CN107606020A - A kind of composite damping structure for airborne lidar for fluorescence - Google Patents
A kind of composite damping structure for airborne lidar for fluorescence Download PDFInfo
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- CN107606020A CN107606020A CN201710700056.1A CN201710700056A CN107606020A CN 107606020 A CN107606020 A CN 107606020A CN 201710700056 A CN201710700056 A CN 201710700056A CN 107606020 A CN107606020 A CN 107606020A
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Abstract
The present invention proposes a kind of composite damping structure for airborne lidar for fluorescence, including 1 circular upper lid, 1 circular bottom end cover being connected with airborne platform, 1 circular carrier being connected with electro-optical system, the cable of the wire rope damper of 8 circumference uniform distributions and the rubber shock absorber of 8 circumference uniform distributions, 1 connection electro-optical system and host computer.Upper end cover is connected with bottom end cover by bolt, forms the sealed internal chamber of a column, carrier is installed in inner chamber centre position, and inner chamber is divided into two chambers up and down.Lower intracavitary, 8 wire rope dampers and 8 rubber shock absorbers are evenly arranged along carrier circumferencial direction；Upper intracavitary arranges connecting cable.The present invention moves to vibration-proof structure between electro-optical system and carrier aircraft platform from electro-optical system inside is outer, in the design aspect of vibration-proof structure, using integration, compact structure design, by vibration-proof structure be designed as one can integral replacing semi-enclosed device, the internals of vibration-proof structure is sufficiently spaced from outside adverse circumstances, ensure that higher Flight Line Maintenance and reliability.
Description
Technical field
The invention belongs to airborne photoelectric antivibration area, is related to a kind of composite damping knot for airborne lidar for fluorescence
Structure.This structure composition wire rope damper and rubber shock absorber are the vibration isolation and context buffer the advantages of, applied to positioning precision
It is required that the airborne photoelectric system that higher, electro-optical system inherent space constraints, use temperature range are wide, vibration and shock environment are more severe
System.
Background technology
Vital task equipment of the electro-optical system as aircraft platform, possess battle reconnaissance, target following and instruction etc. and fight
Ability.Vibration-proof structure is unique vibration damping and buffer unit in electro-optical system, for reducing carrier aircraft Platform Vibration and impact to light
The influence of electric system performance.At present, vibration-proof structure is usually integrated inside electro-optical system, and this mounting means is occupying
Inside electro-optical system while the useful space, the maintenance difficulty of vibration-proof structure is added.Also, in recent years, with military affairs
The diversified demand of development, it is desirable to which airborne lidar for fluorescence develops towards lightness, miniaturization and intelligent direction so that existing light
The vibration-proof structure of electric system can not meet the growth requirement of electro-optical system, thus, design a kind of maintainability height, suitable for new
The vibration-proof structure of electro-optical system is just particularly important.
Compared with other airborne task devices, the working environment of electro-optical system mainly has following characteristics：1. environment temperature model
Enclose width；2. to the existing insulated degree requirement of vibration-proof structure, also there is positioning accuracy request；3. the useful space is narrow and small inside electro-optical system,
It is larger internally to design vibration-proof structure difficulty；4. requiring higher to loss of weight, therefore it is difficult to obtain larger support stiffness；5. use
Environment is complicated, various, is easily influenceed by adverse circumstances such as temperature change, humidity, vibration, impacts.Electro-optical system vibration damping knot at present
Structure uses rubber shock absorber, is symmetrically arranged on inside electro-optical system, between photoelectric sensor and outer framework, this vibration-proof structure is set
Meter has the following disadvantages：1. occupying the useful space narrow and small inside electro-optical system, electro-optical system size can not be reduced；2. increase
Electro-optical system weight；3. rubber shock absorber high temperature resistant, poor performance at low temperatures, service life is limited, and damping property drops after long-term use
It is low；4. damper service is poor, changes or need to remove internal photoelectric sensor when maintaining shock absorber.
The content of the invention
The shortcomings that to overcome current airborne lidar for fluorescence vibration-proof structure, adapt to the growth requirement of novel photoelectric system, this hair
It is bright to propose a kind of composite damping structure for airborne lidar for fluorescence.
