CN108180791A - Split type rudder face rudderpost structure and guided missile - Google Patents
Split type rudder face rudderpost structure and guided missile Download PDFInfo
- Publication number
- CN108180791A CN108180791A CN201810020179.5A CN201810020179A CN108180791A CN 108180791 A CN108180791 A CN 108180791A CN 201810020179 A CN201810020179 A CN 201810020179A CN 108180791 A CN108180791 A CN 108180791A
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- rudder face
- rudderpost
- split type
- auricles
- steering engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
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- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
The present invention provides a kind of split type rudder face rudderpost structure and guided missiles, are related to weapon technologies field.The split type rudder face rudderpost structure includes rudder face and rudderpost；The both sides at the middle part of one end of told rudder face offer auricle slot；The rudderpost includes pedestal, and one end of the pedestal is affixed there are two auricle, and the other end is connected with spline；Two auricles are inlaid in respectively in two auricle slots；Two auricles are detachably connected with the rudder face.The guided missile includes split type rudder face rudderpost structure as described above, further includes steering engine；The output terminal of the steering engine is provided with keyway, and the spline is inserted into the keyway；The output terminal of the pedestal and the steering engine is affixed.The present invention solves the problems, such as that existing rudderpost rudder face structure difficulty of processing is not greatly and easy to assemble.
Description
Technical field
The present invention relates to weapon technologies field, more particularly, to a kind of split type rudder face rudderpost structure and guided missile.
Background technology
Guided missile is rotated in flight course centered rudder around rudderpost, to generate control moment so that and guided missile can adjust posture, according to
The ballistic trajectory flight specified.At present, most of rudder faces are rotated using servos control, but its form is often that rudderpost is with rudder face
One, complicated, difficulty of processing is big, of high cost；Or independent rudder face and rudderpost are connected as entirety by way of rivet, tool
There is the defects of non-dismountable.
In addition, small part air-to-air missile is using novel purely mechanic device --- gyro rudder controls its rolling, although reaching
The effect for reducing Mechatronic control system volume has been arrived, but has also had lost certain mobility.
Based on this, the present invention provides a kind of split type rudder face rudderpost structure and guided missiles to solve the technical issues of above-mentioned.
Invention content
The purpose of the present invention is to provide a kind of split type rudder face rudderpost structures, are added with solving existing rudderpost rudder face structure
The problem of work difficulty is big and not easy to assemble.
The present invention also aims to provide a kind of guided missile, for solving above-mentioned technical problem.
Based on above-mentioned first purpose, the present invention provides a kind of split type rudder face rudderpost structure, including rudder face and rudderpost；
The both sides at the middle part of one end of told rudder face offer auricle slot；
The rudderpost includes pedestal, and one end of the pedestal is affixed there are two auricle, and the other end is connected with spline；
Two auricles are inlaid in respectively in two auricle slots；
Two auricles are detachably connected with the rudder face.
Optionally, the lateral surface of the lateral surface of two auricles side corresponding with the rudder face respectively is concordant.
Optionally, the through-hole of multiple perforations, the phase of two auricles are provided between the slot bottom of two auricle slots
Position is answered to be respectively arranged with counter sink, two auricles and the rudder face are connected by screw, and the screw is located at described heavy
In head bore and the through-hole.
Optionally, the through-hole is four, and four through-holes are uniformly distributed in the slot bottom of the auricle slot.
Optionally, it is opened up on the seat surface of the pedestal there are four counter sink, four counter sinks are uniformly distributed.
Optionally, the both ends of slot formed between two auricles offer reaming respectively, two reamings and its
In two countersunk head hole sites correspond.
Optionally, the rudder face uses shuttle-type.
Optionally, the spline uses outer-hexagonal rectangular spline.
Based on above-mentioned second purpose, the present invention provides a kind of guided missile, the guided missile includes split type rudder as described above
Face rudderpost structure, further includes steering engine；
The output terminal of the steering engine is provided with keyway, and the spline is inserted into the keyway；
The output terminal of the pedestal and the steering engine is affixed.
Optionally, there are four the steering engine settings, four steering engines are uniformly distributed around the central axis of guided missile；Accordingly
, the split type rudder face rudderpost structure is also equipped with four groups, is correspondingly connected with respectively with four steering engines.
The split type rudder face rudderpost structure provided by the invention is designed suitable for the rudder face rudderpost of middle-size and small-size guided missile.Rudder
Face is connect by rudderpost with steering engine, can be rotated around rudderpost so as to fulfill guided missile attitude control.The split type rudder face rudderpost mechanism work
When by attitude control system send out instruction control steering engine rotation, be further driven to rudderpost and rudder face rotation, so as to fulfill posture control
The function of system.
The split type rudder face rudderpost structure provided by the invention, using independent rudderpost, rudderpost and rudder face are individual part,
Between the two using dismountable connection.It is connected by double-deck rectangle auricle with screw type of attachment with rudder face, the other end uses
Rectangular spline is connect with steering engine.Device overall structure is simple, is readily disassembled and mobility is higher.Suitable for middle-size and small-size missile aerodynamic
Rudder face designs, and structure is connected firmly, and parts are few, and reliability is high.Rudder face and rudderpost structure type are simple, can be separately machined,
The difficulty of processing is greatly reduced, advantageously ensures that higher parts machining quality and relatively low processing cost.Entire rudder
The steering engine that face can be controlled in posture control system is freely rotated under driving, and larger control moment is provided for missile attitude control, is had
The advantages of mobility is high.Its rudder face and rudderpost such as are connected by screw at the modes, are readily disassembled, and those skilled in the art can be
Various deformations or amendments are made in the scope of the claims, rudder face of different shapes can be extended to so that rudderpost design can mould
Block, it is preferably compatible with various forms of rudder faces.
Description of the drawings
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution of the prior art
Embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, in being described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, can also be obtained according to these attached drawings other attached drawings.
Fig. 1 is the assembling stereogram of split type rudder face rudderpost structure provided in an embodiment of the present invention；
Fig. 2 is the axonometric drawing of the rudder face described in Fig. 1；
Fig. 3 is the axonometric drawing of the rudderpost described in Fig. 1；
Fig. 4 is the bottom view of the rudderpost described in Fig. 3.
Icon：1- rudder faces；2- rudderposts；101- through-holes；102- auricle slots；201- auricles；202- counter sinks；203- countersunk heads
Hole；204- reamings；205- splines；206- pedestals.
Specific embodiment
Technical scheme of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's all other embodiments obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instructions such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Convenient for the description present invention and simplify description rather than instruction or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is only used for description purpose, and it is not intended that instruction or hint relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected or be integrally connected；It can
To be mechanical connection or be electrically connected；It can be directly connected, can also be indirectly connected by intermediary, Ke Yishi
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
Split type rudder face rudderpost constructive embodiment one
As shown in Figs 1-4, a kind of split type rudder face rudderpost structure, the split type rudder face rudder are provided in the present embodiment
Axle construction includes rudder face 1 and rudderpost 2；
The both sides at the middle part of one end of told rudder face 1 offer auricle slot 102；
The rudderpost 2 includes pedestal 206, and one end of the pedestal 206 is affixed, and there are two auricles 201, and the other end is connected with
Spline 205；
Two auricles 201 are inlaid in respectively in two auricle slots 102；
Two auricles 201 are detachably connected with the rudder face 1.
Preferably, the pedestal 206 uses round base 206.
The split type rudder face rudderpost structure provided by the invention is designed suitable for 1 rudderpost 2 of rudder face of middle-size and small-size guided missile.
Rudder face 1 is connect by rudderpost 2 with steering engine, can be rotated around rudderpost 2 so as to fulfill guided missile attitude control.1 rudderpost of split type rudder face, 2 machine
Instruction control steering engine rotation is sent out by attitude control system when structure works, rudderpost 2 is further driven to and rudder face 1 rotates, so as to real
The function of existing gesture stability.
The split type rudder face rudderpost structure provided by the invention, using independent rudderpost 2, rudderpost 2 and rudder face 1 are independent zero
Part, between the two using dismountable connection.It is connected by double-deck rectangle auricle 201 with screw type of attachment and rudder face 1, it is another
End is connect using rectangular spline 205 with steering engine.Device overall structure is simple, is readily disassembled and mobility is higher.Suitable for medium and small
Type missile aerodynamic rudder face 1 designs, and structure is connected firmly, and parts are few, and reliability is high.Rudder face 1 and the letter of 2 structure type of rudderpost
It is single, can be separately machined, greatly reduce the difficulty of processing, advantageously ensure that higher parts machining quality and it is relatively low plus
Work cost.The steering engine that entire rudder face 1 can be controlled in posture control system is freely rotated under driving, and is provided for missile attitude control larger
Control moment has the advantages that mobility is high.Its rudder face 1 and rudderpost 2 such as are connected by screw at the modes, and connection is effectively reliable,
It is readily disassembled, those skilled in the art can make various deformations or amendments within the scope of the claims, can extend to not
The rudder face 1 of similar shape so that rudderpost 2 design can modularization, it is preferably compatible with various forms of rudder faces 1.
