CN204495199U - The folding rudder development mechanism of a kind of rapid adjustment angle of attack - Google Patents
The folding rudder development mechanism of a kind of rapid adjustment angle of attack Download PDFInfo
- Publication number
- CN204495199U CN204495199U CN201520088438.XU CN201520088438U CN204495199U CN 204495199 U CN204495199 U CN 204495199U CN 201520088438 U CN201520088438 U CN 201520088438U CN 204495199 U CN204495199 U CN 204495199U
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- CN
- China
- Prior art keywords
- rudder face
- rudder
- rudderpost
- spring
- camshaft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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Abstract
The utility model discloses the folding rudder development mechanism of a kind of rapid adjustment angle of attack.At present, the rudder face guiding mechanism of guided missile is complicated, and response speed is slow.Driven by servomotor leading screw of the present utility model; Long nut and leading screw form screw pair connected mode; One end of connecting rod by camshaft and long nut hinged, the other end and rudderpost affixed; The lower end of camshaft forms rolling pair by multi-directional ball and installing plate; On a mounting board, two ends are all fixed with rudder face installing rack in rudderpost supporting; Rudder face installing rack and rudder face hinged; Two rudder faces are symmetricly set on rudderpost two ends, and a rudder face is provided with angular transducer; Spring is placed in the spring seating holes of rudder face installing rack both sides; One end of locking pin is nested with on spring, and the other end embeds in chute corresponding to rudder face; One end and the rudder face of torsion spring are fixed, and the other end and rudder face installing rack are fixed.Rudder face of the present utility model can launch and complete locking under air lift, can at the rapid adjustment rudder face angle of attack under Serve Motor Control after rudder face locking.
Description
Technical field
The utility model belongs to aerospace field, controls the folding rudder development mechanism of the rapid adjustment angle of attack in course when being specifically related to follow the trail of.
Background technology
Excessive for taking carrier aircraft space when reducing seeker on-hook, rudder face adopts the folded form being close to bomb body usually.When after MISSILE LAUNCHING, folding rudder launches under unwind force effect.The folding steering wheel structure of current use all adopts independently power source, development mechanism relative complex.Seeker is generally equipped with four fixing rudder faces, is divided into orthogonal two groups.Awing, the external force that arbitrary rudder face is subject to all vertically can act on the heading of guided missile to guided missile, forms centripetal force.Under centripetal force effect, guided missile can change direction so that accurate tracking target and raising stability.At present, the rudder face guiding mechanism system complex of guided missile, response speed is comparatively slow, and mobility is relatively poor, follows the trail of poor effect.
Summary of the invention
The purpose of this utility model is for the deficiencies in the prior art, provides a kind of rapid adjustment angle of attack folding rudder development mechanism.After MISSILE LAUNCHING, rudder face can launch and launching to complete locking when putting in place, at the rapid adjustment rudder face angle of attack under Serve Motor Control, thus can realize the quick change in missile guidance direction after rudder face locking under the effect of air lift.
The technical solution adopted in the utility model is as follows:
The utility model comprises installing plate, servomotor, power transmission shaft, leading screw, long nut, camshaft, connecting rod, rudder face, torsion spring, rotating shaft, rudderpost, locking pin, spring, rudder face installing rack and angular transducer; Described servomotor is fixing on a mounting board, and cardan-shaft suspension on a mounting board; The output shaft of servomotor is all connected by flexible coupling with leading screw with the other end of one end of power transmission shaft, power transmission shaft.Described long nut is connected by screw pair with leading screw; One end of long nut offers axle sleeve installing hole, and axle sleeve embeds in axle sleeve installing hole; Camshaft passes the end, one end of axle sleeve and connecting rod; It is affixed after the self-locking nut at camshaft two ends is all threaded with camshaft; Described installing plate offers circular arc cam groove, and lower end and the multi-directional ball of camshaft are fixed, and multi-directional ball and circular arc cam groove form rolling pair.The middle part of described rudderpost offers rod hinge connection hole, and the other end of connecting rod and rudderpost pass through hinge at rod hinge connection hole place; The self-locking nut at bearing pin two ends is all connected rear affixed with pin shaft thread; Described rudderpost is supported on a mounting board by double-direction thrust ball bearing.
