CN106643340A - Missile control surface space linkage type control mechanism - Google Patents
Missile control surface space linkage type control mechanism Download PDFInfo
- Publication number
- CN106643340A CN106643340A CN201610961206.XA CN201610961206A CN106643340A CN 106643340 A CN106643340 A CN 106643340A CN 201610961206 A CN201610961206 A CN 201610961206A CN 106643340 A CN106643340 A CN 106643340A
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- China
- Prior art keywords
- rudder
- rudder stock
- fixed
- hole
- stock
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Classifications
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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
- F42B15/01—Arrangements thereon for guidance or control
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Steering Controls (AREA)
Abstract
The invention discloses a missile control surface space linkage type control mechanism to solve the problem that steering engine installation requires occupying more missile body space currently. The missile control surface space linkage type control mechanism is characterized in that each first cockpit and an adjacent second cockpit are fixed through a connecting compartment; the first cockpits are connected with first rudders; the second cockpits are connected with second rudders; a first rudder shaft fixed to one first rudder and one first cockpit form a rotation pair correspondingly; rotation blocks are fixed to the first rudder shafts; a sliding rod and a second through hole of one rotation block form a sliding pair correspondingly; a guide rail and a sliding block with a boss formed at the top form a sliding pair correspondingly; the two ends of a first connecting rod are hinged to one boss and one sliding rod correspondingly; one end of a second connecting rod and one sliding block are fixed correspondingly; a nut block fixed to the other end of each second connecting rod and a screw rod form a helical pair correspondingly; one end of each screw rod is connected with an output shaft of a second steering engine through a coupler; a second rudder shaft of each second rudder and a third through hole of the corresponding second cockpit form a rotation pair; and an output shaft of a first steering engine and one second rudder shaft are fixed correspondingly. According to the missile control surface space linkage type control mechanism, the steering engines of certain rudders are moved to the cockpits where the other rudders are located, and the size occupation of a missile body is reduced.
Description
Technical field
The invention belongs to weaponry field, and in particular to a kind of guided missile rudder face space coordinated type controlling organization.
Background technology
Guided missile rudder face rotates in flight course around rudderpost, to adjust the controling power of guided missile pose and generation to guided missile
(torque), makes guided missile adjust flight path in time, reaches the purpose of precision strike.At present, most of rudder faces are mainly by steering wheel control
System rotation, and steering wheel occupies the larger volume of body in body, is ensured by increasing the size of body during design
The installing space of the relevant apparatus such as steering wheel.With the continuous development of missilery, the position of appearance and size and steering wheel to guided missile,
Volume is put forward higher requirement, and developing a kind of interior guided missile rudder plane controlling mechanism for not placing steering wheel of some rudder stocks has its important
Meaning.
The content of the invention
The purpose of the present invention is the problem for current steering wheel more occupancy body space in placement, there is provided a kind of guided missile
Rudder face space coordinated type controlling organization, can be effectively saved installing space on the premise of the existing aerodynamic configuration of body is kept, and enter
And efficiently reduce occupancy of the steering wheel placement to body volume.
The present invention employs the following technical solutions realization：
The present invention includes rudder stock one and rudder stock two；Quantity identical rudder stock one and rudder stock two are evenly distributed in body tail
Portion, rudder stock one and rudder stock two are fixedly connected with body；Each rudder stock one is fixed by connecting cabin with an adjacent rudder stock two and connected
Connect, all connecting cabins are circumferential uniform along body；Described rudder stock one is connected with rudder one, and rudder stock two is connected with rudder two.
It is secondary that the rudderpost one being fixed on rudder one constitutes rotation with the through hole one and blind hole of rudder stock one；Described through hole one and blind hole
It is coaxially disposed, and through hole one is opened in the top of groove one of rudder stock one, blind hole is opened in the bottom of groove one of rudder stock one；Moving block
It is fixed on rudderpost one；Slide bar constitutes sliding pair with the through hole two of moving block, and the axis horizontal of through hole two is arranged；Top is provided with convex
The slide block of platform constitutes sliding pair with guide rail, and the two ends of the guide rail are bearing in respectively on bearing block one and bearing block two；Bearing block
One and bearing block two be each attached to the bottom of groove one of rudder stock one；The two ends of connecting rod one are hinged respectively with boss and slide bar；Connecting rod two
One end fix with slide block；The nut block and leading screw for being fixed on the other end of connecting rod two constitutes screw pair；Described leading screw two ends point
It is not bearing on bearing block three and bearing block four；One end of leading screw is connected with the output shaft of steering wheel two by shaft coupling；Steering wheel two,
Bearing block three and bearing block four are fixed with the bottom of groove two of rudder stock two.The rudderpost two of rudder two and the through hole three of rudder stock two
Constitute and rotate secondary, through hole three is opened in the top of groove two of rudder stock two；The top of groove two of rudder stock two is fixed with steering wheel frame；Steering wheel
One is fixed on steering wheel frame, and output shaft and the rudderpost two of steering wheel one are fixed.
Described connecting cabin is fastened on afterbody.
Described connecting rod two is in circular arc.
Described rudder stock one and rudder stock two is two.
Beneficial effects of the present invention：
1st, the screw pair between leading screw and nut block is passed through into the sliding pair that connecting rod two is converted between slide block and guide rail, then is led to
The rotation that sliding pair is converted into rudderpost one for connecting rod one and slide block etc. is crossed, motion conversion spatially is realized；
2nd, the control steering wheel of some rudders is moved in the rudder stock that another rudder control steering wheel is located, so that
Steering wheel is not placed in some rudder stocks, the occupancy to body volume is reduced, space availability ratio is lifted, met to Missile Actuator
Position and volume propose the guided missile rudder plane controlling mechanism demand of particular/special requirement.
Description of the drawings
Fig. 1 is the overall structure stereogram of the present invention；
Fig. 2 is the schematic diagram that rudder one is connected with rudder stock two by connecting rod two in the present invention；
Fig. 3 is the end view of the present invention；
Fig. 4 is the partial enlarged drawing in Fig. 1 at A；
Fig. 5 is the component assembly stereogram in rudder stock two.
In figure：1st, rudder stock one, 1a, through hole one, 1b, groove one, 1c, blind hole, 2, rudder one, 2a, rudderpost one, turn 2b
Motion block, 2c, through hole two, 3, connecting cabin, 4, rudder stock two, 4a, through hole three, 4b, groove two, 5, rudder two, 5a, rudderpost two, 6,
Slide bar, 7, connecting rod one, 8, bearing block one, 9, guide rail, 10a, slide block, 10b, connecting rod two, 10c, boss, 10d, nut block, 11, axle
Bearing two, 12, steering wheel one, 13, screw mandrel, 14, bearing block three, 15, bearing block four, 16, shaft coupling, 17, steering wheel two, 18, steering wheel
Frame.
Specific embodiment
Below in conjunction with the accompanying drawings and embodiment the present invention will be further described.
As shown in Fig. 1～Fig. 5, a kind of guided missile rudder face space coordinated type controlling organization, including rudder stock 1 and rudder stock 24；Two
Individual rudder stock 1 and two rudder stocks 24 are uniformly distributed along the circumference in afterbody, and are fixedly connected with body；Two connecting cabins 3 are fastened
In afterbody, each two ends of connecting cabin 3 is fixedly connected respectively with a rudder stock 1 and a rudder stock 24；Rudder stock 1 connects
There is rudder 1, rudder stock 24 is connected with rudder 25；Each rudder 1 passes through a connecting rod with a corresponding rudder stock 24
Two 10b connect.In Fig. 1, v is the speed of service of body.
As shown in figure 4, the 1a of through hole one and the equal structure of blind hole 1c of the 2a of rudderpost one being fixed on rudder 1 and rudder stock 1
It is secondary into rotating；The 1a of through hole one is coaxially disposed with blind hole 1c, and the 1a of through hole one is opened in the 1b of groove one tops of rudder stock 1, blind hole
1c is opened in the bottom of groove one of rudder stock 1；Moving block 2b is fixed on the 2a of rudderpost one；The through hole of slide bar 6 and moving block 2b
Two 2c constitute sliding pair, and the axis horizontal of the 2c of through hole two is arranged；Top is provided with the slide block 10a of boss 10c and guide rail 9 constitutes slip
Pair, the two ends of guide rail 9 are bearing in respectively on bearing block 1 and bearing block 2 11；Bearing block 1 and bearing block 2 11 are each attached to
The bottom of groove one of rudder stock 1；The two ends of connecting rod 1 are hinged respectively with boss 10c with slide bar 6；One end of the 10b of connecting rod two and slide block
10a is fixedly connected.
As shown in figure 5, the other end of the 10b of connecting rod two is fixedly connected with nut block 10d, nut block 10d passes through with leading screw 13
Screw pair connects；The two ends of leading screw 13 are bearing in respectively on bearing block 3 14 and bearing block 4 15；One end of leading screw 13 and steering wheel two
17 output shaft is connected by shaft coupling 16；Steering wheel 2 17, bearing block 3 14 and bearing block 4 15 with the groove two of rudder stock 24
4b bottoms are fixedly connected.
As shown in Figure 1, Figure 2, Figure 5, the 5a of rudderpost two of rudder 25 is constituted with the 4a of through hole three of rudder stock 24 and is rotated secondary, is led to
The 4a of hole three is opened in the top of groove two of rudder stock 24；The top of groove two of rudder stock 24 is fixed with steering wheel frame 18；Steering wheel 1 is consolidated
It is scheduled on steering wheel frame 18, the output shaft of steering wheel 1 is fixedly connected with the 5a of rudderpost two.
The operation principle of the guided missile rudder face space coordinated type controlling organization：
As shown in Fig. 1～5, steering wheel 2 17 is rotated and drives screw mandrel 13 to rotate；Nut block 10d is done directly under the driving of screw mandrel 13
Line is moved, and nut block 10d is slided on the rail 9 by the 10b of connecting rod two band movable slider 10a；The mobile drivening rod one of slide block 10a
7 rotate, and slide bar 6 slides under the drive of connecting rod 7 relative to the 2c of through hole two, and the relative slip between slide bar 6 and the 2c of through hole two is ordered about
The 2a of rudderpost one is rotated so that rudder 1 is rotated；The rotation of steering wheel 1 drives the 5a of rudderpost two to rotate so that 25 turns of rudder
It is dynamic；In addition, the rotation direction of change steering wheel 1 and steering wheel 2 17 can change the rotation direction of rudder 1 and rudder 25.
Claims (4)
1. a kind of guided missile rudder face space coordinated type controlling organization, including rudder stock one and rudder stock two, it is characterised in that：Quantity identical
Rudder stock one and rudder stock two are evenly distributed in afterbody, and rudder stock one and rudder stock two are fixedly connected with body；Each rudder stock one
It is fixedly connected by connecting cabin with an adjacent rudder stock two, all connecting cabins are circumferential uniform along body；Described rudder stock one connects
There is rudder one, rudder stock two is connected with rudder two；It is fixed on rudderpost one on rudder one and the through hole one of rudder stock one and blind
It is secondary that hole constitutes rotation；Described through hole one is coaxially disposed with blind hole, and through hole one is opened in the top of groove one of rudder stock one, blind
Hole is opened in the bottom of groove one of rudder stock one；Moving block is fixed on rudderpost one；Slide bar is constituted with the through hole two of moving block and slided
Pair, the axis horizontal of through hole two is arranged；Top is provided with the slide block of boss and guide rail constitutes sliding pair, the two ends difference of the guide rail
It is bearing on bearing block one and bearing block two；Bearing block one and bearing block two are each attached to the bottom of groove one of rudder stock one；Connecting rod
One two ends are hinged respectively with boss and slide bar；One end of connecting rod two is fixed with slide block；It is fixed on the nut block of the other end of connecting rod two
Screw pair is constituted with leading screw；Described leading screw two ends are bearing in respectively on bearing block three and bearing block four；One end of leading screw and rudder
The output shaft of machine two is connected by shaft coupling；Steering wheel two, bearing block three and bearing block four are consolidated with the bottom of groove two of rudder stock two
It is fixed；The rudderpost two of rudder two is constituted with the through hole three of rudder stock two and rotates secondary, and through hole three is opened in the top of groove two of rudder stock two；
The top of groove two of rudder stock two is fixed with steering wheel frame；Steering wheel one is fixed on steering wheel frame, and output shaft and the rudderpost two of steering wheel one are consolidated
It is fixed.
2. a kind of guided missile rudder face space coordinated type controlling organization according to claim 1, it is characterised in that：Described connection
Cabin is fastened on afterbody.
3. a kind of guided missile rudder face space coordinated type controlling organization according to claim 1, it is characterised in that：Described connecting rod
Two is in circular arc.
4. a kind of guided missile rudder face space coordinated type controlling organization according to claim 1, it is characterised in that：Described rudder stock
One and rudder stock two be two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961206.XA CN106643340B (en) | 2016-10-27 | 2016-10-27 | A kind of guided missile rudder face space coordinated type controlling organization |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961206.XA CN106643340B (en) | 2016-10-27 | 2016-10-27 | A kind of guided missile rudder face space coordinated type controlling organization |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106643340A true CN106643340A (en) | 2017-05-10 |
| CN106643340B CN106643340B (en) | 2018-01-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610961206.XA Active CN106643340B (en) | 2016-10-27 | 2016-10-27 | A kind of guided missile rudder face space coordinated type controlling organization |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935507A (en) * | 2014-04-04 | 2014-07-23 | 北京航空航天大学 | Self-driven intelligent all-dynamic air rudder |
| CN104596362A (en) * | 2013-11-01 | 2015-05-06 | 苏诗洋 | Multipurpose comprehensive short-range full-automatic orbital transfer tactical missile device |
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| CN104712459A (en) * | 2013-12-12 | 2015-06-17 | 上海机电工程研究所 | Solid rocket power control device and control method |
| CN206330489U (en) * | 2016-10-27 | 2017-07-14 | 浙江理工大学 | Guided missile rudder face space coordinated type controlling organization |
-
2016
- 2016-10-27 CN CN201610961206.XA patent/CN106643340B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596362A (en) * | 2013-11-01 | 2015-05-06 | 苏诗洋 | Multipurpose comprehensive short-range full-automatic orbital transfer tactical missile device |
| CN104712459A (en) * | 2013-12-12 | 2015-06-17 | 上海机电工程研究所 | Solid rocket power control device and control method |
| CN103935507A (en) * | 2014-04-04 | 2014-07-23 | 北京航空航天大学 | Self-driven intelligent all-dynamic air rudder |
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| CN206330489U (en) * | 2016-10-27 | 2017-07-14 | 浙江理工大学 | Guided missile rudder face space coordinated type controlling organization |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106643340B (en) | 2018-01-19 |
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