CN206330490U - Guided missile rudder plane controlling mechanism - Google Patents
Guided missile rudder plane controlling mechanism Download PDFInfo
- Publication number
- CN206330490U CN206330490U CN201621185969.1U CN201621185969U CN206330490U CN 206330490 U CN206330490 U CN 206330490U CN 201621185969 U CN201621185969 U CN 201621185969U CN 206330490 U CN206330490 U CN 206330490U
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- China
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- rudder
- rudder stock
- stock
- steering wheel
- fixed
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- Withdrawn - After Issue
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Abstract
The utility model discloses guided missile rudder plane controlling mechanism.Current steering wheel, which is installed, need to take more body space.Each rudder stock one of the present utility model is fixed with an adjacent rudder stock two by connecting cabin；Rudder stock one is connected with rudder one, and rudder stock two is connected with rudder two；Each rudder one is connected with a corresponding rudder stock two by a connecting rod one；The rudderpost one being fixed on rudder one passes through the axle sleeve for being fixed on the one end of connecting rod one, and constitutes rotation pair with the through hole one and blind hole of rudder stock one；Axle sleeve is arranged in the groove one of rudder stock one；The sliding block and ring-shaped guide rail for being fixed on the other end of connecting rod one constitute spherical pair, and ring-shaped guide rail is fixed on the bottom of groove two of rudder stock two；Steering wheel one drives sliding block；The rudderpost two of rudder two is constituted with the through hole two of rudder stock two rotates secondary, the driving rudderpost two of steering wheel two.The utility model moves to the steering wheel for special procuring rudder in the rudder stock of another rudder steering wheel place, reduces the occupancy to body volume, space efficiency utilization is effectively lifted.
Description
Technical field
The utility model belongs to weaponry field, and in particular to a kind of guided missile rudder plane controlling mechanism.
Background technology
Guided missile rudder rotates in flight course around rudderpost, to adjust guided missile pose and produce the controling power to guided missile and control
Torque, makes guided missile adjust flight path in time, reaches the purpose of precision strike.At present, most of rudder faces are main by servos control
Rotate, and steering wheel is arranged in body, is occupied the larger volume of body, must be protected during design by increasing the size of body
Demonstrate,prove the installing space of the associated mechanisms such as steering wheel.With continuing to develop for missilery, the appearance and size of guided missile is proposed higher
Requirement, or even position to Missile Actuator and volume propose particular/special requirement, researches and develops in a kind of some rudder stocks and does not place steering wheel
Guided missile rudder plane controlling mechanism have its Special Significance.
The content of the invention
The purpose of this utility model is that there is provided one the problem of body volume is more taken in placement for current steering wheel
Guided missile rudder plane controlling mechanism is planted, installing space, Jin Eryou can be effectively saved on the premise of the existing aerodynamic configuration of body is kept
Reduce occupancy of the steering wheel placement to body volume in effect ground.
The utility model is realized using following technical scheme：
The utility model includes rudder stock one and rudder stock two；Quantity identical rudder stock one and rudder stock two are uniformly distributed along the circumference in body
Afterbody, 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
Connection, 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；Each rudder one is connected with a corresponding rudder stock two by a connecting rod one.The rudderpost one being fixed on rudder one is worn
The axle sleeve for being fixed on the one end of connecting rod one is crossed, and rotation pair is constituted with the through hole one and blind hole of rudder stock one；Described through hole one with
Blind hole is coaxially disposed, and through hole one is opened in the top of groove one of rudder stock one, and blind hole is opened in the bottom of groove one of rudder stock one；Axle
It is set in the groove one of rudder stock one；Axle sleeve is fixedly connected with rudderpost one by stop pin.It is fixed on the other end of connecting rod one
Sliding block constitutes spherical pair with ring-shaped guide rail, and ring-shaped guide rail is fixed on the bottom of groove two of rudder stock two；The bottom of groove two of rudder stock two
It is fixed with bearing block one and bearing block two；Screw mandrel two ends are supported on bearing block one and bearing block two respectively, nut and screw mandrel shape
Into screw pair, the two ends of connecting rod two are hinged with the boss of nut side and the boss of sliding block side respectively, the bottom of groove two of rudder stock two
Portion is fixed with steering wheel one, and the output shaft of steering wheel one is connected with screw mandrel by shaft coupling one.The rudderpost two of rudder two and rudder stock two
Through hole two constitute and rotate secondary, through hole two is opened in the top of groove two of rudder stock two；The top of groove two of rudder stock two is fixed with rudder
Steering wheel two is fixed on frame, steering wheel frame, the output shaft of steering wheel two is connected with rudderpost two by shaft coupling two.
Described connecting cabin is fastened on afterbody.
Described connecting rod one and ring-shaped guide rail are in circular arc.
Described rudder stock one and rudder stock two is two.
The beneficial effects of the utility model：
The spherical pair of ring-shaped guide rail (sphere) the 1st, is converted into the rotation pair of axle sleeve, motion conversion spatially is realized；
2nd, some control steering wheels for special procuring rudder are moved in the rudder stock where another rudder controls steering wheel, so that
So that not placing steering wheel in some rudder stocks, the occupancy to body volume is reduced, space efficiency is improved, met to guided missile
The position of steering wheel and volume propose the guided missile rudder plane controlling mechanism demand of particular/special requirement.
Brief description of the drawings
Fig. 1 is overall structure stereogram of the present utility model；
The schematic diagram that Fig. 2 is connected for rudder one in the utility model with rudder stock two by connecting rod one；
Fig. 3 is end view of the present utility model；
Fig. 4 is the partial enlarged drawing at A in Fig. 1；
Fig. 5 is the assembling stereogram of the top shoe of connecting rod one in the utility model；
Fig. 6 is the schematic view of the mounting position of steering wheel two in the utility model.
In figure：1st, rudder stock one, 1a, through hole one, 1b, groove one, 1c, blind hole, 2, rudder one, 2a, rudderpost one, 3, connection
Cabin, 4, rudder stock two, 4a, through hole two, 4b, groove two, 5, rudder two, 5a, rudderpost two, 6, connecting rod one, 6a, stop pin, 6b, cunning
Block, 6c, boss, 6d, axle sleeve, 7, ring-shaped guide rail, 8, steering wheel one, 9, shaft coupling one, 10, bearing block one, 11, connecting rod two, 12, spiral shell
Mother, 13, bearing block two, 14, screw mandrel, 15, steering wheel two, 16, steering wheel frame, 17, shaft coupling two.
Embodiment
Below in conjunction with the accompanying drawings and embodiment is described further to the utility model.
As shown in Fig. 1~Fig. 6, guided missile rudder plane controlling mechanism, including rudder stock 1 and rudder stock 24；Two rudder stocks one 1 and two
Individual rudder stock 24 is uniformly distributed along the circumference in afterbody, and is fixedly connected with body；Two connecting cabins 3 are fastened on afterbody, often
The individual two ends of connecting cabin 3 are fixedly connected with a rudder stock 1 and a rudder stock 24 respectively；Rudder stock 1 is connected with rudder 1, rudder
Cabin 24 is connected with rudder 25；Each rudder 1 is connected with a corresponding rudder stock 24 by a connecting rod 1.In Fig. 1,
V is the speed of service of body.
As shown in Figures 4 and 5, the 2a of rudderpost one being fixed on rudder 1 passes through the axle sleeve for being fixed on the one end of connecting rod 1
6d, and constitute rotation pair with the 1a of through hole one and blind hole 1c of rudder stock 1；The 1a of through hole one is coaxially disposed with blind hole 1c, and through hole
One 1a is opened at the top of the 1b of groove one of rudder stock 1, and blind hole 1c is opened in the 1b bottoms of groove one of rudder stock 1；Axle sleeve 6d is set
In the 1b of groove one of rudder stock 1；Axle sleeve 6d is fixedly connected with the 2a of rudderpost one by stop pin 6a.
As shown in Figure 1, Figure 2 with the sliding block 6b and the composition spherical pair of ring-shaped guide rail 7 for shown in Fig. 5, being fixed on the other end of connecting rod 1,
Ring-shaped guide rail 7 is fixed on the 4b bottoms of groove two of rudder stock 24；The 4b bottoms of groove two of rudder stock 24 are fixed with the He of bearing block 1
Bearing block 2 13；The two ends of screw mandrel 14 are supported on bearing block 1 and bearing block 2 13 respectively, nut 12 and the formation spiral shell of screw mandrel 14
Rotation is secondary, and the two ends of connecting rod 2 11 are hinged with the boss of the side of nut 12 and the boss 6c of sliding block 6b sides respectively, the groove of rudder stock 24
Two 4b bottoms are fixed with steering wheel 1, and the output shaft of steering wheel 1 is connected with screw mandrel 14 by shaft coupling 1.
As shown in figure 4, the 5a of rudderpost two of rudder 25 is constituted with the 4a of through hole two of rudder stock 24 rotates secondary, the 4a of through hole two is opened
At the top of the 4b of groove two for being located at rudder stock 24；It is fixed with the top of the 4b of groove two of rudder stock 24 fixed on steering wheel frame 16, steering wheel frame 16
Steering wheel 2 15, the output shaft of steering wheel 2 15 is connected with the 5a of rudderpost two by shaft coupling 2 17.
The operation principle of the guided missile rudder plane controlling mechanism：
As shown in figs. 1 to 6, in the guided missile rudder plane controlling mechanism, steering wheel 1, which is rotated, drives screw mandrel 14 to rotate；Nut 12 exists
Moved linearly under the driving of screw mandrel, nut 12 drives the sliding block 6b being fixed on connecting rod 1 to be led in annular by connecting rod 2 11
Rail 7 is slided；Connecting rod 2 11 slides sliding block 6b sphere the rotation for being converted into axle sleeve 6d；Stop pin 6a fixed hubs and rudderpost one
2a, it is ensured that axle sleeve 6a and the 2a of rudderpost one are rotated simultaneously so that rudder 1 is rotated；Steering wheel 2 15, which is rotated, drives the 5a of rudderpost two to turn
It is dynamic so that rudder 25 is rotated；Additionally, the He of rudder 1 can be changed by changing steering wheel 1 and the rotation direction of steering wheel 2 15
The rotation direction of rudder 25.
Claims (4)
1. guided missile rudder plane controlling mechanism, including rudder stock one and rudder stock two, it is characterised in that：Quantity identical rudder stock one and rudder stock two
It is uniformly distributed along the circumference in afterbody, rudder stock one and rudder stock two are fixedly connected with body；Each rudder stock one and an adjacent rudder stock
Two are fixedly connected by connecting cabin, and all connecting cabins are circumferential uniform along body；Described rudder stock one is connected with rudder one, rudder stock
Two are connected with rudder two；Each rudder one is connected with a corresponding rudder stock two by a connecting rod one；It is fixed on rudder
Rudderpost one on one passes through the axle sleeve for being fixed on the one end of connecting rod one, and constitutes rotation pair with the through hole one and blind hole of rudder stock one；
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, and blind hole is opened in rudder stock one
The bottom of groove one；Axle sleeve is arranged in the groove one of rudder stock one；Axle sleeve is fixedly connected with rudderpost one by stop pin；It is fixed on
The sliding block of the other end of connecting rod one constitutes spherical pair with ring-shaped guide rail, and ring-shaped guide rail is fixed on the bottom of groove two of rudder stock two；Rudder stock
Two bottom of groove two is fixed with bearing block one and bearing block two；Screw mandrel two ends are supported on bearing block one and bearing block two respectively
On, nut is hinged with the boss of nut side and the boss of sliding block side respectively with screw mandrel formation screw pair, the two ends of connecting rod two, rudder
The bottom of groove two in cabin two is fixed with steering wheel one, and the output shaft of steering wheel one is connected with screw mandrel by shaft coupling one；Rudder two
Rudderpost two constitutes with the through hole two of rudder stock two and rotates secondary, and through hole two is opened in the top of groove two of rudder stock two；The groove of rudder stock two
Two tops, which are fixed with steering wheel frame, steering wheel frame, fixes steering wheel two, and the output shaft of steering wheel two is connected with rudderpost two by shaft coupling two.
2. guided missile rudder plane controlling mechanism according to claim 1, it is characterised in that：Described connecting cabin is fastened on body tail
Portion.
3. guided missile rudder plane controlling mechanism according to claim 1, it is characterised in that：Described connecting rod one and ring-shaped guide rail are equal
In circular arc.
4. guided missile rudder plane controlling mechanism according to claim 1, it is characterised in that：Described rudder stock one and rudder stock two is
Two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621185969.1U CN206330490U (en) | 2016-10-27 | 2016-10-27 | Guided missile rudder plane controlling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621185969.1U CN206330490U (en) | 2016-10-27 | 2016-10-27 | Guided missile rudder plane controlling mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206330490U true CN206330490U (en) | 2017-07-14 |
Family
ID=59287132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621185969.1U Withdrawn - After Issue CN206330490U (en) | 2016-10-27 | 2016-10-27 | Guided missile rudder plane controlling mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206330490U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568356A (en) * | 2016-10-27 | 2017-04-19 | 浙江理工大学 | Missile rudder surface control mechanism |
| CN114593644A (en) * | 2022-01-25 | 2022-06-07 | 北京宇航系统工程研究所 | Restraining locking mechanism for limiting deflection and buffeting of plane rudder |
-
2016
- 2016-10-27 CN CN201621185969.1U patent/CN206330490U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568356A (en) * | 2016-10-27 | 2017-04-19 | 浙江理工大学 | Missile rudder surface control mechanism |
| CN114593644A (en) * | 2022-01-25 | 2022-06-07 | 北京宇航系统工程研究所 | Restraining locking mechanism for limiting deflection and buffeting of plane rudder |
| CN114593644B (en) * | 2022-01-25 | 2023-06-06 | 北京宇航系统工程研究所 | Suppression locking mechanism for limiting deflection and buffeting of plane rudder |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170714 Effective date of abandoning: 20180119 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20170714 Effective date of abandoning: 20180119 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |