CN106643340B - A kind of guided missile rudder face space coordinated type controlling organization - Google Patents
A kind of guided missile rudder face space coordinated type controlling organization Download PDFInfo
- Publication number
- CN106643340B CN106643340B CN201610961206.XA CN201610961206A CN106643340B CN 106643340 B CN106643340 B CN 106643340B CN 201610961206 A CN201610961206 A CN 201610961206A CN 106643340 B CN106643340 B CN 106643340B
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- Prior art keywords
- rudder
- rudder stock
- fixed
- stock
- steering wheel
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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
Abstract
The invention discloses a kind of guided missile rudder face space coordinated type controlling organization.Steering wheel installation at present need to take more body space.Each rudder stock one of the present invention is fixed with an adjacent rudder stock two by connecting cabin；The closure rudder one of rudder stock one, the closure rudder two of rudder stock two；The rudderpost one being fixed on rudder one forms revolute pair with rudder stock one；Moving block is fixed on rudderpost one；The through hole two of slide bar and moving block forms sliding pair；Top is provided with the sliding block of boss and guide rail forms sliding pair；The both ends of connecting rod one are hinged with boss and slide bar respectively；One end of connecting rod two is fixed with sliding block；The nut block and leading screw for being fixed on the other end of connecting rod two form screw pair；One end of leading screw is connected with the output shaft of steering wheel two by shaft coupling；The rudderpost two of rudder two forms revolute pair with the through hole three of rudder stock two；The output shaft of steering wheel one is fixed with rudderpost two.In rudder stock where the steering wheel of some rudders is moved to another rudder by the present invention, reduce and body volume is taken.
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 guided missile pose and produce the controling power 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 is arranged in body, occupies the larger volume of 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 proposes higher requirement, and developing the guided missile rudder plane controlling mechanism for not placing steering wheel in a kind of some rudder stocks has its important
Meaning.
The content of the invention
The purpose of the present invention be for current steering wheel in placement it is more occupancy body space the problem of, there is provided a kind of guided missile
Rudder face space coordinated type controlling organization, it can be effectively saved installing space on the premise of the existing aerodynamic configuration of body is kept, enter
And efficiently reduce occupancy of the steering wheel placement to body volume.
The present invention is realized using following technical scheme：
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 with an adjacent rudder stock two by connecting cabin to be connected
Connect, all connecting cabins are circumferentially uniform along body；Described rudder stock one is connected with rudder one, and rudder stock two is connected with rudder two.
The through hole one and blind hole of the rudderpost one being fixed on rudder one and rudder stock one form revolute pair；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；The through hole two of slide bar and moving block forms sliding pair, and the axis horizontal of through hole two is set；Top is provided with convex
The sliding block of platform forms sliding pair with guide rail, and the both ends of the guide rail are supported on bearing block one and bearing block two respectively；Bearing block
One and bearing block two be each attached to the bottom of groove one of rudder stock one；The both ends of connecting rod one are hinged with boss and slide bar respectively；Connecting rod two
One end fixed with sliding block；The nut block and leading screw for being fixed on the other end of connecting rod two form screw pair；Described leading screw both ends point
It is not supported 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,
The bottom of groove two of bearing block three and bearing block four with rudder stock two is fixed.The rudderpost two of rudder two and the through hole three of rudder stock two
Revolute pair is formed, 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 converted into sliding pair between sliding block and guide rail by connecting rod two, then led to
The rotation that sliding pair is converted into rudderpost one by connecting rod one and sliding block etc. is crossed, realizes motion conversion spatially；
2nd, the control steering wheel of some rudders is moved in the rudder stock where another rudder controls steering wheel, so that
Steering wheel is not placed in some rudder stocks, reduces the occupancy to body volume, space availability ratio is lifted, and is met to Missile Actuator
Position and volume propose the guided missile rudder plane controlling mechanism demand of particular/special requirement.