The technical scheme is that：
A kind of composite damping structure for airborne lidar for fluorescence, it is characterised in that：Including 1 circular upper
Lid, 1 circular bottom end cover being connected with airborne platform, 1 circular carrier being connected with electro-optical system, N number of circumference are equal
The cable of the rubber shock absorber of the wire rope damper of cloth, N number of circumference uniform distribution, 1 connection electro-optical system and host computer；Upper end cover
It is connected with bottom end cover by bolt, forms the sealed internal chamber of a column, carrier is installed in inner chamber centre position, and by
Chamber is divided into two chambers up and down；Lower intracavitary, N number of wire rope damper and N number of rubber damping are evenly arranged along carrier circumferencial direction
Device, and be separately fixed at by bolt on carrier and bottom end cover, wire rope damper and rubber shock absorber are alternately arranged；Epicoele
It is interior, it is disposed with the connecting cable of electro-optical system and host computer.
A kind of composite damping structure for airborne lidar for fluorescence, it is characterised in that：Upper end cover medial surface has footpath
To segmentation positive stop lug boss, carrier lateral surface has a stopper slot of segmentation, the segmentation positive stop lug boss of upper end cover and the limit of carrier
Position groove can be coordinated by rotation mode.
Beneficial effect
Beneficial effects of the present invention are embodied in the following aspects：
1st, vibration-proof structure is moved between electro-optical system and carrier aircraft platform from electro-optical system inside is outer, increases electro-optical system
The internal useful space, realize that lightness, miniaturization create conditions for electro-optical system.
2nd, in terms of environmental suitability, using the composite design of two kinds of shock absorbers, it is resistance to overcome current single rubber shock absorber
The shortcomings that high temperature, low temperature properties difference.
3rd, anti-vibration and impact aspect, steel wire rope is good to low frequency vibration isolation effect, and rubber shock absorber is good to high-frequency vibration isolation effect,
Composite damping structure can reach good vibration isolating effect in the whole frequency band range of carrier aircraft.Rubber shock absorber has higher rush
Rigidity is hit, is advantageous to the combined vibration-damping of shock resistance deformation, rubber and steel wire rope, it is big to overcome wire rope damper static deflection
The shortcomings that.
4th, in terms of the service life of vibration-proof structure, composite damping structure overcomes single rubber shock absorber due to for a long time
The shortcomings that declining using effectiveness in vibration suppression, the use longevity of vibration-proof structure is greatly extended by being used in combination with wire rope damper
Life.
5th, in terms of the maintainability of electro-optical system, semi-enclosed external composite damping structure design is as overall replaceable list
Member, when outfield is safeguarded and is changed, without removing electro-optical system sensor, improve the maintainability of electro-optical system.
Brief description of the drawings
Fig. 1 is overall appearance figure of the present invention.
Fig. 2 is structure composition figure of the present invention.
Fig. 3 is sectional arrangement drawing of the present invention.
Fig. 4 is the present invention and electro-optical system simulation installation diagram.
Wherein：1-bottom end cover, 2-carrier, 3-upper end cover, 4-carrier aircraft installation pedestal, 5-cable interface, 6-limit
Position groove, 7-wire rope damper, 8-rubber shock absorber, 9-connecting cable.
Embodiment
The present invention moves to vibration-proof structure between electro-optical system and carrier aircraft platform from electro-optical system inside is outer, increases photoelectricity
The internal system useful space, realize that lightness, miniaturization create conditions for electro-optical system；In the design aspect of vibration-proof structure, adopt
With integration, compact structure design, by vibration-proof structure be designed as one can integral replacing semi-enclosed device, vibration-proof structure
Internals be sufficiently spaced from outside adverse circumstances, ensure that higher Flight Line Maintenance and reliability.The vibration-proof structure bag
Include 1 circular upper lid, 1 circular bottom end cover being connected with airborne platform, 1 circular carrying being connected with electro-optical system
Disk, the wire rope damper of 8 circumference uniform distributions and the rubber shock absorber of 8 circumference uniform distributions, 1 connection electro-optical system and host computer
Cable.Upper end cover is connected with bottom end cover by bolt, forms the sealed internal chamber of a column, and carrier is mounted in the lumen
Between position, and by inner chamber be divided into up and down two chambers.Lower intracavitary, 8 wire rope dampers are evenly arranged along carrier circumferencial direction
With 8 rubber shock absorbers, and it is separately fixed at by bolt on carrier and bottom end cover, wire rope damper and rubber shock absorber
It is alternately arranged；Upper intracavitary, reasonable Arrangement the connecting cable of electro-optical system and host computer.