The two ends of described rudderpost are all fixed with rudder face installing rack; The end of rudder face is provided with auricle, and the auricle of both sides all offers chute, and the bottom of chute offers multiple auricle locating hole; Two rudder face installing racks are hinged by rotating shaft with all auricles of a rudder face respectively; Two rudder faces are symmetricly set on rudderpost two ends, and one of them rudder face is provided with angular transducer; Described angular transducer is connected with the control system controlling servomotor; The self-locking nut at rotating shaft two ends is all connected rear affixed with shaft thread; The both sides of described rudder face installing rack all offer multiple spring seating holes, and the quantity of spring seating holes is equal with the quantity of auricle locating hole; Spring is placed in spring seating holes; Each spring is nested with the one end at a locking pin, and the other end of locking pin embeds in the chute of corresponding side auricle; One end and the rudder face of described torsion spring are fixed, and the other end and rudder face installing rack are fixed.
Described installing plate is provided with fixing lug boss and hold-down support; Described servomotor is loaded in fixing lug boss, and cardan-shaft suspension is on hold-down support.
The auricle that one end of described torsion spring and rudder face are arranged on middle part is fixed.
The utility model has following beneficial effect relative to prior art:
1, adopt the combining form of servomotor, power transmission shaft, worm drive and grooved cam mechanism, comparatively high pulling torque can be exported, effective adjustment of the rudder face angle of attack can be realized quickly and accurately;
2, two rudder face symmetries are arranged on same rudderpost, motion Complete Synchronization, little to body interference, are conducive to the maintenance of missile flight process centered rudder face stability;
3, rudder face angle of attack guiding mechanism structure is simple, is easy to install, and reaches the effect identical with complex control system;
4, application is wide, except can be applicable to weaponry guiding mechanism, also may be used on civil folding development mechanism.
Accompanying drawing explanation
Fig. 1 is integrated model axonometric drawing of the present utility model;
Fig. 2 is the assembling schematic diagram of long nut and connecting rod in the utility model;
Fig. 3 is kinematic sketch of mechanism of the present utility model;
Fig. 4 is the schematic diagram of rudder face of the present utility model when being in folded state;
Fig. 5 is two rudder face position views symmetrical in the utility model;
Fig. 6-1 is the assembling schematic diagram of rudder face and rudder face installing rack in the utility model;
Fig. 6-2 is the A-A sectional view of Fig. 6-1;
Fig. 6-3 is the B-B sectional view of Fig. 6-1;
Fig. 7 is the assembly relation enlarged drawing of locking pin and rudder face installing rack in the utility model.
In figure: 1, installing plate, 101, fixing lug boss, 102, hold-down support, 103, circular arc cam groove, 2, servomotor, 3, flexible coupling, 4, power transmission shaft, 5, leading screw, 6, long nut, 601, axle sleeve installing hole, 7, camshaft, 8, connecting rod, 9, rudder face, 901, auricle locating hole, 10, torsion spring, 11, rotating shaft, 12, rudderpost, 1201, rod hinge connection hole, 13, bearing pin, 14, double-direction thrust ball bearing, 15, locking pin, 16, spring, 17, rudder face installing rack, 1701, spring seating holes, 18, multi-directional ball, 19, axle sleeve, 20, self-locking nut, 21, angular transducer.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail.
As shown in figs. 1 and 3, the folding rudder development mechanism of a kind of rapid adjustment angle of attack, comprises installing plate 1, servomotor 2, flexible coupling 3, power transmission shaft 4, leading screw 5, long nut 6, camshaft 7, connecting rod 8, rudder face 9, torsion spring 10, rotating shaft 11, rudderpost 12, double-direction thrust ball bearing 14, locking pin 15, spring 16, rudder face installing rack 17 and angular transducer 21; Servomotor 2 is fixed in the fixing lug boss 101 of installing plate 1, and power transmission shaft 4 is bearing on the hold-down support 102 of installing plate 1; The output shaft of servomotor 2 is all connected by flexible coupling 3 with leading screw 5 with the other end of one end of power transmission shaft 4, power transmission shaft 4.Flexible coupling 3 has comprehensive displacement compensate function, damping and good buffer effect.