Brief 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 at A in Fig. 1；
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, 2b, turn
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, sliding 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.
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 fasten
In afterbody, each both ends of connecting cabin 3 are fixedly connected with a rudder stock 1 and a rudder stock 24 respectively；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 connections.In Fig. 1, v is the speed of service of body.
As shown in figure 4, the 2a of rudderpost one being fixed on rudder 1 and the rudder stock 1 equal structure of the 1a of through hole one and blind hole 1c
Into revolute pair；The 1a of through hole one is coaxially disposed with blind hole 1c, and the 1a of through hole one is opened at the top of the 1b of groove one 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；Slide bar 6 and moving block 2b through hole
Two 2c form sliding pair, and the 2c of through hole two axis horizontal is set；Sliding block 10a of the top provided with boss 10c is formed with guide rail 9 to be slided
Pair, the both ends of guide rail 9 are supported on bearing block 1 and bearing block 2 11 respectively；Bearing block 1 and bearing block 2 11 are each attached to
The bottom of groove one of rudder stock 1；The both ends of connecting rod 1 are be hinged with boss 10c and slide bar 6 respectively；The 10b of connecting rod two one end and sliding block
10a is fixedly connected.
As shown in figure 5, the 10b of connecting rod two other end is fixedly connected with nut block 10d, nut block 10d passes through with leading screw 13
Screw pair connects；The both ends of leading screw 13 are supported on bearing block 3 14 and bearing block 4 15 respectively；One end of leading screw 13 and steering wheel two
17 output shaft is connected by shaft coupling 16；The groove two of steering wheel 2 17, bearing block 3 14 and bearing block 4 15 with 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 and rudder stock 24 4a of through hole three form revolute pair, lead 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 solid
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, which rotates, 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 bands movable slider 10a；Sliding block 10a mobile drivening rod one
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 driven
The 2a of rudderpost one is rotated so that rudder 1 rotates；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 to be fixedly connected in afterbody, rudder stock one and rudder stock two with body；Each rudder stock one
It is fixedly connected with an adjacent rudder stock two by connecting cabin, all connecting cabins are circumferentially uniform along body；Described rudder stock one connects
There is rudder one, rudder stock two is connected with rudder two；It is fixed on the through hole one of rudderpost one on rudder one and rudder stock one and blind
Hole forms revolute pair；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；The through hole two of slide bar and moving block, which is formed, to be slided
Pair, the axis horizontal of through hole two are set；Top is provided with the sliding block of boss and guide rail forms sliding pair, the both ends difference of the guide rail
It is supported 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 both ends are hinged with boss and slide bar respectively；One end of connecting rod two is fixed with sliding block；It is fixed on the nut block of the other end of connecting rod two
Screw pair is formed with leading screw；Described leading screw both ends are supported on bearing block three and bearing block four respectively；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 forms revolute pair with the through hole three of rudder stock two, 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 the output shaft and rudderpost two of steering wheel one are solid
It is fixed.
A kind of 2. 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.
A kind of 3. guided missile rudder face space coordinated type controlling organization according to claim 1, it is characterised in that：Described connecting rod
Two be in circular arc.
A kind of 4. 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 CN106643340A (en) | 2017-05-10 |
| CN106643340B true CN106643340B (en) | 2018-01-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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Family Cites Families (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 |
| CN103935507B (en) * | 2014-04-04 | 2015-11-11 | 北京航空航天大学 | Self-driven intelligence is dynamic air rudder entirely |
| CN104677201B (en) * | 2015-02-09 | 2016-08-24 | 浙江理工大学 | Quickly adjust the angle of attack with folding rudder development mechanism |
| CN206330489U (en) * | 2016-10-27 | 2017-07-14 | 浙江理工大学 | Guided missile rudder face space coordinated type controlling organization |
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- 2016-10-27 CN CN201610961206.XA patent/CN106643340B/en active Active
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| Publication number | Publication date |
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| CN106643340A (en) | 2017-05-10 |
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