Such as Fig. 1, in the alternative of the present embodiment, the lateral surface of two auricles 201 is corresponding with the rudder face 1 respectively
The lateral surface of side is concordant.
Made in order to not influence the aerodynamic configuration of whole missile wing completely flat with 1 upper surface of rudder face in auricle 201 outer surface in top
Neat bevel-faced form, 201 outer surface of lower part auricle are similary.
Such as Fig. 2,3, in the alternative of the present embodiment, multiple pass through is provided between the slot bottom of two auricle slots 102
Logical through-hole 101, the corresponding position of two auricles 201 are respectively arranged with counter sink 202, two auricles 201 and institute
It states rudder face 1 to be connected by screw, the screw is located in the counter sink 202 and the through-hole 101, and the screw passes through described
Counter sink 202 and the through-hole 101 realize being connected for rudder face 1 and rudderpost 2.
2 screw of rudder face 1 of rudderpost is connected, and to ensure bonding strength, should at least use the sunk screw of M6.
Preferably, the through-hole 101 is four, and four through-holes 101 uniformly divide in the slot bottom of the auricle slot 102
Cloth.
Four through-holes 101 are easy to process in criss-cross symmetrical, can also effectively fix rudderpost 2 and steering engine.
Such as Fig. 3, in the alternative of the present embodiment, opened up on the seat surface of the pedestal 206 there are four counter sink 203, four
A counter sink 203 is uniformly distributed.
Pedestal 206 is provided with counter sink 203, to being connected for rudderpost 2 and steering engine, is connected using screw, easy to disassemble.
Further, the both ends of slot formed between two auricles 201 offer reaming 204 respectively, described in two
Reaming 204 is corresponded with 203 position of counter sink described in two of which.
It is to enter the tools such as screw and screwdriver for convenience to open up reaming 204, facilitates fixed and uses.
Such as Fig. 1,2, in the alternative of the present embodiment, the rudder face 1 uses shuttle-type.
Rudder face 1 is conducive to reduce air drag, the flying speed of the lifting of missile using shuttle-type.
Such as Fig. 3,4, in the alternative of the present embodiment, the spline 205 uses outer-hexagonal rectangular spline.
Type higher, driving that is less easy to fall off and facilitating steering engine are completely embedded using the spline 205 of outer-hexagonal rectangle.
Guided missile embodiment
This embodiment offers a kind of guided missile, the guided missile includes split type rudder face rudderpost structure as described above, also wraps
Include steering engine；
The output terminal of the steering engine is provided with keyway, and the spline 205 is inserted into the keyway；
The output terminal of the pedestal 206 and the steering engine is affixed.Preferably, there are four the steering engine settings, described in four
Steering engine is uniformly distributed around the central axis of guided missile；Correspondingly, the split type rudder face rudderpost structure is also equipped with four groups, respectively
It is correspondingly connected with four steering engines.
The split type rudder face rudderpost structure provided by the invention is designed suitable for 1 rudderpost 2 of rudder face of middle-size and small-size guided missile.
Rudder face 1 is connect by rudderpost 2 with steering engine, can be rotated around rudderpost 2 so as to fulfill guided missile attitude control.1 rudderpost of split type rudder face, 2 machine
Instruction control steering engine rotation is sent out by attitude control system when structure works, rudderpost 2 is further driven to and rudder face 1 rotates, so as to real
The function of existing gesture stability.
Finally it should be noted that：It is obvious to a person skilled in the art that the application is not limited to above-mentioned exemplary implementation
The details of example, and in the case of without departing substantially from spirit herein or essential characteristic, can realize in other specific forms
The application.Therefore, in all respects, the present embodiments are to be considered as illustrative and not restrictive, this Shen
Range please is indicated by the appended claims rather than the foregoing description, it is intended that by containing in the equivalent requirements of the claims is fallen
All changes in justice and range are included in the application.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in each embodiment can also be properly combined, forms those skilled in the art
The other embodiment being appreciated that.
Claims (10)
1. a kind of split type rudder face rudderpost structure, which is characterized in that including rudder face and rudderpost；
The both sides at the middle part of one end of told rudder face offer auricle slot；
The rudderpost includes pedestal, and one end of the pedestal is affixed there are two auricle, and the other end is connected with spline；
Two auricles are inlaid in respectively in two auricle slots；
Two auricles are detachably connected with the rudder face.
