CN107606020B - 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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- CN107606020B CN107606020B CN201710700056.1A CN201710700056A CN107606020B CN 107606020 B CN107606020 B CN 107606020B CN 201710700056 A CN201710700056 A CN 201710700056A CN 107606020 B CN107606020 B CN 107606020B
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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 round lower cover being connected with airborne platform, 1 round carrier being connected with electro-optical system, the wire rope damper of 8 circumference uniform distributions and the rubber shock absorber of 8 circumference uniform distributions, the cable of 1 connection electro-optical system and host computer.Upper end cover is connected with lower cover by bolt, forms a columnar sealed internal chamber, carrier is installed in inner cavity middle position, and inner cavity is divided into two chambers up and down.Under it is intracavitary, be evenly arranged 8 wire rope dampers and 8 rubber shock absorbers along carrier circumferencial direction；Upper intracavitary arrangement 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 internal component of vibration-proof structure is sufficiently spaced from external adverse circumstances, ensure that higher Flight Line Maintenance and reliability.
Description
Technical field
The invention belongs to airborne photoelectric antivibration areas, are 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 applied to positioning accuracy the vibration isolation and context buffer the advantages of
The airborne photoelectric system that more demanding, electro-optical system inherent space constraints, use temperature range are wide, vibration and shock environment are more severe
System.
Background technique
Vital task equipment of the electro-optical system as aircraft platform has the operation such as battle reconnaissance, target following and instruction
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.It is mounted on inside electro-optical system currently, vibration-proof structure is usually integrated, this mounting means is occupying
Inside electro-optical system while the useful space, the maintenance difficulty of vibration-proof structure is increased.Also, in recent years, with military affairs
The diversified demand of development, it is desirable that airborne lidar for fluorescence develops towards lightness, miniaturization and intelligent direction, so that existing light
The vibration-proof structure of electric system has been unable to satisfy the growth requirement of electro-optical system, thus, design that a kind of maintainability is high, it is novel to be suitable for
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. also having positioning accuracy request to the existing insulated degree requirement of vibration-proof structure；3. the useful space is narrow inside electro-optical system,
It is larger in interior design vibration-proof structure difficulty；4. it is more demanding to loss of weight, therefore be difficult to obtain biggish support stiffness；5. using
Environment is complicated, various, the influence vulnerable to 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
1. meter, which has the disadvantage in that, occupies the useful space narrow inside electro-optical system, can not reduce electro-optical system size；2. increasing
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-time service
It is low；4. damper service is poor, replaces or need to remove internal photoelectric sensor when maintaining damper.
Summary of the invention
The shortcomings that overcome current airborne lidar for fluorescence vibration-proof structure, adapts 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 solution of the present invention is as follows:
A kind of composite damping structure for airborne lidar for fluorescence, it is characterised in that: including 1 circular upper
Lid, 1 round lower cover being connected with airborne platform, 1 round carrier being connected with electro-optical system, N number of circumference are equal
The rubber shock absorber of the wire rope damper of cloth, N number of circumference uniform distribution, the cable of 1 connection electro-optical system and host computer；Upper end cover
It is connected with lower cover by bolt, forms a columnar sealed internal chamber, carrier is installed in inner cavity middle position, and will be interior
Chamber is divided into two chambers up and down；Under it is intracavitary, be evenly arranged N number of wire rope damper and N number of rubber damping along carrier circumferencial direction
Device, and be separately fixed on carrier and lower cover by bolt, 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 diameter
To segmentation positive stop lug boss, carrier lateral surface has a limiting slot of segmentation, the limit of the segmentation positive stop lug boss and carrier of upper end cover
Position slot can be cooperated by rotation mode.
Beneficial effect
The beneficial effects of the present invention are embodied in the following aspects:
1, vibration-proof structure is outer inside electro-optical system to move between electro-optical system and carrier aircraft platform, increase electro-optical system
The internal useful space realizes that lightness, miniaturization create conditions for electro-optical system.