This composite structural design integrates the advantages of steel wire rope vibration damping and rubber damping, can solve current electro-optical system
Varied with temperature by itself rubber shock absorber, the shortcomings that its antivibration effect constantly decays, meanwhile, widen electro-optical system itself
Antivibration frequency bandwidth.In this structure, because 8 wire rope dampers and 8 rubber shock absorbers are evenly distributed in the circumferential direction, and
Wire rope damper and rubber shock absorber are alternately arranged, so the overall relative electro-optical system mass axis of shock absorber is symmetrical,
And symmetric position equal stiffness, therefore two kinds of vibrations of revolution of the vibration-proof structure to electro-optical system and translation are independent of each other, and are formed non-
Couple vibration insulating system.Vibration and impact for axial direction, fully with wire rope damper and rubber shock absorber to the excellent of vibration isolation
Point, solve damping and the intrinsic contradiction of rigidity this shock absorber, and circumferential uniformly installation well, reduce vibration-proof structure by
While life loss caused by installation deviation, and circular stopper slot ensures electro-optical system all the time perpendicular to Aircraft together
To；Vibrate and impact for horizontal direction, due to the installation form of vibration-proof structure, the structure is carrying out antivibration and buffered same
When, the vibration that can correct electro-optical system axis in time tilts, and possesses axis self-calibrating capabilities.Transported for the revolution around three axles
It is dynamic, due to being symmetrically installed for shock absorber, a moment of torsion directly proportional, in opposite direction with disturbing angular dimension will be formed, will be possessed pair
The self-correcting capability of gyration.
The invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 3, for the present invention using integration, compact structure design, vibration-proof structure is designed as into one can
The semi-enclosed device of integral replacing.Upper end cover 3 and bottom end cover 1 form the cavity of a column, carrier 2 by cylindrical cavities every
It is divided into two cavitys up and down, lower chamber installation wire rope damper and rubber shock absorber, two kinds of shock absorbers are equal along carrier circumference
Even distribution, blending bolt are fixed on bottom end cover and carrier, are vibration isolation in damper structure, buffering device.Under upper cavity
The opening in portion is used to install electro-optical system, and after installation, upper end cover, carrier, and electro-optical system form a semi-enclosed chamber
Body, block influence of the extraneous adverse circumstances (such as greasy dirt, rainwater, sand and dust) to vibration-proof structure；Upper cavity top, upper end cover with
Carrier is assembled by position limiting structure, limits the peak swing of electro-optical system, ensure that the higher positioning precision of electro-optical system；
Connecting cable in epicoele is used to connect electro-optical system and host computer.Operating temperature is -40 DEG C~+65 DEG C, and antivibration is horizontal：≥
2g, shock resistance are horizontal：Vertically >=20g, level >=15g.
As shown in Fig. 2 this vibration-proof structure includes as overall replaceable units, its composition：Bottom end cover 1, carrier 2, on
End cap 3, carrier aircraft installation pedestal 4, cable interface 5, stopper slot 6, wire rope damper 7, rubber shock absorber 8, connecting cable 9.Its
Installation steps are：
Step 1：Bottom end cover is placed on the openr place of horizontal table top；
Step 2：It is corresponding that 8 wire rope dampers and 8 rubber shock absorbers with M4 and M6 are bolted to bottom end cover
Position；
Step 3：Carrier is put into from top to bottom in the structure assembled, rotates carrier, make its mounting hole with it is each
Shock absorber mounting hole aligns, and is fixed with M4 bolts；
Step 4：Cable interface is arranged on to the interface installation position of upper end cover with 4 M3 bolts；
Step 5：Positive stop lug boss in upper end cover and carrier indentation, there are alignd, move upper end cover from top to bottom until
Contacted with lower end cap surface, rotate to adjacent mounting hole clockwise or counterclockwise, now, positive stop lug boss is just at holding
In stopper slot on load plate, and upper end cover and bottom end cover are fixed with M6 bolts.
By more than five steps, mounted vibration-proof structure will be used as overall replaceable units it is at different levels maintenance systems and
Changed in field trial.
As shown in figure 4, the installation of vibration-proof structure and electro-optical system is simple, convenient, it is low to change environmental requirement.First, remove
M6 fixing bolts between vibration-proof structure upper end cover and bottom end cover, rotation upper end cover are removed from the bottom up to adjacent mounting hole
Upper end cover.Then, the shock-damping structure for removing upper end cover is moved to the installation surface of electro-optical system from top to bottom, rotates vibration damping knot
Structure, its mounting hole is alignd with electro-optical system mounting hole, and be fixed with 6 M6 bolt.Then, upper end cover is connected into electricity
The hanging interface of cable is tightened in the communication interface of electro-optical system.Finally, upper end cover is assembled to the vibration damping with electro-optical system
In structure.Whole installation process can be completed entirely to install to equipment and personal security by 1 M6 inner hexagon spanner.
Claims (2)
- A kind of 1. composite damping structure for airborne lidar for fluorescence, it is characterised in that：Including 1 circular upper lid, 1 with The circular bottom end cover that airborne platform is connected, 1 circular carrier being connected with electro-optical system, the steel wire of N number of circumference uniform distribution The cable of rope shock absorber, the rubber shock absorber of N number of circumference uniform distribution, 1 connection electro-optical system and host computer；Upper end cover and bottom end cover It is connected by bolt, forms the sealed internal chamber of a column, carrier is installed in inner chamber centre position, and inner chamber is divided into Lower two chambers；Lower intracavitary, N number of wire rope damper and N number of rubber shock absorber are evenly arranged along carrier circumferencial direction, and passed through Bolt is separately fixed on carrier and bottom end cover, and wire rope damper and rubber shock absorber are alternately arranged；Upper intracavitary, is disposed with The connecting cable of electro-optical system and host computer.
- A kind of 2. composite damping structure for airborne lidar for fluorescence according to claim 1, it is characterised in that：Upper end cover Medial surface has a segmentation positive stop lug boss of radial direction, and carrier lateral surface has a stopper slot of segmentation, the segmentation positive stop lug boss of upper end cover and The stopper slot of carrier can be coordinated by rotation mode.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2017102693855 | 2017-04-24 | ||
| CN201710269385 | 2017-04-24 |
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| Publication Number | Publication Date |
|---|---|
| CN107606020A true CN107606020A (en) | 2018-01-19 |
| CN107606020B CN107606020B (en) | 2019-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710700056.1A Active CN107606020B (en) | 2017-04-24 | 2017-08-16 | A kind of composite damping structure for airborne lidar for fluorescence |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110873187A (en) * | 2018-08-29 | 2020-03-10 | 中国科学院长春光学精密机械与物理研究所 | Sealing vibration damper for airborne photoelectric equipment and airborne photoelectric equipment |
| CN114060460A (en) * | 2021-11-25 | 2022-02-18 | 武汉华中天经通视科技有限公司 | On-hook device of photoelectric turret |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1067948A (en) * | 1991-06-17 | 1993-01-13 | 华中理工大学 | Combined shock isolating unit |
| US5710945A (en) * | 1996-07-03 | 1998-01-20 | Mcmahon Helicopter Services, Inc. | Resilient camera mount usable on a helicopter |
| CN102410329A (en) * | 2011-09-10 | 2012-04-11 | 中国兵器工业第二〇六研究所 | Compound vibration-isolating and buffering device |
| KR20120132741A (en) * | 2011-05-30 | 2012-12-10 | 재단법인 국방기술품질원 | Device for preventing malfunctioning of helicopter radio altimeter |
| CN202627441U (en) * | 2012-07-11 | 2012-12-26 | 中国人民解放军总参谋部工程兵科研三所 | Rapid assembling type shock-insulating floor |
| CN203889080U (en) * | 2014-06-05 | 2014-10-22 | 中孚航空科技（天津）有限公司 | Vertical lifting holder device of unmanned aerial vehicle |
-
2017
- 2017-08-16 CN CN201710700056.1A patent/CN107606020B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1067948A (en) * | 1991-06-17 | 1993-01-13 | 华中理工大学 | Combined shock isolating unit |
| US5710945A (en) * | 1996-07-03 | 1998-01-20 | Mcmahon Helicopter Services, Inc. | Resilient camera mount usable on a helicopter |
| KR20120132741A (en) * | 2011-05-30 | 2012-12-10 | 재단법인 국방기술품질원 | Device for preventing malfunctioning of helicopter radio altimeter |
| CN102410329A (en) * | 2011-09-10 | 2012-04-11 | 中国兵器工业第二〇六研究所 | Compound vibration-isolating and buffering device |
| CN202627441U (en) * | 2012-07-11 | 2012-12-26 | 中国人民解放军总参谋部工程兵科研三所 | Rapid assembling type shock-insulating floor |
| CN203889080U (en) * | 2014-06-05 | 2014-10-22 | 中孚航空科技（天津）有限公司 | Vertical lifting holder device of unmanned aerial vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110873187A (en) * | 2018-08-29 | 2020-03-10 | 中国科学院长春光学精密机械与物理研究所 | Sealing vibration damper for airborne photoelectric equipment and airborne photoelectric equipment |
| CN110873187B (en) * | 2018-08-29 | 2021-02-12 | 中国科学院长春光学精密机械与物理研究所 | Sealing vibration damper for airborne photoelectric equipment and airborne photoelectric equipment |
| CN114060460A (en) * | 2021-11-25 | 2022-02-18 | 武汉华中天经通视科技有限公司 | On-hook device of photoelectric turret |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107606020B (en) | 2019-05-31 |
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