As illustrated in fig. 1 and 2, long nut 6 is connected by screw pair with leading screw 5; One end of long nut 6 offers axle sleeve installing hole 601, and axle sleeve 19 embeds in axle sleeve installing hole 601; Camshaft 7 passes the end, one end of axle sleeve 19 and connecting rod 8; It is affixed after the self-locking nut 20 at camshaft 7 two ends is all threaded with camshaft 7; Axle sleeve 19 makes to be rolling friction between camshaft 7 and axle sleeve installing hole 601, improves and rotates flexibility.Installing plate 1 offers circular arc cam groove 103, and lower end and the multi-directional ball 18 of camshaft 7 are fixed, and multi-directional ball 18 and circular arc cam groove 103 form rolling pair.
As shown in Fig. 1,4 and 5, the middle part of rudderpost 12 offers rod hinge connection hole 1201, and the other end of connecting rod 8 and rudderpost 12 are hinged by bearing pin 13 at rod hinge connection hole 1201 place; It is affixed after the self-locking nut 20 at bearing pin 13 two ends is all threaded with bearing pin 13; Rudderpost 12 is bearing on installing plate 1 by double-direction thrust ball bearing 14.
As shown in Fig. 5,6-1,6-2,6-3 and 7, the two ends of rudderpost 12 are all fixed with rudder face installing rack 17; The end of rudder face 9 is provided with three auricles side by side, and the auricle of both sides all offers chute, and the bottom of chute offers two auricle locating holes 901; Two rudder face installing racks 17 are hinged by rotating shaft 11 with three auricles of a rudder face 9 respectively; Two rudder faces 9 are symmetricly set on rudderpost 12 two ends, and one of them rudder face 9 is provided with angular transducer 21; Angular transducer 21 is connected with control system, and control system controls servomotor 2; It is affixed after the self-locking nut 20 at rotating shaft 11 two ends is all threaded with rotating shaft 11; The both sides of rudder face installing rack 17 all offer two spring seating holes 1701, and in spring seating holes, 1701 place spring 16; One end of four locking pins 15 is nested with respectively in a spring 16, and the other end embeds in the chute of corresponding side auricle; One end of torsion spring 10 and rudder face 9 are arranged on middle auricle and fix, and the other end and rudder face installing rack 17 are fixed.
This rapid adjustment angle of attack operation principle of folding rudder development mechanism is:
As shown in Fig. 4,6 and 7, before MISSILE LAUNCHING, rudder face 9 is in folded state, is close to body, to reduce guided missile memory space; After MISSILE LAUNCHING, rudder face 9 launches under the deformation power of torsion spring 10 by after lift, and be deployed into certain position, four locking pins 15 are all pressed in the auricle locating hole 901 of rudder face under the active force of spring 16, realize location and the locking of rudder face 9.
The angle signal of measurement is passed to servomotor 2 by angular transducer 21 after treatment, the moment of torsion of input is passed to screw mandrel 5 through power transmission shaft 4 by servomotor 2, screw mandrel 5 will be converted to the movement of long nut 6 by screw pair, the circular arc cam groove 103 of camshaft 7 along installing plate under the thrust of long nut slides, the circular motion of camshaft 7 is converted to the rotation of rudderpost 12 by connecting rod 8, and then drives the rudder face 9 be arranged on rudder face installing rack 17 to rotate.Two rudder faces 9 are symmetricly set on rudderpost 12 two ends, have rotation synchronism.Angular transducer 21 is placed on rudder face 9, for measuring the longitudinal drift angle of rudder face 9 and guided missile in real time, and by Signal transmissions by its measurement result Real-time Feedback to the control system of servomotor 2, to reach accurately, the object of the rapid adjustment rudder face angle of attack.The folding rudder development mechanism of this rapid adjustment angle of attack, structure is simple, is easy to install, and it is convenient, practical to control.
