CN108801574A - The verification system of spacecraft high score camera optical axis jitter performance - Google Patents
The verification system of spacecraft high score camera optical axis jitter performance Download PDFInfo
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- CN108801574A CN108801574A CN201810617609.1A CN201810617609A CN108801574A CN 108801574 A CN108801574 A CN 108801574A CN 201810617609 A CN201810617609 A CN 201810617609A CN 108801574 A CN108801574 A CN 108801574A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/06—Multidirectional test stands
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Abstract
The invention discloses a kind of verification systems of spacecraft high score camera optical axis jitter performance, including ground simulator, 2 vibration-isolating platforms and target simulator, wherein simulator and target simulator are separately positioned on two vibration-isolating platforms, by the position for adjusting each mirror of parallel light tube on vibration-isolating platform two, so that the source of parallel light that target simulator is sent out, the tested payload reception being arranged on another vibration-isolating platform one, optical jitter micro-vibration operating mode is simulated into row energization to tested load by spacecraft high resolution camera optical jitter micro-vibration source ground simulator.The present invention can accurate simulation go out the micro-vibration rule of the high-precisions such as camera load optical axis under interference source working condition, and the influence size that vibration source shakes camera optical axis, the validity of authentication image quality assurance means and the validity etc. of offline image restoration methods are disturbed by the system evaluation satellite.
Description
Technical field
The invention belongs to spacecraft interference source micro-vibrations to test field, and in particular to a kind of spacecraft high score camera optical axis is trembled
The verification system of dynamic performance.
Background technology
Continuous improvement with satellite spatial camera to requirements such as spatial resolutions, in-orbit micro-vibration on certain satellites
Environmental requirement is extremely stringent, and being undertaken for task also requires celestial body that must have extremely low in-orbit micro-vibration environment, such as high-resolution
Rate earth observation systems.Therefore the superior high-precision camera of various designs, performance and precision will be special far more than current version
Not being high-resolution performance requirement causes spacecraft to increase the susceptibility of micro-vibration, and celestial body is shaken a little to image quality
Influence be can not ignore, when the influence that disturbance amplitude generates camera imaging quality reaches unacceptable degree, it is necessary to take
Effective measures are inhibited or are compensated.
Currently, the image quality under the influence of high-precision payload micro-vibration can only be verified by simulation analysis, lack
The verification means of subsystem grade can only deliver and carry out system-level test verification after AIT on whole star, cause to verify it is of high cost,
Period is long, risk is big, once test result cannot be met the requirements, will seriously affect development progress.If interference can be provided accurately
The micro-vibration rule of the high-precisions such as camera load optical axis under the working condition of source, then can by build corresponding simplation verification device with
Analysis system was just adequately examined and is verified to it in the payload development stage.
Invention content
Based on this, goal of the invention of the invention is to provide a kind of verification system of spacecraft high score camera optical axis jitter performance
System, by establishing relevant micro-vibration simulation and test platform, in conjunction with the measurements dress such as imaging target, camera, integrated measuring instrument
It sets and analytical equipment, forms the verification system of complete set, the principle prototype and engineering prototype for carrying out compact camera are dry
Optical jitter performance test is verified under the influence of disturbing source, and assessment satellite disturbs the influence size that vibration source shakes camera optical axis, proof diagram
The validity of image quality amount Means of Ensuring verifies the validity of the offline image restoration methods based on inflight measurement information.
Purpose of the present invention is to what is be achieved through the following technical solutions：
For micro-vibration image-forming detecting system characteristic, two kinds of trystates i.e. two kinds of optical jitter generation sides are set herein
Formula is camera exciting and target exciting respectively.
