, make the air current be difficult to erode backplate 3, backplate 3 laminates the surface at the rocket body, the second terminal surface of tiller 4 and the first terminal surface fixed connection of backplate 3, the second terminal surface and the 2 fixed connection of rudder face of backplate 3, make rudder body 1 can reduce the scouring and destruction of the internal components and parts of heat current to the rocket body.
Further, referring to fig. 1, the tiller 4 is integrally constructed with the control surface 2.
In the embodiment, the rudder stock 4 and the control surface 2 are integrally constructed, so that the quality of the gas rudder is reduced, and the heat protection and heat sealing performance of the gas rudder are improved.
Further, referring to fig. 1, the shape of the control surface 2 includes an airfoil.
In the present embodiment, the shape of the control surface 2 includes a section shape, also called an aerofoil section or a blade section, parallel to the symmetry plane of the aircraft or perpendicular to the leading edge (or the line connecting the chord length points of 1/4) on an aerofoil, an aircraft wing, a tail wing, a missile wing surface, a helicopter rotor blade and a propeller blade, and the section of the aerofoil control surface 2 includes a front wedge plate shape.
Further, referring to fig. 1, the rudder key 7 includes a key body 6 and at least one key groove 5 for connecting with the rocket body, the key body 6 is fixedly connected with the first end face of the tiller 4, and the at least one key groove 5 is disposed on the key body 6.
In this embodiment, rudder key 7 includes the key body 6 and at least one keyway 5 that is used for being connected with the rocket body, keyway 5 is the through-hole of connecting key body 6 both sides face, the quantity of through-hole is three, evenly distributed is on the key body 6, connect key body 6 left and right sides face, the shape of key body 6 is the cube, the side contains the circular arc, make key body 6 be connected with the rocket body more easily, the middle part fixed connection of the first terminal surface of key body 6 and tiller 4, three keyway 5 all sets up on key body 6, the interval of two adjacent keyways 5 equals in the three keyway 5.
Based on the same technical conception, the embodiment of the present application further provides a gas vane connecting assembly, including: the rudder shaft is connected with a rudder key 7 key.
In this embodiment, rudder axle and 7 key connections of rudder key, the key-type connection realizes through the key that the circumference between axle and the epaxial part is fixed in order to transmit motion and torque, wherein, some types can also realize axial fixity and transmission axial force, some types can realize the axial and move the hookup for the rudder axle can drive rudder key 7 and rotate.
Based on the same technical concept, the embodiment of the present application further provides a rocket, including: rocket bodies and gas rudders, and rudder keys 7 included in the gas rudders are fixed on the rocket bodies.
In this embodiment, the rocket includes gas rudder and rocket body, and the gas rudder sets up in the engine nozzle that rocket body contains, is located the bottom of engine nozzle, and rudder key 7 is fixed on rocket body.
Further, referring to fig. 1, the rocket body is provided with an accommodating groove corresponding to the step end face, and the accommodating groove is attached to the step end face.
In this embodiment, be equipped with the holding tank that corresponds with the ladder terminal surface on the rocket body, the holding tank is multilayer rocket ladder terminal surface, and the terminal surface that is close to the contrary ladder terminal surface of multilayer of gas rudder is greater than the contrary ladder terminal surface of multilayer rocket of keeping away from the gas rudder, and the distance of every terminal surface equals, and every holding tank is laminated with the ladder terminal surface mutually.
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. A gas vane, comprising: the rocket comprises a rudder body (1), a rudder stock (4) and a rudder key (7) used for being connected with a rocket body;
the first terminal surface of tiller (4) is the ladder terminal surface, rudder key (7) are connected the ladder terminal surface top of tiller (4), the top of ladder terminal surface is less than the bottom, the ladder terminal surface of tiller (4) with the laminating of rocket body, the second terminal surface of tiller (4) with rudder body (1) is connected.
2. Gas rudder according to claim 1, characterised in that the stepped end surface comprises a plurality of end surfaces, each of which is circular in shape, which end surfaces taper in the direction of the rudder key (7) along the rudder body (1).
3. The gas vane of claim 2, wherein the plurality of end surfaces is three.
4. Gas rudder according to claim 3, characterised in that the rudder body (1) comprises a rudder face (2) and a fender (3);
the second end surface of the tiller (4) is fixedly connected with the first end surface of the guard plate (3), and the second end surface of the guard plate (3) is fixedly connected with the control surface (2).
5. Gas rudder according to claim 4, characterised in that the rudder stock (4) is of one-piece construction with the control surface (2).
6. Gas rudder according to claim 5, characterised in that the shape of the control surface (2) comprises an airfoil profile.
7. Gas rudder according to claim 6, characterised in that the rudder key (7) comprises a key body fixedly connected with the first end face of the tiller (4) and at least one key slot (5) for connection with a rocket body, said at least one key slot (5) being provided on the key body.
8. Gas rudder connection assembly, characterised in that it comprises a rudder shaft and a gas rudder according to any of the claims 1-7, the rudder shaft being keyed with the rudder key (7).
9. A rocket, comprising a rocket body and a gas rudder according to any one of claims 1-8, said gas rudder comprising a rudder key (7) fixed to said rocket body.
10. The rocket according to claim 9, wherein the rocket body is provided with a receiving groove corresponding to the step end surface, and the receiving groove is attached to the step end surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920555171.9U CN210526883U (en) | 2019-04-22 | 2019-04-22 | Gas rudder, gas rudder connecting assembly and rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920555171.9U CN210526883U (en) | 2019-04-22 | 2019-04-22 | Gas rudder, gas rudder connecting assembly and rocket |
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| Publication Number | Publication Date |
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| CN210526883U true CN210526883U (en) | 2020-05-15 |
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| CN201920555171.9U Active CN210526883U (en) | 2019-04-22 | 2019-04-22 | Gas rudder, gas rudder connecting assembly and rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116538871A (en) * | 2023-07-05 | 2023-08-04 | 北京凌空天行科技有限责任公司 | Novel gas rudder and verification method thereof |
| CN116853481A (en) * | 2023-07-10 | 2023-10-10 | 北京新风航天装备有限公司 | Folding fixing device of air rudder |
-
2019
- 2019-04-22 CN CN201920555171.9U patent/CN210526883U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116538871A (en) * | 2023-07-05 | 2023-08-04 | 北京凌空天行科技有限责任公司 | Novel gas rudder and verification method thereof |
| CN116538871B (en) * | 2023-07-05 | 2023-10-20 | 北京凌空天行科技有限责任公司 | Novel gas rudder and verification method thereof |
| CN116853481A (en) * | 2023-07-10 | 2023-10-10 | 北京新风航天装备有限公司 | Folding fixing device of air rudder |
| CN116853481B (en) * | 2023-07-10 | 2024-01-05 | 北京新风航天装备有限公司 | Folding fixing device of air rudder |
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