2. split type rudder face rudderpost structure according to claim 1, which is characterized in that the lateral surface of two auricles point
The lateral surface of other side corresponding with the rudder face is concordant.
3. split type rudder face rudderpost structure according to claim 1, which is characterized in that the slot bottom of two auricle slots it
Between be provided with the through-holes of multiple perforations, the corresponding positions of two auricles is respectively arranged with counter sink, two auricles and
The rudder face is connected by screw, and the screw is located in the counter sink and the through-hole.
4. split type rudder face rudderpost structure according to claim 3, which is characterized in that the through-hole is four, four institutes
The slot bottom that through-hole is stated in the auricle slot is uniformly distributed.
5. split type rudder face rudderpost structure according to claim 1, which is characterized in that offered on the seat surface of the pedestal
Four counter sinks, four counter sinks are uniformly distributed.
6. split type rudder face rudderpost structure according to claim 5, which is characterized in that formed between two auricles
The both ends of slot offer reaming respectively, and two reamings are corresponded with countersunk head hole site described in two of which.
7. split type rudder face rudderpost structure according to claim 1, which is characterized in that the rudder face uses shuttle-type.
8. split type rudder face rudderpost structure according to claim 1, which is characterized in that the spline uses outer-hexagonal rectangle
Spline.
9. a kind of guided missile, which is characterized in that the guided missile includes such as the split type rudder face rudderpost of claim 1-8 any one of them
Structure further includes steering engine；
The output terminal of the steering engine is provided with keyway, and the spline is inserted into the keyway；
The output terminal of the pedestal and the steering engine is affixed.
10. guided missile according to claim 9, which is characterized in that there are four the steering engine settings, and four steering engines surround
The central axis of guided missile is uniformly distributed；Correspondingly, the split type rudder face rudderpost structure is also equipped with four groups, respectively with four institutes
Steering engine is stated to be correspondingly connected with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810020179.5A CN108180791A (en) | 2018-01-09 | 2018-01-09 | Split type rudder face rudderpost structure and guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810020179.5A CN108180791A (en) | 2018-01-09 | 2018-01-09 | Split type rudder face rudderpost structure and guided missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108180791A true CN108180791A (en) | 2018-06-19 |
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ID=62550339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810020179.5A Pending CN108180791A (en) | 2018-01-09 | 2018-01-09 | Split type rudder face rudderpost structure and guided missile |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631682A (en) * | 2019-02-22 | 2019-04-16 | 西北工业大学 | A kind of missile wing single-shaft-rotation development system and method for deploying considering aileron driving |
| CN111664756A (en) * | 2020-05-12 | 2020-09-15 | 上海机电工程研究所 | Structure suitable for air rudder and steering engine system connection |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659783B (en) * | 2008-12-26 | 2014-01-08 | 北京精密机电控制设备研究所 | Eccentric lever type servo control mechanism |
| CN103612748A (en) * | 2013-10-12 | 2014-03-05 | 中国运载火箭技术研究院 | Positioning drive mechanism for aircraft full-movement V tail |
| CN204757831U (en) * | 2015-06-10 | 2015-11-11 | 华中科技大学 | Guided missile rudder stock |
| EP3032212A1 (en) * | 2014-12-11 | 2016-06-15 | MBDA Deutschland GmbH | Rudder system |
-
2018
- 2018-01-09 CN CN201810020179.5A patent/CN108180791A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659783B (en) * | 2008-12-26 | 2014-01-08 | 北京精密机电控制设备研究所 | Eccentric lever type servo control mechanism |
| CN103612748A (en) * | 2013-10-12 | 2014-03-05 | 中国运载火箭技术研究院 | Positioning drive mechanism for aircraft full-movement V tail |
| EP3032212A1 (en) * | 2014-12-11 | 2016-06-15 | MBDA Deutschland GmbH | Rudder system |
| CN204757831U (en) * | 2015-06-10 | 2015-11-11 | 华中科技大学 | Guided missile rudder stock |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631682A (en) * | 2019-02-22 | 2019-04-16 | 西北工业大学 | A kind of missile wing single-shaft-rotation development system and method for deploying considering aileron driving |
| CN109631682B (en) * | 2019-02-22 | 2024-01-19 | 西北工业大学 | Missile wing single-shaft rotation unfolding system and unfolding method considering aileron driving |
| CN111664756A (en) * | 2020-05-12 | 2020-09-15 | 上海机电工程研究所 | Structure suitable for air rudder and steering engine system connection |
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Application publication date: 20180619 |
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