CN105757164A - Vibration reducing mechanism suitable for infrared camera on aircraft - Google Patents
Vibration reducing mechanism suitable for infrared camera on aircraft Download PDFInfo
- Publication number
- CN105757164A CN105757164A CN201610217074.XA CN201610217074A CN105757164A CN 105757164 A CN105757164 A CN 105757164A CN 201610217074 A CN201610217074 A CN 201610217074A CN 105757164 A CN105757164 A CN 105757164A
- Authority
- CN
- China
- Prior art keywords
- screw
- vibration reducing
- infrared camera
- cushion blocking
- aircraft
- Prior art date
- 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.)
- Pending
Links
- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000000903 blocking effect Effects 0.000 claims description 20
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 238000013016 damping Methods 0.000 description 5
- 238000003384 imaging method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 2
- 206010019133 Hangover Diseases 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B43/00—Washers or equivalent devices; Other devices for supporting bolt-heads or nuts
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Studio Devices (AREA)
- Photometry And Measurement Of Optical Pulse Characteristics (AREA)
Abstract
A vibration reducing mechanism suitable for an infrared camera on an aircraft is composed of a flange plate and four dampers (2) which are evenly arranged at the periphery of the flange plate (1). Each damper (2) comprises a screw (3), a limiting lining (4), a vibration reducing pad A (5), a vibration reducing pad B (7) and a limiting gasket (6), wherein the screw (3) penetrates through the damper (2) to fix the damper on an installation base surface, the vibration reducing pad A (5) and the vibration reducing pad B (7) are respectively arranged on the left side and the right side of the screw (3) penetrating through the flange plate (1), and the limiting lining (4) and the limiting gasket (6) are respectively and additionally arranged at the left ends and the right ends of the vibration reducing pad A (5) and the vibration reducing pad B (7).
Description
Technical field
This technology belongs to damper mechanism field, is specifically related to a kind of damper mechanism being adapted on aircraft infrared camera.
Background technology
Development along with modern science and technology, numerous weapon models and satellite more and more start to be equipped with infreared imaging device, infreared imaging device utilizes the heat radiation temperature difference of target and background, the image forming target and surrounding scenes realizes the homing guidance of aircraft, infrared image resolution is high, dynamic range is big, capacity of resisting disturbance is strong, and owing to adopting passive detection, disguised better.High-end Infrared Detectors mainly comprises high sensitivity infrared focal plane detector Dewar component and integrated sterling refrigerating machine, and both sensitivity is all significantly high, and device can be brought very big harm by mechanical vibration.The impact of vibration in various degree, impact and overload is being launched and be subjected in running to the aerospace craft of the structural load such as carrier rocket, guided missile, generation is had a strong impact on by the interference of vibration for normal use of the various instrument and equipment in body inside, strong vibration directly results in the reliability decrease of guided missile structure, destroy the normal operation of the high-precision equipments such as Infrared Detectors, therefore, how to improve the vibration environment in instrument room, avoid the covibration of instrument and equipment in cabin particularly important.In order to ensure the normal operation of infrared camera in emission process, it is necessary to reasonably design vibration-proof structure for infrared camera, it is ensured that this mechanism has a sufficiently large damping efficiency, and make the infrared camera can blur-free imaging.
Summary of the invention
It is an object of the invention to: by installing rational damper mechanism on the body of infrared camera, vibration source and infrared camera are kept apart, the damping vibration impact on camera, improves the distribution form of vibroshock simultaneously, it is to avoid the driving frequency of vibration source produces resonance with infrared camera system.
Technical scheme is as follows: a kind of damper mechanism being adapted on aircraft infrared camera, by ring flange with form at four vibroshocks that ring flange surrounding is uniform, vibroshock includes screw, limiting bush, cushion blocking A, cushion blocking B, spacing shim, wherein screw is fixed on installation base surface through vibroshock, and the left and right sides of screw traverse ring flange is separately installed with cushion blocking A, cushion blocking B, the left and right end at cushion blocking A, cushion blocking B installs limiting bush 4 and spacing shim 6 respectively additional.
Screw is M5 screw.
The remarkable result of the present invention is in that: after vibration damping, the damping efficiency of damping assembly, line/angular frequency and peak value amplification all can meet the designing requirement that aircraft is overall, ensure infrared camera system normal operation under severe vibration environment, and ensure that imaging is without hangover and blooming.
Accompanying drawing explanation
Fig. 1 is a kind of damper mechanism front view being adapted on aircraft infrared camera of the present invention
Fig. 2 is a kind of damper mechanism left view being adapted on aircraft infrared camera of the present invention
Fig. 3 is a kind of damper mechanism amortisseur schematic diagram being adapted on aircraft infrared camera of the present invention
In figure: 1 ring flange, 2 vibroshocks, 3 screws, limit 4 linings, 5 cushion blocking A, 6 spacing shims, 7 cushion blocking B, 8 infrared cameras
Detailed description of the invention
Below in conjunction with drawings and the specific embodiments, the present invention is described in further detail.
A kind of damper mechanism being adapted on aircraft infrared camera, by ring flange with form at four vibroshocks 2 that ring flange 1 surrounding is uniform, vibroshock 2 includes screw 3, limiting bush 4, cushion blocking A5, cushion blocking B7, spacing shim 6, wherein screw 3 is fixed on installation base surface through vibroshock 2, and the left and right sides of screw 3 traverse ring flange 1 is separately installed with cushion blocking A5, cushion blocking B7, the left and right end at cushion blocking A5, cushion blocking B7 installs limiting bush 4 and spacing shim 6 respectively additional.Screw 3 is M5 screw.
Claims (2)
1. the damper mechanism being adapted on aircraft infrared camera, it is characterized in that: by ring flange with form four vibroshocks (2) that ring flange (1) surrounding is uniform, vibroshock (2) includes screw (3), limiting bush (4), cushion blocking A (5), cushion blocking B (7), spacing shim (6), wherein screw (3) is fixed on installation base surface through vibroshock (2), and the left and right sides of screw (3) traverse ring flange (1) is separately installed with cushion blocking A (5), cushion blocking B (7), in cushion blocking A (5), the left and right end of cushion blocking B (7) installs limiting bush (4) and spacing shim (6) respectively additional.
2. the damper mechanism that a kind of according to claim is adapted on aircraft infrared camera, it is characterised in that: screw (3) is M5 screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610217074.XA CN105757164A (en) | 2016-04-08 | 2016-04-08 | Vibration reducing mechanism suitable for infrared camera on aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610217074.XA CN105757164A (en) | 2016-04-08 | 2016-04-08 | Vibration reducing mechanism suitable for infrared camera on aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105757164A true CN105757164A (en) | 2016-07-13 |
Family
ID=56334539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610217074.XA Pending CN105757164A (en) | 2016-04-08 | 2016-04-08 | Vibration reducing mechanism suitable for infrared camera on aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105757164A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108121048A (en) * | 2017-12-05 | 2018-06-05 | 北京空间机电研究所 | A kind of adaptive rigging error of Space Remote Sensors and transmitting principal piece isolation mounting |
| CN109268446A (en) * | 2018-10-25 | 2019-01-25 | 湖北航天技术研究院总体设计所 | The stand-alone device mounting device and aircraft of tandem three-dimensional vibration damping |
| CN109449591A (en) * | 2018-10-25 | 2019-03-08 | 湖北航天技术研究院总体设计所 | Active radar and passive radar seeker antenna cover and aircraft |
| CN114215870A (en) * | 2021-11-29 | 2022-03-22 | 北京空间机电研究所 | Metal rubber combined vibration isolation device of space remote sensing camera and installation method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1824579A (en) * | 2006-03-31 | 2006-08-30 | 郑钢铁 | Integral vibration isolation platform of astrovehicle |
| CN201027898Y (en) * | 2006-12-18 | 2008-02-27 | 中国科学院长春光学精密机械与物理研究所 | Vibration damping structure for aviation optical remote sensing device |
| CN101871505A (en) * | 2010-06-12 | 2010-10-27 | 江苏大学 | Positive and negative stiffness parallel three-translation vibration and impact isolation platform |
| CN201837394U (en) * | 2010-10-28 | 2011-05-18 | 中国航天科工集团第二研究院二一〇所 | Vibration-isolating installing device of inertial measurement unit for strapdown laser gyroscope |
| CN103410911A (en) * | 2013-08-05 | 2013-11-27 | 上海宇航***工程研究所 | Payload vibration reduction device adapted to space environment application |
| CA2850810A1 (en) * | 2013-05-08 | 2014-11-08 | Leonard T. Chapman | Invertible vertical axis shock and vibration isolator for a camera |
-
2016
- 2016-04-08 CN CN201610217074.XA patent/CN105757164A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1824579A (en) * | 2006-03-31 | 2006-08-30 | 郑钢铁 | Integral vibration isolation platform of astrovehicle |
| CN201027898Y (en) * | 2006-12-18 | 2008-02-27 | 中国科学院长春光学精密机械与物理研究所 | Vibration damping structure for aviation optical remote sensing device |
| CN101871505A (en) * | 2010-06-12 | 2010-10-27 | 江苏大学 | Positive and negative stiffness parallel three-translation vibration and impact isolation platform |
| CN201837394U (en) * | 2010-10-28 | 2011-05-18 | 中国航天科工集团第二研究院二一〇所 | Vibration-isolating installing device of inertial measurement unit for strapdown laser gyroscope |
| CA2850810A1 (en) * | 2013-05-08 | 2014-11-08 | Leonard T. Chapman | Invertible vertical axis shock and vibration isolator for a camera |
| CN103410911A (en) * | 2013-08-05 | 2013-11-27 | 上海宇航***工程研究所 | Payload vibration reduction device adapted to space environment application |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108121048A (en) * | 2017-12-05 | 2018-06-05 | 北京空间机电研究所 | A kind of adaptive rigging error of Space Remote Sensors and transmitting principal piece isolation mounting |
| CN109268446A (en) * | 2018-10-25 | 2019-01-25 | 湖北航天技术研究院总体设计所 | The stand-alone device mounting device and aircraft of tandem three-dimensional vibration damping |
| CN109449591A (en) * | 2018-10-25 | 2019-03-08 | 湖北航天技术研究院总体设计所 | Active radar and passive radar seeker antenna cover and aircraft |
| CN109449591B (en) * | 2018-10-25 | 2021-08-03 | 湖北航天技术研究院总体设计所 | Active and passive radar seeker antenna housing and aircraft |
| CN114215870A (en) * | 2021-11-29 | 2022-03-22 | 北京空间机电研究所 | Metal rubber combined vibration isolation device of space remote sensing camera and installation method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160713 |
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| RJ01 | Rejection of invention patent application after publication |