2, in terms of environmental suitability, using the composite design of two kinds of dampers, it is resistance to overcome current single rubber shock absorber
The disadvantage of high temperature, low temperature properties difference.
3, anti-vibration and impact aspect, wirerope 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 entire frequency range of carrier aircraft.Rubber shock absorber has higher punching
Rigidity is hit, shock resistance deformation is conducive to, it is big to overcome wire rope damper static deflection for the combined vibration-damping of rubber and wirerope
The shortcomings that.
4, 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 being declined using effectiveness in vibration suppression greatly extends the use longevity of vibration-proof structure by being used in combination with wire rope damper
Life.
5, in terms of the maintainability of electro-optical system, semi-enclosed external composite damping structure is configured as whole replaceable list
Member does not have to remove electro-optical system sensor, improves the maintainability of electro-optical system when outfield is safeguarded and is replaced.
Detailed description of the invention
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-lower cover, 2-carriers, 3-upper end covers, 4-carrier aircraft installation pedestals, 5-cable interfaces, 6-limits
Position slot, 7-wire rope dampers, 8-rubber shock absorbers, 9-connecting cables.
Specific 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 realizes 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
Internal component be sufficiently spaced from external adverse circumstances, ensure that higher Flight Line Maintenance and reliability.The vibration-proof structure packet
Include 1 circular upper lid, 1 round lower cover being connected with airborne platform, 1 round 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 lower cover by bolt, and a columnar sealed internal chamber is formed, and carrier is mounted in the lumen
Between position, and by inner cavity be divided into up and down two chambers.Under it is intracavitary, be evenly arranged 8 wire rope dampers along carrier circumferencial direction
With 8 rubber shock absorbers, and it is separately fixed on carrier and lower cover by bolt, wire rope damper and rubber shock absorber
It is alternately arranged；It is upper intracavitary, reasonable Arrangement the connecting cable of electro-optical system and host computer.
This composite structural design integrates the advantages of wirerope vibration damping and rubber damping, can solve current electro-optical system
It is varied with temperature by itself rubber shock absorber, the shortcomings that antivibration effect constantly decays, meanwhile, widen electro-optical system itself
Antivibration frequency bandwidth.In this structure, since 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 whole opposite electro-optical system mass axis of damper is symmetrical,
And symmetric position equal stiffness, therefore the vibration-proof structure is independent of each other to two kinds of vibrations of revolution and translation of electro-optical system, is formed non-
Couple vibration insulating system.For axial vibration and impact, sufficiently with wire rope damper and rubber shock absorber to the excellent of vibration isolation
Point well solves damping and the intrinsic contradiction of this damper of rigidity, and circumferential uniformly installation, reduce vibration-proof structure by
Caused by installation deviation while life loss, and round limiting slot guarantees electro-optical system always perpendicular to Aircraft together
To；For horizontally vibrating and impacting, due to the installation form of vibration-proof structure, which is carrying out the same of antivibration and buffering
When, the vibration inclination of energy timely correction electro-optical system axis has axis self-calibrating capabilities.For the revolution fortune around three axis
It is dynamic, due to being symmetrically installed for damper, a torque directly proportional, contrary with angular dimension is disturbed will be formed, will be had pair
The self-correcting capability of rotary motion.
The invention will be further described with reference to the accompanying drawing.
As shown in Figure 1, Figure 3, for the present invention using integration, compact structure design, vibration-proof structure is designed as one can
The semi-enclosed device of integral replacing.Upper end cover 3 and lower cover 1 form a columnar cavity, carrier 2 by cylindrical cavities every
It is divided into two cavitys up and down, lower chamber installs wire rope damper and rubber shock absorber, two kinds of dampers are equal along carrier circumference
Even distribution, blending bolt are fixed on lower cover and carrier, are vibration isolation in damper structure, buffering device.Under upper cavity
The opening in portion is for installing electro-optical system, and after installation, upper end cover, carrier and electro-optical system form a semi-enclosed chamber
Body blocks 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, is limited the peak swing of electro-optical system, be ensure that the higher positioning accuracy of electro-optical system；
Connecting cable in epicoele is for connecting electro-optical system and host computer.Operating temperature is -40 DEG C~+65 DEG C, and antivibration is horizontal: >=
2g, shock resistance are horizontal: vertical >=20g, level >=15g.
As shown in Fig. 2, this vibration-proof structure replaceable units as a whole, composition includes: lower cover 1, carrier 2, on
End cap 3, carrier aircraft installation pedestal 4, cable interface 5, limiting slot 6, wire rope damper 7, rubber shock absorber 8, connecting cable 9.Its
Installation steps are as follows:
Step 1: lower 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 bolt are fixed on lower cover
Position；
Step 3: carrier is put into from top to bottom in the structure assembled, rotates carrier, makes its mounting hole and each
The alignment of damper mounting hole, and be fixed with M4 bolt；
Step 4: cable interface is mounted on to the interface installation position of upper end cover with 4 M3 bolts；
Step 5: by upper end cover positive stop lug boss and carrier indentation, there be aligned, move from top to bottom upper end cover until
It is contacted with lower end cap surface, rotates to adjacent mounting hole clockwise or counterclockwise, at this point, positive stop lug boss is just at holding
In limiting slot on load plate, and upper end cover and lower cover are fixed with M6 bolt.
By above five steps, mounted vibration-proof structure will as a whole replaceable units in maintenance systems at different levels and
It is replaced in field trial.
As shown in figure 4, the installation of vibration-proof structure and electro-optical system is simple, convenient, replacement environmental requirement is low.Firstly, removing
M6 fixing bolt between vibration-proof structure upper end cover and lower cover rotates upper end cover to adjacent mounting hole, removes from the bottom up
Upper end cover.Then, the shock-damping structure for removing upper end cover is moved to the mounting surface of electro-optical system from top to bottom, rotates vibration damping knot
Structure is aligned its mounting hole with electro-optical system mounting hole, and is fixed with the bolt of 6 M6.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 is to equipment and personnel safety, by the allen wrench of 1 M6 with regard to achievable entire installation.
Claims (2)
1. a kind of composite damping structure for airborne lidar for fluorescence, it is characterised in that: including 1 circular upper lid, 1 with
The round lower cover that airborne platform is connected, 1 round carrier being connected with electro-optical system, the steel wire of N number of circumference uniform distribution
The rubber shock absorber of rope damper, N number of circumference uniform distribution, the cable of 1 connection electro-optical system and host computer；
The circle lower cover is hollow structure, and there is an inside circular table in the lower end of round lower cover, under round lower cover
There is the auricle of connection airborne platform in end outside；
The upper end of the circle lower cover is bolted to connection with the circular upper lid, and formation one is columnar closed interior
Chamber；
The circle carrier is hollow stepped cylindrical structure；Round carrier upper end major diameter section lateral surface and circular upper lid
Inner cavity is divided into two chambers up and down by medial surface connection, wherein cavity of resorption be by round carrier step surface, round carrier path section outside
The annular housing of side, round lower cover medial surface and round lower cover circular table composition；
Under it is intracavitary, be evenly arranged N number of wire rope damper and N number of rubber shock absorber along carrier circumferencial direction, and pass through spiral shell
Bolt is separately fixed on the round carrier and the round lower cover, and wire rope damper and rubber shock absorber replace cloth
It sets；It is upper intracavitary, it is disposed with the connecting cable of electro-optical system and host computer.
2. a kind of composite damping structure for airborne lidar for fluorescence according to claim 1, it is characterised in that: upper end cover
Medial surface has a radial segmentation positive stop lug boss, and carrier lateral surface has a limiting slot of segmentation, the segmentation positive stop lug boss of upper end cover and
The limiting slot of carrier can be cooperated by rotation mode.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710269385 | 2017-04-24 | ||
| CN2017102693855 | 2017-04-24 |
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| Publication Number | Publication Date |
|---|---|
| CN107606020A CN107606020A (en) | 2018-01-19 |
| CN107606020B true 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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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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 |
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| CN107606020A (en) | 2018-01-19 |
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