The verification system of spacecraft high score camera optical axis jitter performance, including spacecraft high resolution camera optical jitter are micro-
Vibration source ground simulator, vibration-isolating platform and target simulator, wherein above-mentioned simulator is arranged on vibration-isolating platform one, mesh
It marks simulator to be arranged on another vibration-isolating platform two, vibration-isolating platform one includes vibration isolation air bag, marble countertop and aluminium alloy switching
Table top, several vibration isolation bladder supports are in marble countertop bottom, and aluminium alloy transfers table top setting on marble countertop, Dali
Stone table board liftable；Target simulator is collectively constituted by integrating sphere, target and parallel light tube, and integrating sphere sends out uniform optical transport
To parallel light tube, parallel light tube is the microscope group for target plane being placed in using optical means infinite point, mainly by off-axis parabolic
Face mirror and mirror two parts composition of turning back, light source penetrate target plane again after mirror of turning back is reflected into primary mirror, formation collimated light beam, most
Enter afterwards and is tested load；Wherein, vibration-isolating platform two is optics vibration-isolating platform, by adjusting each mirror of parallel light tube on vibration-isolating platform two
Position so that the source of parallel light that target simulator is sent out, the tested payload reception being arranged on another vibration-isolating platform one,
By spacecraft high resolution camera optical jitter micro-vibration source ground simulator to being tested load into row energization come simulated light
Dither axis micro-vibration operating mode.
Wherein, two kinds of situations of defocus and in-orbit camera optical axis micro-vibration are simulated by target vibration respectively, is tested carries at this time
Lotus and parallel light tube on the same vibration-isolating platform (i.e. vibration-isolating platform two), target simulator sends out source of parallel light, is tested load
Source of parallel light is received, is tested by encouraging target.
Wherein, the primary mirror of parallel light tube and catadioptric mirror have corresponding supporting support respectively, are separately fixed at vibration-isolating platform two
On, optical axis and position of focal plane are demarcated using interferometer and plane mirror.
Further, connecting platform is added to place translation stage mechanism at two edge of vibration-isolating platform.
Further, by integrating sphere light-emitting window and target center close proximity to reduce the influence to imagewise uniform.
Further, optical axis height adjusts primary mirror, folding on the basis of the height at primary mirror center to vibration-isolating platform with this height
The height of anti-mirror and integrating sphere.
Wherein, it is camera to be tested load.
Wherein, high resolution camera optical jitter micro-vibration source ground simulator, mainly include bearing system part with
And excitation system part, the bearing system part for bearing test load mainly it is supported by mounting plate and bottom six
Degree of freedom tooling forms；It includes vibrator, exciting rod, control sensor, control to provide the excitation system part quantitatively encouraged mainly
System processed, wherein vibrator one end is fixed on hoistable platform, and the other end passes through activation lever, the control being pasted onto in transfer block
Sensor is connected with mounting plate, then adjust hoistable platform height, the control sensor installed between mounting plate and activation lever into
The monitoring of row output mechanics parameter, using single-point control mode, computer control system output drive signal, after zero-bit is modulated
It is input to vibrator after being output to signal amplifier amplification, so that table top is generated vibration, the response at control point will by control sensor
Mechanics parameter feeds back to calculating control system and is compared and corrects, and the mechanics parameter that drive signal generates on vibrator is made to ring
Requirement of experiment should be met.
Apparatus of the present invention have the ability of fabulous isolation external disturbance, can provide strong item for camera optical axis joggling test
Part.Also, apparatus of the present invention can provide two kinds of optical jitter producing methods, be camera exciting and target exciting, Jin Erke respectively
The Multitests Verification Projects such as the in-orbit optical jitter of high split-phase motor, defocus are realized on the ground.
Description of the drawings
Fig. 1 is the structural schematic diagram of vibration-isolating platform one in present system.
Wherein：11, air spring is damped greatly, 12, marble countertop, 13 aluminium alloys are transferred table top.
Fig. 2 is the structural schematic diagram of vibration-isolating platform two in present system；
Wherein：21, air spring is damped greatly, 22, optics table top.
Fig. 3 be the present invention system in target simulator structural schematic diagram；
Wherein：31, integrating sphere, 32, target, 33, parallel light tube, wherein parallel light tube includes：331, it turns back mirror, 332, main
Mirror.
Fig. 4 is several frequently seen graticle pattern form；Wherein 4, graticle.
Fig. 5 is work of the verification system of the spacecraft high score camera optical axis jitter performance of the present invention in the case where camera encourages operating mode
Make schematic diagram；
Wherein：1, vibration-isolating platform 1,2, vibration-isolating platform 2,31, integrating sphere, 32, target, 33, parallel light tube, 331, turn back
Mirror, 332, primary mirror, 4, on the ground simulator of spacecraft high resolution camera optical jitter micro-vibration source, 5, camera, 6, one
Change measuring instrument.
Fig. 6 is work of the verification system of the spacecraft high score camera optical axis jitter performance of the present invention in the case where target encourages operating mode
Make schematic diagram；
Wherein：Reference numeral is the same as the respective description in Fig. 5.
Specific implementation mode
Below in conjunction with attached drawing, invention is further described in detail, but this is only exemplary, it is no intended to this
The protection domain of invention carries out any restrictions.
1, vibration isolation is installed in vibration-isolating platform 1, i.e. spacecraft high resolution camera optical jitter micro-vibration source ground simulator
Platform
The structural schematic diagram of vibration-isolating platform one in present system is shown referring to Fig. 1, Fig. 1；Wherein vibration-isolating platform 1 is by 4
13 3 a big damping air spring 11, marble countertop 12 and aluminium alloy switching table top parts form.4 big damping air
Spring 11 is supported in 12 bottom four corners of marble countertop, and 13 rigidity of aluminium alloy switching table top is connected on marble countertop 12
Face.12 mesa dimensions of marble countertop about 1.2m × 1.2m × 0.8m (length × width × height, height is adjustable), vibration-isolating platform is integrally solid
There is frequency to be less than 1.5Hz, quiet bearing capacity is more than 2000kg, and switching table top is equipped with installation interface.
The devices such as air source, control needed for mating vibration isolation air bag work.
2, vibration-isolating platform is installed in vibration-isolating platform 2, i.e. target and parallel light tube
The structural schematic diagram of vibration-isolating platform two in present system is shown referring to Fig. 2, Fig. 2；Wherein vibration-isolating platform 2 is by 6
A big damping air spring 21, optics table top 22 form, and 6 big damping air spring 21 is supported in 22 bottom four corners of optical table
And centre position, there are mounting holes for optics table top upper surface, for installing optical device.22 mesa dimensions of optical table are 1.5m
×6m×0.457m.The 6 groups big damping air spring of vibration-isolating platform can carry out automatic horizontal adjustment and can be effectively isolated the external world shaking
It is dynamic.Entire platform fundamental frequency is not higher than 1.5Hz.Wherein 5Hz or more extraneous vibrations response amplitude decaying 85%, 10Hz or more can
Decaying 90% meets high-precision optical test to external environment vibration isolation requirement.
The devices such as air source, control needed for mating vibration isolation air bag work.
3, target simulator
The structural schematic diagram of target simulator in the system of the present invention is shown referring to Fig. 3, Fig. 3；Mesh wherein in system
Mark simulator is collectively constituted by integrating sphere 31, target 32, parallel light tube 33, and parallel light tube 33 is using optical means target surface
(target) is placed in the microscope group of infinite point.Mainly by turning back mirror 331 and 332 two parts of primary mirror form.Integrating sphere 31 be installed on every
Shake 2 side of platform, and target 32 and parallel light tube 33 are secured by bolts on vibration-isolating platform 2, is adjusted and is put according to light path demand
Put method.Integrating sphere 31 generates light source and penetrates target 32 again after mirror 331 of turning back is reflected into primary mirror 332, formation collimated light beam, most
Enter camera afterwards.
(1), integrating sphere
Integrating sphere 31 sends out uniform optical transport to parallel light tube system, light-emitting window effective diameter Φ 45mm, irradiation level
For 1 solar constant.
(2), target
According to the difference that parallel light tube requires, target is equipped with graticle 4 on 32, and graticle 4 is carved with a variety of different patterns.Fig. 4
For several frequently seen graticle pattern form.(a) graticulated graticle is carved, the correction of instrument optical axis is commonly used in；(b) band
The graticle of angle differentiation, is commonly used in angle measurement；(c) there are one the graticles of aperture at center；(d) resolution chart is used for
The image quality of detection optical system.(e) graticle of several groups of lines at equal intervals, the directional light for measuring the focal length of lens are carried
Pipe.
According to experiment demand, selects line to being that resolution chart evaluates imaging effect herein, pass through the line pair of different size
Image quality to be assessed, x-ray is right/mm, refer to the line of how many root equidistantly distributed 1mm Nei, line is being tested overstocked
Influence of the vibration to imaging can not be identified in the process, need that a most suitable demand pairs regional imaging is selected to comment as reference
Estimate, selected in this system 40 lines it is right/mm be used as with reference to assess.
(3), parallel light tube
33 system of parallel light tube is made of primary mirror 332, catadioptric mirror 331, and integrating sphere 31 is responsible for sending out for light source, effectively
Improve light source efficiency and uniformity.Catadioptric mirror 331 is plane mirror, by mirror body bottom surface when light source is switched to integrating sphere
When, the light source sent out in integrating sphere 31 can be all refracted to primary mirror 332 by light path through target surface 32 using catadioptric mirror 331, most
Whole primary mirror 332 is by the parallel outflow of light path.
Arrangement method：
Light path is simulated with software, best optics placement position is selected, using interferometer and plane mirror to optical axis
It is demarcated with position of focal plane.By integrating sphere light-emitting window and target center close proximity to reduce the shadow to imagewise uniform
It rings.Optical axis height adjusts primary mirror 332, catadioptric mirror 331 on the basis of primary mirror 332 center to the height of vibration-isolating platform, with this height
And the height of integrating sphere 31.
Parallel light tube design parameter
(a) primary mirror clamping mechanism and its supporting mechanism design parameter
Primary mirror is for receiving the light from catadioptric mirror, and by light path parallel transmission to camera.Its clear aperture Φ 500mm,
Off-axis angle is 10 °.Minute surface silvered reflective film adds SiO protective films, and average reflectance is not small within the scope of 0.3 μm of -14.0 μm of spectral coverage
In 95%.
(b) catadioptric mirror design parameter
The light that integrating sphere 31 is sent out all is reflexed to primary mirror 332, clear aperture Φ 350mm, face shape by catadioptric mirror 331
The λ of precision≤0.025, flatness<0.2 λ, minute surface silvered reflective film add SiO protective films, are put down within the scope of 360nm-2600nm spectral coverages
Equal reflectivity is not less than 95%.
4, it is directed to micro-vibration image-forming detecting system characteristic, sets two kinds of trystates i.e. two kinds of optical jitter generation sides herein
Formula is camera exciting and target exciting respectively.Including vibration-isolating platform 1, vibration-isolating platform 2, target simulator 3, spacecraft high-resolution
Rate camera optical axis shakes micro-vibration source ground simulator (referring to Chinese patent CN201810612597.3) 4, camera 5, one
Change measuring instrument 6 etc..
The structure of spacecraft high resolution camera optical jitter micro-vibration source ground simulator 4 is disclosed in Chinese patent
In CN201810612597.3, wherein the device mainly includes bearing system part and excitation system parts, for carrying examination
The six degree of freedom tooling that the bearing system part of load mainly supports it by mounting plate and bottom is tested to form；It provides quantitative sharp
The excitation system part encouraged includes mainly vibrator, exciting rod, control sensor, control system, wherein vibrator one end is fixed
Onto hoistable platform, the other end is connected by activation lever, the control sensor being pasted onto in transfer block with mounting plate, is then adjusted
Hoistable platform height, the control sensor installed between mounting plate and activation lever carries out the monitoring of output mechanics parameter, using list
Point control mode, computer control system output drive signal input after being output to signal amplifier amplification after zero-bit is modulated
To vibrator, table top is made to generate vibration, mechanics parameter is fed back to calculating control system by the response at control point by control sensor
It is compared and corrects, the mechanics parameter response that drive signal generates on vibrator is made to meet requirement of experiment.The device is main
For the simulation optical jitter experiment of camera exciting, the tested load such as camera is installed on above-mentioned spacecraft high resolution camera optical axis
It shakes on the mounting plate in the ground simulator of micro-vibration source, camera, the pitching of integrated measuring instrument, yaw is given by the device
The quantitative micro-vibration of two states is simulated, which can be found in Chinese patent CN201810612597.3.