Claims (3)
1. the folding rudder development mechanism of the rapid adjustment angle of attack, comprise installing plate, servomotor, power transmission shaft, leading screw, long nut, camshaft, connecting rod, rudder face, torsion spring, rotating shaft, rudderpost, locking pin, spring, rudder face installing rack and angular transducer, it is characterized in that:
Described servomotor is fixing on a mounting board, and cardan-shaft suspension on a mounting board; The output shaft of servomotor is all connected by flexible coupling with leading screw with the other end of one end of power transmission shaft, power transmission shaft; Described long nut is connected by screw pair with leading screw; One end of long nut offers axle sleeve installing hole, and axle sleeve embeds in axle sleeve installing hole; Camshaft passes the end, one end of axle sleeve and connecting rod; It is affixed after the self-locking nut at camshaft two ends is all threaded with camshaft; Described installing plate offers circular arc cam groove, and lower end and the multi-directional ball of camshaft are fixed, and multi-directional ball and circular arc cam groove form rolling pair; The middle part of described rudderpost offers rod hinge connection hole, and the other end of connecting rod and rudderpost pass through hinge at rod hinge connection hole place; The self-locking nut at bearing pin two ends is all connected rear affixed with pin shaft thread; Described rudderpost supports on a mounting board by double-direction thrust ball bearing;
The two ends of described rudderpost are all fixed with rudder face installing rack; The end of rudder face is provided with auricle, and the auricle of both sides all offers chute, and the bottom of chute offers multiple auricle locating hole; Two rudder face installing racks are hinged by rotating shaft with all auricles of a rudder face respectively; Two rudder faces are symmetricly set on rudderpost two ends, and one of them rudder face is provided with angular transducer; Described angular transducer is connected with the control system controlling servomotor; The self-locking nut at rotating shaft two ends is all connected rear affixed with shaft thread; The both sides of described rudder face installing rack all offer multiple spring seating holes, and the quantity of spring seating holes is equal with the quantity of auricle locating hole; Spring is placed in spring seating holes; Each spring housing is placed in one end of a locking pin, and the other end of locking pin embeds in the chute of corresponding side auricle; One end and the rudder face of described torsion spring are fixed, and the other end and rudder face installing rack are fixed.
2. the folding rudder development mechanism of a kind of rapid adjustment angle of attack according to claim 1, is characterized in that: described installing plate is provided with fixing lug boss and hold-down support; Described servomotor is loaded in fixing lug boss, and cardan-shaft suspension is on hold-down support.
3. the folding rudder development mechanism of a kind of rapid adjustment angle of attack according to claim 1, is characterized in that: the auricle that one end of described torsion spring and rudder face are arranged on middle part is fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520088438.XU CN204495199U (en) | 2015-02-09 | 2015-02-09 | The folding rudder development mechanism of a kind of rapid adjustment angle of attack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520088438.XU CN204495199U (en) | 2015-02-09 | 2015-02-09 | The folding rudder development mechanism of a kind of rapid adjustment angle of attack |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204495199U true CN204495199U (en) | 2015-07-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520088438.XU Withdrawn - After Issue CN204495199U (en) | 2015-02-09 | 2015-02-09 | The folding rudder development mechanism of a kind of rapid adjustment angle of attack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204495199U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN109506525A (en) * | 2018-11-23 | 2019-03-22 | 江西洪都航空工业集团有限责任公司 | A kind of power source eccentrically arranged type folding and expanding mechanism |
| CN114668626A (en) * | 2022-02-15 | 2022-06-28 | 燕山大学 | Pose-adjustable rigid-flexible coupling waist rehabilitation robot |
-
2015
- 2015-02-09 CN CN201520088438.XU patent/CN204495199U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677201A (en) * | 2015-02-09 | 2015-06-03 | 浙江理工大学 | Pucker rudder development mechanism for quickly adjusting attack angle |
| 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 |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN108275259B (en) * | 2017-12-22 | 2021-04-20 | 兰州空间技术物理研究所 | Flat aileron steering wheel mechanism |
| CN109506525A (en) * | 2018-11-23 | 2019-03-22 | 江西洪都航空工业集团有限责任公司 | A kind of power source eccentrically arranged type folding and expanding mechanism |
| CN109506525B (en) * | 2018-11-23 | 2020-12-15 | 江西洪都航空工业集团有限责任公司 | Power source offset type folding and unfolding mechanism |
| CN114668626A (en) * | 2022-02-15 | 2022-06-28 | 燕山大学 | Pose-adjustable rigid-flexible coupling waist rehabilitation robot |
| CN114668626B (en) * | 2022-02-15 | 2023-06-20 | 燕山大学 | Pose-adjustable rigid-flexible coupled waist rehabilitation robot |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150722 Effective date of abandoning: 20160824 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150722 Effective date of abandoning: 20160824 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |