CN203473238U - Missile aileron control mechanism - Google Patents
Missile aileron control mechanism Download PDFInfo
- Publication number
- CN203473238U CN203473238U CN201320303683.9U CN201320303683U CN203473238U CN 203473238 U CN203473238 U CN 203473238U CN 201320303683 U CN201320303683 U CN 201320303683U CN 203473238 U CN203473238 U CN 203473238U
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- aileron
- missile
- control mechanism
- steering engine
- ailerons
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- 230000007246 mechanism Effects 0.000 title claims abstract description 18
- 238000006073 displacement reaction Methods 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The utility model belongs to the technical field of missile control systems and particularly relates to a missile aileron control mechanism. The missile aileron control mechanism comprises a zero adjusting bolt, wherein one end of the zero adjusting bolt is fixed on a cabin body, and the other end face of the zero adjusting bolt is provided with an intersection at which a steering engine is fixed; a steering engine piston pull rod at the steering engine is connected to an aileron rocker arm which is connected with two aileron pull rods on the same plane; the other ends of the two aileron pull rods are connected with aileron rocker arms; the aileron rocker arms are connected with ailerons by using aileron rotating shafts. The missile aileron control mechanism has the advantages that 1. a force transmission way is simple and reliable, and a displacement can be effectively converted into an angle within a limited space; 2. the two aileron pulling rods are kept on the same plane, and when the steering engine piston pull rod moves, the two ailerons are kept to simultaneously and differentially move and have the consistent deflection angle, and errors are reduced to the lowest extent; and 3. the aileron rocker arm can drive the two aileron pull rods to simultaneously and reversely rotate during rotating, so that the ailerons simultaneously and reversely deflect.
Description
Technical field
The utility model belongs to guided missile maneuvering system technical field, relates in particular to a kind of guided missile aileron control mechanism.
Background technology
Steering unit refers in missile control system, from steering wheel to a set of mechanical drive controlsurface rotating shaft.Its function one is that controlsurface is produced and the corresponding angle of inclination of steering wheel displacement; The 2nd, transmit steering wheel moment, in order to balanced surface, obtain hinge moment.For making guided missile produce the rolling moment around the longitudinal axis, can design a kind of aileron control mechanism, aerofoil is oppositely deflection simultaneously all the time.
Summary of the invention
The utility model is in order to overcome above-mentioned defect, and object is to provide a kind of mode of transfer force simple and reliable, can be by the more effective guided missile aileron control mechanism that is converted into angle of displacement in limited space.
In order to achieve the above object, the utility model adopts following technical scheme:
A kind of guided missile aileron control mechanism, it comprises a zeroing bolt, one end of described zeroing bolt is fixed on the body of cabin, the other end end face of zeroing bolt is prong, prong place is steering wheel fixedly, the position of capable of regulating steering wheel like this, and self deflection angle that can solve that steering wheel piston rod produces when flexible.
The steering wheel pitch brace at steering wheel place is connected on aileron pivoted arm, and aileron pivoted arm connects two aileron pull bars at same plane, and the other end of two aileron pull bars connects aileron rocking arm, between aileron rocking arm and aileron, with aileron rotating shaft, is connected.
Aileron pivoted arm can drive two aileron pull bars counter-rotation simultaneously when rotating, thereby guarantees aileron oppositely deflection simultaneously.
Described aileron pivoted arm middle part is provided with bearing.
The beneficial effects of the utility model:
1, the utility model mode of transfer force is simple and reliable, can be by the more effective angle that is converted into of displacement in limited space.
2, two aileron pull bars of the utility model remain in same plane, and when steering wheel piston rod produces displacement, differential deflection angle is consistent simultaneously to guarantee two ailerons, and it is minimum that error is reduced to.
3, the utility model aileron pivoted arm can drive two aileron pull bars counter-rotation simultaneously when rotating, thereby guarantees aileron oppositely deflection simultaneously.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the cross section structure schematic diagram of aileron pivoted arm.
Fig. 3 is aileron transmission principle figure (the first link: oscillating guidebar mechanism).
Fig. 4 is aileron transmission principle figure (the second link: space 4 connecting rod mechanisms (1 group)).
The specific embodiment
Below in conjunction with 1,2,3,4 pairs of the utility model of accompanying drawing, be elaborated:
A kind of guided missile aileron control mechanism, it comprises a zeroing bolt 1, one end of described zeroing bolt 1 is fixed on the body of cabin, the other end end face of zeroing bolt 1 is prong, prong place is steering wheel 2 fixedly, and the steering wheel pitch brace 8 at steering wheel 2 places is connected on aileron pivoted arm 3, and aileron pivoted arm 3 connects two aileron pull bars 4 at same plane, the other end of two aileron pull bars 4 connects aileron Rocker arm 5, between aileron Rocker arm 5 and aileron 7, with aileron rotating shaft 6, is connected.
At described aileron pivoted arm 3 middle parts, be provided with bearing 9.
The whole steering unit system of guided missile aileron is above inlet channel, this Aileron control system is connected and is obtained by two links of 1 oscillating guidebar mechanism and 2 spatial four-bar mechanisms, steering unit drive system principle is decomposed as Fig. 3, Fig. 4: the steering wheel piston rod of the first link produces displacement s, aileron pivoted arm produces angle of inclination φ
1, angle of inclination φ
1drive again the aileron rocking arm of the second link to produce angle of inclination φ
2, aileron arm drives aileron pull bar and slave arm to make aerofoil produce angle of inclination ψ, thereby obtains the drive connection of whole mechanism.
For making 2 spatial four-bar mechanism drive connections consistent, now design a kind of aileron pivoted arm, see accompanying drawing 1,2.Wherein two aileron pull bars remain in same plane, and when steering wheel piston rod produces displacement, differential deflection angle is consistent simultaneously to guarantee two ailerons, and it is minimum that error is reduced to.
Claims (2)
1. a guided missile aileron control mechanism, it is characterized in that: it comprises a zeroing bolt (1), one end of described zeroing bolt (1) is fixed on the body of cabin, the other end end face of zeroing bolt (1) is prong, prong place is steering wheel (2) fixedly, the steering wheel pitch brace (8) that steering wheel (2) is located is connected on aileron pivoted arm (3), aileron pivoted arm (3) connects two aileron pull bars (4) at same plane, the other end of two aileron pull bars (4) connects aileron rocking arm (5), between aileron rocking arm (5) and aileron (7), with aileron rotating shaft (6), is connected.
2. guided missile aileron control according to claim 1 mechanism, is characterized in that: at described aileron pivoted arm (3) middle part, be provided with bearing (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320303683.9U CN203473238U (en) | 2013-05-30 | 2013-05-30 | Missile aileron control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320303683.9U CN203473238U (en) | 2013-05-30 | 2013-05-30 | Missile aileron control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203473238U true CN203473238U (en) | 2014-03-12 |
Family
ID=50221620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320303683.9U Expired - Fee Related CN203473238U (en) | 2013-05-30 | 2013-05-30 | Missile aileron control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203473238U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN105083537A (en) * | 2015-08-05 | 2015-11-25 | 北京韦加航通科技有限责任公司 | Control surface control device and aircraft |
| CN105460225A (en) * | 2015-11-26 | 2016-04-06 | 庆安集团有限公司 | Fault isolation mechanism for elevating rudders |
| CN111731469A (en) * | 2019-04-12 | 2020-10-02 | 北京京东尚科信息技术有限公司 | Airfoil linkages and aircraft |
| CN112196636A (en) * | 2020-09-29 | 2021-01-08 | 中国航发动力股份有限公司 | A method for assembling an engine bleeder mechanism based on a pusher and a pusher |
| CN113978704A (en) * | 2021-12-17 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | A steering gear installation device |
-
2013
- 2013-05-30 CN CN201320303683.9U patent/CN203473238U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN103318404B (en) * | 2013-05-30 | 2016-03-30 | 江西洪都航空工业集团有限责任公司 | A kind of guided missile aileron control mechanism |
| CN105083537A (en) * | 2015-08-05 | 2015-11-25 | 北京韦加航通科技有限责任公司 | Control surface control device and aircraft |
| CN105460225A (en) * | 2015-11-26 | 2016-04-06 | 庆安集团有限公司 | Fault isolation mechanism for elevating rudders |
| CN105460225B (en) * | 2015-11-26 | 2017-12-12 | 庆安集团有限公司 | A kind of Fault Isolation mechanism for elevator |
| CN111731469A (en) * | 2019-04-12 | 2020-10-02 | 北京京东尚科信息技术有限公司 | Airfoil linkages and aircraft |
| CN111731469B (en) * | 2019-04-12 | 2022-04-26 | 北京京东乾石科技有限公司 | Airfoil linkages and aircraft |
| CN112196636A (en) * | 2020-09-29 | 2021-01-08 | 中国航发动力股份有限公司 | A method for assembling an engine bleeder mechanism based on a pusher and a pusher |
| CN112196636B (en) * | 2020-09-29 | 2021-06-08 | 中国航发动力股份有限公司 | Engine deflation mechanism assembling method based on tightening ejection tool and tightening ejection tool |
| CN113978704A (en) * | 2021-12-17 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | A steering gear installation device |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140312 Termination date: 20180530 |
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| CF01 | Termination of patent right due to non-payment of annual fee |