(1), camera exciter test：The spacecraft high score camera optical axis jitter performance of the present invention is shown referring to Fig. 5, Fig. 5
Verification system camera encourage operating mode under structural schematic diagram.Under the operating mode, camera 5, integrated measuring instrument 6 are fixed on space flight
4 on the ground simulator of device high resolution camera optical jitter micro-vibration source, spacecraft high resolution camera optical jitter is micro- to shake
Dynamic source ground simulator 4 is fixed on vibration-isolating platform 1 again.The installation fixed form of target simulator is as previously described, from every
The platform 2 that shakes sends out source of parallel light, and camera 5, integrated measuring instrument 6 receive source of parallel light in another vibration isolation table, pass through space flight
Device high resolution camera optical jitter micro-vibration source ground simulator 4 carrys out analogue camera optical jitter.It can be real by the layout
Exciting now is carried out without influencing parallel light tube light path on camera, is carried out " camera exciting simulates optical jitter experiment ".
(2), target exciter test：It is vibrated by target 32 referring to Fig. 6 and simulates defocus respectively and in-orbit camera optical axis is micro- shakes
Two kinds of situations are moved, the camera 5 and parallel light tube 33 are fixed on together on vibration-isolating platform 2, and target simulator 3 sends out directional light, phase
The tested payload reception source of parallel light such as machine 5, integrated measuring instrument 6 is tested by encouraging target.Target can pass through exciting
The various ways such as device excitation.The layout makes optical jitter minimize, and then carries out " target motion simulation optical jitter examination
Test ", " wavefront distortion measure experiment " and " defocus, which measures, to be tested " etc..
Although giving detailed description and explanation to the specific implementation mode of patent of the present invention above, it should be noted that
Be, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to the above embodiment, produced by
Function still covered without departing from specification and attached drawing spirit when, should all be within the protection domain of patent of the present invention.
Claims (7)
1. the verification system of spacecraft high score camera optical axis jitter performance, including spacecraft high resolution camera optical jitter is micro- shakes
Dynamic source ground simulator, vibration-isolating platform and target simulator, wherein above-mentioned simulator is arranged on vibration-isolating platform one, target
Simulator is arranged on another vibration-isolating platform two, and vibration-isolating platform one includes vibration isolation air bag, marble countertop and aluminium alloy through position
Face, several vibration isolation bladder supports are in marble countertop bottom, and aluminium alloy transfers table top setting on marble countertop, marble
Table top liftable；Target simulator is collectively constituted by integrating sphere, target and parallel light tube, and integrating sphere sends out uniform optical transport extremely
Parallel light tube, parallel light tube are the microscope groups for target plane being placed in using optical means infinite point, mainly by primary mirror and turning back
Mirror two parts form, and light source penetrates target plane again after mirror of turning back is reflected into primary mirror, and formation collimated light beam finally enters tested
Load；Wherein, vibration-isolating platform two is optics vibration-isolating platform is made by adjusting the position of each mirror of parallel light tube on vibration-isolating platform two
The source of parallel light that target simulator is sent out is obtained, the tested payload reception being arranged on another vibration-isolating platform one passes through space flight
It is micro- that device high resolution camera optical jitter micro-vibration source ground simulator simulates optical jitter to tested load into row energization
Vibrate operating mode.
2. verification system as described in claim 1, wherein by encouraging target vibration to simulate defocus and in-orbit camera light respectively
Two kinds of situations of axis micro-vibration are tested load and parallel light tube on the same vibration-isolating platform at this time, and target simulator sends out parallel
Light source is tested payload reception source of parallel light.
3. verification system as described in claim 1, wherein the primary mirror of parallel light tube and catadioptric mirror are equipped with corresponding support branch
Frame is separately fixed on vibration-isolating platform two, is demarcated to optical axis and position of focal plane using interferometer and plane mirror.
4. verification system as described in claim 1, wherein by integrating sphere light-emitting window and target center close proximity to drop
The low influence to imagewise uniform.
5. verification system as described in claim 1, wherein optical axis height is using the height at primary mirror center to vibration-isolating platform as base
Standard adjusts the height of primary mirror, catadioptric mirror and integrating sphere with this height.
6. verification system as described in claim 1, wherein tested load is camera.
7. verification system as claimed in any one of claims 1 to 6, wherein high resolution camera optical jitter micro-vibration source ground
Simulator includes mainly bearing system part and excitation system part, is used for the bearing system part of bearing test load
The six degree of freedom tooling mainly supported to it by mounting plate and bottom forms；It is main to provide the excitation system part quantitatively encouraged
Including vibrator, exciting rod, control sensor, control system, wherein vibrator one end is fixed on hoistable platform, the other end
It is connected with mounting plate by activation lever, the control sensor being pasted onto in transfer block, then adjusts hoistable platform height, mounting plate
The control sensor installed between activation lever carries out the monitoring of output mechanics parameter, using single-point control mode, computer control
System output drive signal processed is input to vibrator after being output to signal amplifier amplification after zero-bit is modulated, table top is made to generate
Mechanics parameter is fed back to calculating control system by control sensor and is compared and corrects by vibration, the response at control point, makes drive
The mechanics parameter response that dynamic signal generates on vibrator meets requirement of experiment.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657961A (en) * | 2019-10-12 | 2020-01-07 | 西安泰豪红外科技有限公司 | Method for measuring optical axis shaking amount of zoom camera |
| CN111323191A (en) * | 2020-04-16 | 2020-06-23 | 北京空间飞行器总体设计部 | Device for testing influence of micro-vibration of spacecraft on imaging quality of optical camera |
| CN112629830A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Optical load imaging performance measuring method and system based on micro-vibration interference |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05322701A (en) * | 1992-05-18 | 1993-12-07 | Canon Inc | Jitter quantity measuring device |
| JPH07168229A (en) * | 1993-12-14 | 1995-07-04 | Nikon Corp | Camera with vibration proof mechanism |
| CN102650563A (en) * | 2011-12-20 | 2012-08-29 | 北京卫星环境工程研究所 | Ground testing system for on-track micro vibration of spacecraft |
| CN102865883A (en) * | 2012-06-26 | 2013-01-09 | 北京航空航天大学 | Test system for impact analysis of imaging quality of TDICCD (Time Delayed Integration Charge Coupled Device) by multi-source interference |
| KR101400137B1 (en) * | 2012-07-16 | 2014-05-28 | 한국과학기술원 | Microvibration emulator, test device of satellite system including the same, and method of emulating microvibration |
| CN104469357A (en) * | 2014-12-30 | 2015-03-25 | 中国科学院长春光学精密机械与物理研究所 | System for testing influences of microvibration on imaging quality of long-focus camera |
| CN104735445A (en) * | 2015-03-17 | 2015-06-24 | 航天东方红卫星有限公司 | Space camera flutter analysis method based on target image |
| CN105530514A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Testing device for affect of satellite platform micro-vibration on camera imaging |
| CN206020919U (en) * | 2016-09-18 | 2017-03-15 | 上海研端信息科技有限公司 | A kind of anti-shake test macro |
| CN107167302A (en) * | 2017-07-12 | 2017-09-15 | 北京卫星环境工程研究所 | Vacuum low-temperature environment imaging shaking detection device based on off-axis collimated optical system |
| CN107543672A (en) * | 2016-12-27 | 2018-01-05 | 北京卫星环境工程研究所 | Multiple degrees of freedom micro-vibration environmental simulation method |
| CN107643156A (en) * | 2017-10-30 | 2018-01-30 | 长春工业大学 | Three axle rotational shaking tables |
| CN107741702A (en) * | 2017-10-30 | 2018-02-27 | 长春工业大学 | Complicated opto-mechanical part IMAQ ground simulation platform stance disturbing generating device |
| CN107782536A (en) * | 2017-09-14 | 2018-03-09 | 北京空间飞行器总体设计部 | A kind of multi-level micro-vibration system test method and system |
-
2018
- 2018-06-15 CN CN201810617609.1A patent/CN108801574B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05322701A (en) * | 1992-05-18 | 1993-12-07 | Canon Inc | Jitter quantity measuring device |
| JPH07168229A (en) * | 1993-12-14 | 1995-07-04 | Nikon Corp | Camera with vibration proof mechanism |
| CN102650563A (en) * | 2011-12-20 | 2012-08-29 | 北京卫星环境工程研究所 | Ground testing system for on-track micro vibration of spacecraft |
| CN102865883A (en) * | 2012-06-26 | 2013-01-09 | 北京航空航天大学 | Test system for impact analysis of imaging quality of TDICCD (Time Delayed Integration Charge Coupled Device) by multi-source interference |
| KR101400137B1 (en) * | 2012-07-16 | 2014-05-28 | 한국과학기술원 | Microvibration emulator, test device of satellite system including the same, and method of emulating microvibration |
| CN104469357A (en) * | 2014-12-30 | 2015-03-25 | 中国科学院长春光学精密机械与物理研究所 | System for testing influences of microvibration on imaging quality of long-focus camera |
| CN104735445A (en) * | 2015-03-17 | 2015-06-24 | 航天东方红卫星有限公司 | Space camera flutter analysis method based on target image |
| CN105530514A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Testing device for affect of satellite platform micro-vibration on camera imaging |
| CN206020919U (en) * | 2016-09-18 | 2017-03-15 | 上海研端信息科技有限公司 | A kind of anti-shake test macro |
| CN107543672A (en) * | 2016-12-27 | 2018-01-05 | 北京卫星环境工程研究所 | Multiple degrees of freedom micro-vibration environmental simulation method |
| CN107167302A (en) * | 2017-07-12 | 2017-09-15 | 北京卫星环境工程研究所 | Vacuum low-temperature environment imaging shaking detection device based on off-axis collimated optical system |
| CN107782536A (en) * | 2017-09-14 | 2018-03-09 | 北京空间飞行器总体设计部 | A kind of multi-level micro-vibration system test method and system |
| CN107643156A (en) * | 2017-10-30 | 2018-01-30 | 长春工业大学 | Three axle rotational shaking tables |
| CN107741702A (en) * | 2017-10-30 | 2018-02-27 | 长春工业大学 | Complicated opto-mechanical part IMAQ ground simulation platform stance disturbing generating device |
Non-Patent Citations (3)
| Title |
|---|
| 徐鹏 等: "卫星振动对成像质量影响的仿真分析", 《宇航学报》 * |
| 李栋 等: "基于光轴位移测量的微振动试验方法研究", 《中国力学大会-2017暨庆祝中国力学学会成立60周年大会论文集》 * |
| 王想响: "高频响大载荷六自由度激振台设计及其动态特性分析", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657961A (en) * | 2019-10-12 | 2020-01-07 | 西安泰豪红外科技有限公司 | Method for measuring optical axis shaking amount of zoom camera |
| CN111323191A (en) * | 2020-04-16 | 2020-06-23 | 北京空间飞行器总体设计部 | Device for testing influence of micro-vibration of spacecraft on imaging quality of optical camera |
| CN112629830A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Optical load imaging performance measuring method and system based on micro-vibration interference |
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