CN109188648A - A kind of floating support device for the unloading of space optics load ground gravity - Google Patents
A kind of floating support device for the unloading of space optics load ground gravity Download PDFInfo
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- CN109188648A CN109188648A CN201811057137.5A CN201811057137A CN109188648A CN 109188648 A CN109188648 A CN 109188648A CN 201811057137 A CN201811057137 A CN 201811057137A CN 109188648 A CN109188648 A CN 109188648A
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
- G02B7/183—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy, or solar concentrators
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Abstract
The present invention relates to precision machineries and space optics technical field, the Floatable supporting mechanism for specifically disclosing a kind of space optics load ground gravity unloading is fixed at the lower section of optics load including unloading pedestal, the several groups gravity unloading device being arranged on unloading pedestal, gravity unloading device；Floating support device further includes the several groups fixed support device that optics load back is arranged in, pass through gravity unloading device, the gravity unloading along gravitational vectors direction may be implemented, to offset the maximum distortion that large-scale mechanical-optical setup is introduced by gravity, substantially alleviate the inconsistent influence to space optics load ground adjustment precision and in-orbit image quality of day-ground mechanical environment, provides basic image quality for the high sense optical component prepackage reconciliation active optics correction in ground.It in addition, unloading by ground gravity, can also substantially reduce the unnecessary design redundancy of large-aperture optical load mechanical-optical setup, reduce the service efficiency of launch cost and space vehicles tool.
Description
Technical field
The present invention relates to precision machinery and space optics technical field, in particular to a kind of large-caliber space optical load
The Floatable supporting mechanism of face gravity unloading.
Background technique
Space optics telescope, which refers to, to be equipped on satellite platform, for being imaged and surveying to chronometer phenomenons all kinds of in universe
Amount, or push away to ground scenery target a kind of space optics load for sweeping or staring observation.Such as widely known Hubble hopes
Such space optics telescope is carried on remote mirror, WordView earth observation satellite, for all kinds of chronometer phenomenons or ground
Scenery optical target studies picture.All kinds of space optics load finally work in space microgravity environment, but the adjustment of optics load
It with test is carried out on ground, gravity will test process with entire adjustment.This results in the adjustment of space optics load, surveys
The mechanical environment of examination process and practical in-orbit state mechanical environment are inconsistent.And above-mentioned " day-ground " mechanical environment is inconsistent will be right
Space optics load major optical performance is realized and maintaining a long-term stability property brings greater risk.Main reason is that spatial light
The main performance for learning telescope is its quality of optical imaging.And on the one hand to depend on optical design residual for the guarantee of image quality
Difference and the precision of optics manufacture and processing.On the other hand then by ground adjustment precision and the structural stability of optical-mechanical system
It determines.Adjustment process is to instruct adjustment personnel by optics member each in telescope using certain criterion for image evaluation as criterion and pointer
The spatial position and posture that part adjustment to optical design gives, and guarantee that adjustment residual error is less than distributed threshold value.And ray machine knot
Structure and heat control system then need to guarantee that above-mentioned adjustment result has long-time stability, make in the entire working life of space optics load
All have design performance.But during the adjustment of ground, gravity acts on each optical element in ray machine load, support always
Truss, instrument module etc..Lighting apparatus component position and posture volume is caused to adjust positioning under micro flexible deformation caused by gravity
It realizes.And after in-orbit gravity release, flexible deformation will be caused to restore, erection stress release, and then lead to each ray machine group, component
Relative position and posture change, so that the image quality of space optics load generates large change.
For in, small-bore space optics load, above-mentioned " day-ground " mechanical environment is inconsistent to cause space optics load
The risk of major optical penalty is not still significant.The small-bore optics load in, necessary mechanical-optical setup weight and body
Product is of less demanding.Under the premise of transmitting delivery gross mass is certain, optical-mechanical system structure can be improved by increasing design redundancy
Rigidity makes lighting apparatus component have stronger resistance gravity deformation ability, it is ensured that under gravity and under the conditions of in-orbit zero-g, light
The optical element that machine structure " rebound " introduces is smaller with respect to the comfortable variable quantity in position, is unlikely to change system imaging quality.
In order to improve observation resolution ratio and investigation depth, the more details for obtaining object space shape characteristic, space optics
The bore of telescope is increasing, and must be provided simultaneously with longer focal length.For ensure image quality under in-orbit environment and
Optics load main performance in orbital stability, causes necessary construction weight volume constantly soaring for a long time.But heavy caliber space is looked in the distance
Mirror and its satellite platform, which are both needed to be equipped on the delivery vehicles such as rocket or space shuttle just emit, enters the orbit, and above-mentioned delivery vehicle
Carrying capacity is limited.If still based on the rigidity of structure is improved by increasing design redundancy at present, to overcome " day-ground " mechanical environment
The conventional thought of inconsistency, necessarily leading to the gross mass of optics load is more than spacecraft limit carrying capacity, and is caused not
Necessary launch cost.And corresponding resolving ideas is exactly to be existed by simulating in ground adjustment, test process with optics load
The similar mechanical environment of track-like state, to achieve the effect that alleviate above-mentioned " day-ground " mechanical environment inconsistency.But existing test
Technology and method for supporting are difficult to meet the above-mentioned mechanical environment simulation demand of large-caliber space optical load, and can not accurately sentence
Determine after gravity unloading lighting apparatus component whether adjustment in place, main cause is as follows.
(1) existing gravity unloading method mainly includes full unloading and two kinds of main thoughts of partial relief.Full unloading thinking is big
" falling tower method ", " aircraft parabolic flight method " and other implementations are mostly used, it is weightless to simulate each dimension omnidirectional of carrying object.But big mouth
The adjustment of diameter space optics load, test period are longer, during which also need to intert all kinds of verification tests, and it also requires a large amount of bodies
Product, the biggish optic test of weight and assistant resetting equipment.Therefore existing omnidirectional's weightless flight method is difficult to meet big mouth
Gravity unloading demand during the adjustment of diameter space optics load, test.
(2) another weightlessness simulation thinking is to carry out the unloading of omnidirectional, part gravity, and main analog form is
It is soaked in heavy water basin by the way that object will be unloaded, gravity field action in part is offset by liquid buoyancy, unloaded with reaching omnidirectional part
The purpose of load.But the adjustment of space optics load, test process require optical signal to transmit in adjustment and the real optical path of survey always.And liquid
Body refractive index differs greatly with vacuum and air, furthermore to avoid suspension from corroding photoelectronic imaging device and other circuit systems
System, needs to carry out the sealing waterproofing design of large amount of complex.Therefore from feasibility and cost etc., existing omnidirectional part
Gravity unloading technology is difficult to meet the simulation demand of the microgravity in large-caliber space optical load adjustment test process.
(3) adjustment of space optics load, in test process, the adjustment stress and flexible deformation that gravity introduces mostly there is only
In along gravitational vectors direction, and after gravity release of entering the orbit, the stress variation of the direction significantly affects each optical module relative pose.
Based on These characteristics, there is also the technical thoughts of non-omnidirectional's gravity unloading.Its main thought is to actuate branch by air bearing or multiple spot
Support mode offsets the gravity effect along gravitational vectors direction, reaches compensation along gravitational vectors direction flexible deformation and assembly
The effect of stress.But the prior art is directed to big rigidity shell or symmetrical structure, and it is larger to unload residual error.Large-caliber space optical
Load, in particular by off-axis light path the generally existing self structure rigidity of space optics load it is lower, Mass Distribution is asymmetric,
Geometric center and mass center deviate the features such as larger, adjustment precision is extremely sensitive to unloading residual error.In addition large-caliber space optical carries
Adjustment precision comfortable with respect to position between each ray machine group parts and stability needs reach " wavelength " and rad magnitude in lotus.It is existing non-complete
Meet demand is difficult in terms of gravity unloading technology is from unloading precision, application conditions.
(4) adjustment test process in large-caliber space optical load ground is required to experience vacuum, cold darkness environment verification experimental verification.
Therefore the above-mentioned special test environment of space loading, also proposes particular/special requirement to gravity discharge mechanism, so that generalling use at present
Air bearing Deng Fei omnidirectional, Low rigidity gravity unloading technology be unsatisfactory for use environment requirement.
Summary of the invention
The present invention is directed to overcome heavy caliber, long-focus space optics telescope to be drawn in ground adjustment, test process by gravity
The internal distortions risen can be sprung back after gravity release of entering the orbit, and be changed so as to cause optical element pose low with image quality
Defect.
To achieve the above object, the present invention provides a kind of floating support dress for the unloading of space optics load ground gravity
It sets, is fixed at optics load including pedestal, several groups gravity unloading device, the gravity unloading device of setting on the base
Lower section；Floating support device further includes the several groups fixed support device that optics load back is arranged in.
Further, gravity unloading device includes gravity unloading package base, vertical freedom degree release component, power transmission machine
Structure, tension sensor, five degree of freedom discharge component；Gravity unloading package base is fixedly installed on the base, and vertical freedom degree is released
It puts component one end to connect with gravity unloading package base, the other end is connect by connecting plate with tension sensor；Five degree of freedom is released
It puts component one end to connect with tension sensor, the other end is connect with optics load, and tension sensor is for measuring gravity unloading dress
Set internal pressure and pulling force.
Preferably, five degree of freedom release component includes the ball bearing assembly connecting with optics load, thrust shaft module, ball
Bearing assembly one end is connected with unloading attachment base, and the other end is connected with thrust shaft module.
Preferably, ball bearing assembly includes ball bearing, ball bearing housing, ball bearing pressing plate, and ball bearing is mounted on ball bearing housing
Interior, ball bearing pressing plate provides precompression.
Preferably, thrust shaft module includes thrust ring, steel ball, retainer, thrust shaft block, thrust ring and ball bearing housing
It is fixedly connected, annular gap is set between retainer and thrust shaft block.
Preferably, vertical freedom degree release component includes that lift connection plate and running block component, lift connection plate are solid
The bottom end of force transmission mechanism is set calmly, and the two sides of lift connection plate are fixedly connected with running block component respectively.
It further, further include quiet pulley blocks component, quiet pulley blocks component is fixed at weight by quiet pulley bearings seat
On the column of power unloading assembly two sides of base, running block component cooperates with quiet pulley blocks component realizes that steel cable multiple groups twine
Around.
It further, further include trim case bulb connection component, trim case, the wirerope both ends in running block component are logical
Trim case bulb connection component is crossed to be fixedly connected with trim case, the trim releasable wirerope of case bulb connection component and trim case it
Between three-dimensional rotation freedom degree.
Further, gravity unloading package base stiffening plate is fixedly installed in gravity unloading package base.
Preferably, gravity unloading device is four groups, and fixed support device is three groups.
The beneficial effects of the present invention are:
1, the present invention devises the gravity unloading device using particular configuration, realizes that trim power passes based on purely mechanic mechanism
It leads, and realizes that space optics load position and posture are kept with fixed supporting point cooperation.
2, the present invention devises unloading force 6 DOF relieving mechanism, and substantially reduces apparatus body after integrating with force transmission mechanism
Product.And unloading residual error can be effectively reduced in the layout order of sextuple freedom degree relieving mechanism in the present invention, improves applying for unloading force
Add precision.
3, the present invention using particular configuration dynamic-quiet pulley blocks component, on the one hand realize trim object gravity and unloading force it
Between conversion, and only need 1/6 trim object gravity that the purpose of 1 times of gravity unloading can be realized.Particular configuration is dynamic-quiet simultaneously
Pulley blocks component, which can also be effectively eliminated, adds unbalanced moments due to caused by discharge mechanism processing, rigging error, makes to be loaded
The relatively local unloading point of unloading force power and torque balance simultaneously.Third, the pulley assemblies configuration also effectively realize bottom
The purpose of portion's gravity unloading further functions as the purpose for reducing device volume and weight.
4, gravity unloading technology involved by the present invention, can solve the ground adjustment of large-caliber space optical load, test process
In microgravity problem of modelling.By designing the gravity unloading device of particular configuration and layout, may be implemented along gravitational vectors side
To gravity unloading substantially alleviate day-ground mechanical environment not to offset the maximum distortion that large-scale mechanical-optical setup is introduced by gravity
It is the high pre- adjustment of sense optical component in ground unanimously to the influence of space optics load ground adjustment precision and in-orbit image quality
It is corrected with active optics and basic image quality is provided.In addition, unloading by ground gravity, it can also substantially reduce large-aperture optical load light
The unnecessary design redundancy of machine structure reduces the service efficiency of launch cost and space vehicles tool.
5, furthermore the present invention also has application potential in terms of flexible, the adaptive support of large-scale thin walled shell structural member.Example
Such as large thin-wall carbon fiber cylinder or special-shaped shell, high-precision is required to during winding, processing, assembly etc. and is supported.
The metal die that existing support scheme mostly uses greatly shape similar, this can reduce production line flexibility ratio, improve manufacturing cost and
In the period, there is also bottlenecks in terms of size and machining accuracy.Using discharge mechanism involved in the present invention, non-static determinacy may be constructed
Floating support structure, it is ensured that large thin-wall shell can determine spatial position and posture during process and assemble, on the other hand
It realizes thin wall gravity unloading, eliminates mismachining tolerance and rigging error caused by flexible deformation.The present invention is low just in special material
Spend component machining, the assembly great application prospect in field.
Detailed description of the invention
Fig. 1 schematically shows working principle diagram according to the present invention；
Fig. 2 is a kind of front view of the floating support device for the unloading of space optics load ground gravity of the present invention；
Fig. 3 is a kind of side view of the floating support device for the unloading of space optics load ground gravity of the present invention；
Fig. 4 is the structural schematic diagram of the single gravity unloading device of the present invention；
Fig. 5 is the structural schematic diagram that the single gravity unloading device of the present invention does not include gravity unloading package base；
Fig. 6 is the structural schematic diagram of the static-dynamic pulley blocks components mechanism of the present invention.
1, the first finite element；2, the second finite element；3, the first gravity unloading device；
4, the second gravity unloading device；5, fixed supporting point；6, gravity unloading device；
7, optics load；8, pedestal；9, fixed support device；10, attachment base is unloaded；
11, ball bearing；12, ball bearing housing；13, ball bearing pressing plate；14, thrust pressing plate；
15, thrust ring；16, steel ball；17, retainer；18, thrust shaft block；
19, sensor connecting base；20, tension sensor；21, strut and its connecting plate；
22, lift connection plate；23, trim case bulb connection component；24, trim case；
25, gravity unloading package base stiffening plate；26, gravity unloading package base；
27, running block component；28, quiet pulley blocks component.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with attached drawing and specific implementation
Example, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only to explain this hair
It is bright, but not to limit the present invention.
Referring initially to Fig. 1, illustrate the working principle of the invention, discharge mechanism needs while providing given unloading force
Discharge the freedom degree of unloading force vector six direction simultaneously, and ensure the uninstall direction of added unloading force always with gravitational vectors
Direction is parallel, and added unloading force does not change with loading position and changed, and does not change with space loading attitudes vibration.This
Outside, gravity unloading device should be as compact as possible, to meet the bulk used in vacuum tank limitation.
For above-mentioned purpose, gravity unloading device according to the present invention is proposed, working principle is as shown in Figure 1.It can incite somebody to action
It is first " 1 and 2 " that any part of space optics load mechanical-optical setup is divided into adjacent finite.Under the conditions of non-loading and unloading power, by
Internal force and " fixed supporting point 5 " effect, finite element is in stationary state, but can have flexible deformation " Δ "." the first gravity unloads
Carry set 3 " and " the second gravity unloading device 4 " and mechanical-optical setup part finite element 1,2 it is connected after, there are the non-static determinacy of transient state
Process, since the internal stress along gravity reversal is greater than the resultant force along gravity direction, and the dimension freedom degree of unloading force 6 applied is complete
Release allows between finite element since the internal stress that flexible deformation " Δ " introduces promotes " the first finite element 1 " and " second has
Opposite free movement between limit member 2 ", and mutual crosstalk and interference is not present, until the resultant force along gravity direction balances again.Herein
Under new equilibrium state, unloading force is equal to local finite member gravity, when ignoring simulation analysis of computer error, flexible deformation
" Δ " is close to zero, and simulates microgravity state in gravitational vectors direction.
To realize above-mentioned principle, the device composition of the bright offer of this law is as shown in Figure 2,3.In integrated, test mode sky
Between optics load be in optical axis horizontality, positioned at its back three " fixed support devices 9 " for determine to photometry carry
Lotus spatial position and posture.One end of multiple groups " gravity unloading device 6 " is fixedly connected on the bottom plate of " pedestal 8 ", the other end with
Optics load 7, i.e. " space optics telescope to be measured " are fixedly connected.Above-mentioned gravity unloading device 6 realizes that space optics to be measured is hoped
Gravity unloading of the remote mirror along gravitational vectors direction.The fixed support device 9 on pedestal 8 is rigidly connected in therewith simultaneously then by rigid
Property support determine space optics telescope pose to be measured, and realize unstressed or microstress inside rigid support point, guarantee light
Learn the validity in dress school.Pedestal 8 is the rigidity basis of the gravity unloading device, has and keeps each unloading point relative position and appearance
State, and the function of rigidity connected discharge mechanism and fixed support device.
Fig. 4, Fig. 5 respectively illustrate the composition of single gravity unloading device, and multiple groups gravity unloading device realizes multiple spot jointly
Floating gravity unloading.Unloading attachment base 10 connect and sells by screw with the connecting flange given on space optics telescope to be measured
Axis positioning, is based on " plane and two pits " positioning principle, realizes single gravity unloading device 6 and space optics telescope ray machine knot to be measured
Structure is connected completely.Ball bearing 11 is located in ball bearing housing 12, precompression is provided by ball bearing pressing plate 13, thus by static friction
The sensitivity and amount of deflection of power control ball bearing assembly.Component " ball bearing 11, ball bearing housing 12 and ball bearing pressing plate 13 " constitutes ball
Spherical bearing component discharges the relative freedom of three direction of rotation between unloading attachment base 10 and thrust ring 15 connected in series.
Thrust ring 15 and ball bearing housing 12 are connected, and constitute thrust shafting with thrust pressing plate 14, steel ball 16 and thrust shaft block 18.It protects
17 one side of frame is held for locking ball, relative motion between steel ball during preventing freedom degree from discharging, on the other hand, by holding
The free movement of any translational direction in horizontal plane is realized, to discharge in annular gap between frame 17 and thrust shaft block 18
Bidimensional translation freedoms.Said modules " 10 " to " 18 " constitute five degree of freedom release component and pass through sensor connecting base 19 and tension
Sensor 20 is connected.Tension sensor 20 is vacuum compatible device, can pressure and pulling force inside real-time measurement discharge mechanism, and
By cable with numeric form Real-time Feedback, so that the interior mechanics state for rational judgment gravity unloading device provides foundation.
Tension sensor 20 is located between the final stage of unloading force Path of Force Transfer and five degree of freedom release component simultaneously, can integrally measure and unload
The coupling effect of unloading force and frictional force in power Path of Force Transfer is carried, while avoiding being discharged caused by component movement as freedom degree
Unloading force measurement error.The connected strut of 20 other end of tension sensor and its connecting plate 21, pass through the strut for choosing different length
Adapt to the different height of space optics telescope mechanical-optical setup bottom to be measured.Strut and its connecting plate 21 are unloading force Path of Force Transfer
Final stage and output end.Lift connection plate 22 is located at the other end of strut and its connecting plate 21, is connected therewith.Lift connection plate 22
Using plate-shell structure, inside is equipped with reinforcing rib to improve its rigidity, the two sides of lift connection plate 22 respectively with running block group
Part 27 is connected, and such as Fig. 6, realizes component " 10 " to " 21 " freely rising along gravitational vectors direction thereon by running block component 27
Drop, to achieve the purpose that discharge another one vertical direction freedom degree.Furthermore lift connection plate 22 also passes through running block component
27 realize the conduction of unloading force.The winding of steel cable multiple groups is realized in running block component 27 and the cooperation of quiet pulley blocks component 28,
And it eliminates and is missed due to each movable pulley in unloading force transmission path with respect to the relative position between 21 axis of strut and its connecting plate
Poor and introducing unbalance loading torque.In addition, multiple groups movable pulley, which also acts as, reduces trim object weight, reduce gravity unloading device total volume
With the function of weight.Quiet pulley blocks component 28 is fixed on the column of 26 two sides of gravity unloading package base by bearing block.It is dynamic
Wirerope both ends in pulley blocks component 27 are connected by trim case bulb connection component 23 and trim case 24.Trim case bulb connects
Three-dimensional rotation freedom degree between the releasable wirerope of connected components 23 and trim case 24, so that trim case 24 is in free state,
Unbalanced moments caused by eliminating frictional force unevenly.It unloads pedestal stiffening plate 25 and gravity unloading package base 26 is connected, rise
To 26 local strength of gravity unloading package base is reinforced, the purpose of entire unloading assembly rigidity is improved, is reduced by gravity unloading group
Residual error is unloaded caused by 26 local deformation of part pedestal.Gravity unloading package base 26 uses multiple groups screw by the flange face of bottom
It is fixedly connected with the flange face in 8 bottom support plate of pedestal.8 bottom support plate of pedestal realizes the purpose for positioning each gravity unloading component.
The course of work of the present invention:
1. the working principle of the invention:
It, can be according to the light of large-aperture optical load after simulation analysis and load specific mathematical model and simulation algorithm
Mechanism type and the optical module pose of optical design distribution change threshold residual value, and the coordinate and correspondence of optimization gravitational equilibrium point unload
The unloading force size of loading point.Above-mentioned analysis is the result is that the input that gravity unloading device designs.
Firstly, large-aperture optical load realizes space orientation by several fixed supporting points under agravic unloaded state.
But there is the micro flexible deformation as caused by gravity inside optical-mechanical system, generally in micron to some tens of pm magnitude, and thus
Caused internal stress.Above-mentioned deformation will be sprung back after gravity release of entering the orbit, and then change the perfect optical path in ground dress school
In each optical element pose, destroy system imaging quality.For this purpose, introducing gravity unloading device in adjustment test process.
Firstly, according to simulation analysis of computer as a result, applying trim power.By the output end of each independent gravity unloading device with
Fixing tool connection, is gradually added trim mass block in trim case, and tension sensor measurement is introduced by trim mass block gravity
Equilibrant force, until tension sensor shown by wirerope internal tension it is consistent with simulation analysis of computer result.At this time using weight
Static-dynamic pulley block mechanism in power discharge mechanism.The gravity unloading device output end and large-aperture optical load that adjustment is finished
On unloading point be fixedly connected, and unlock static-dynamic pulley block mechanism.At this point, trim mass block position discharges, it is instantaneous non-there are one
Static determinacy process, as shown in Figure 1.Since under above-mentioned non-offloaded state, there are internal stress caused by gravity inside mechanical-optical setup, and
And there are associated local elastic deformations.And the equilibrant force loaded is less than the support reaction reversed with gravitational vectors direction and interior
The resultant force of stress, therefore the micro- finite element in part of mechanical-optical setup will be along gravitational vectors opposite direction fine motion.Gravity unloading device at this time
The freedom degree of translation and Three dimensional rotation direction in the complete release plane of the soft section of five degree of freedom, static-dynamic pulley block mechanism discharge edge
The freedom degree in gravitational vectors direction will not cause to interfere to above-mentioned counter motion, so that micron order flexible deformation caused by gravity
The direction of rebound and size are determined by mechanical-optical setup internal stress completely, so that simulated gravity discharges process.
After micro-deformation, which recoils to flexible deformation, to be eliminated, by gravity introducing near unloading point inside mechanical-optical setup
Stress is close to zero.In this case, the equilibrant force of gravity unloading device load is equal with the gravity of unloading point attachment, above-mentioned wink
State motion process terminates.Similarly, gravity unloading point can be connected with the given position on mechanical-optical setup component one by one, and released one by one
Put unloading point near zone flexible deformation as caused by gravity.After being completely used for the equilibrant force load of unloading, between unloading point
Between regional area in short span, mechanical-optical setup local stiffness is promoted, and can be resisted and be eliminated the elasticity as caused by gravity
Deformation.Unloading point nearby then offsets local gravity by trim quality, the shape characteristic of mechanical-optical setup after simulated gravity release.Upper
State each optical module of adjustment under state, and optical module and support construction be connected after pose dress school is improved, can obtain and
Consistent optical path states under in-orbit microgravity condition, to eliminate the inconsistent caused image quality variation of " day-ground " mechanical environment.
2. the device of the invention principle:
The output end being connected with space optics load unloading point is spherical bearing, is discharged by ball-joint around three-dimensional rotating
Freedom degree.The Thrust shafting of series connection with it then can completely in release plane any direction translational degree of freedom.And it is located at
Then discharged completely in gravity unloading package base and with the above-mentioned soft concatenated static-dynamic pulley assembly of section along gravitational vectors direction from
By spending.Above structure discharges the six-dimensional space freedom degree of unloading force completely, and uses arranged in series it is possible to prevente effectively from mutually dry
It relates to, to realize freely composing for spatial motion vectors direction.It is dry as caused by Planar Mechanisms that above structure can be such that unloading point eliminates
It relates to, determines that the loading direction for unloading equilibrant force only by the release direction of internal stress, without by device connection precision, position
The influence of precision.
Concatenated with the soft section of five degree of freedom is high-precision tension sensor, is located at the end of discharge mechanism Path of Force Transfer,
The equilibrant force loaded on unloading point can be directly measured, for judging the deviation of itself and computer artificial result, above-mentioned arrangement side
Formula can act on sensor to avoid the component as caused by loading force direction change, and introduce load balance power error.It is located at
Path of Force Transfer final stage is static-dynamic pulley assembly, by the static-dynamic pulley assembly of one group of particular configuration, by trim mass block
Gravity is converted into unloading force, and the volume and gross weight for putting down and substantially reducing trim power, reducing gravity unloading device meet and hold in vacuum
Demand under the application circumstances such as device.
Multiple gravity unloading devices are fixed in bottom base, and stable branch support group is provided for multiple groups gravity unloading device
Plinth, and ensure that the position between each unloading point and its relative variation as caused by environment are less than above-mentioned freedom degree relieving mechanism
Limit travel.It unloads and the bracket that is connected is set above pedestal, also set up on the bracket that is connected there are three fixed supporting point, be used for heavy caliber
The space orientation of optics load.Above-mentioned fixed supporting point and gravity unloading point collectively form floating support system, that is, determine space
The spatial position of optics load and posture meet test, adjustment in the process to the accurate adjustment of optics load optical axis and positioning need
It asks.The unloading point of positioning is not constrained using multiple only load balance power and simultaneously, after being adjustment, the release of test process simulated gravity
The topographical property of mechanical-optical setup provides mechanical environment.Furthermore above-mentioned apparatus uses purely mechanic design, avoids gas or liquid is quiet
The pollution problem as caused by gas leakage or leakage in pressure system meets vacuum, the cold special tests environmental demand such as black.And pass through spy
Different configuration reduces device volume, meets and the limitation of the application circumstances to device volume, weight such as uses in positive empty container.
The above described specific embodiments of the present invention are not intended to limit the scope of the present invention..Any basis
Any other various changes and modifications made by technical concept of the invention should be included in the guarantor of the claims in the present invention
It protects in range.
Claims (10)
1. it is a kind of for space optics load ground gravity unloading floating support device, which is characterized in that including pedestal (8),
Several groups gravity unloading device (6), the gravity unloading device (6) being arranged on pedestal (8) are fixed at optics load
The lower section of lotus (7)；The floating support device further includes several groups fixed support device of the setting at optics load (7) back
(9)。
2. a kind of floating support device for the unloading of space optics load ground gravity as described in claim 1, feature
It is, the gravity unloading device (6) includes gravity unloading package base (26), vertical freedom degree release component, power transmission machine
Structure, tension sensor (20), five degree of freedom discharge component；The gravity unloading package base (26) is fixed at pedestal
(8) on, described vertical freedom degree release component one end is connect with gravity unloading package base (26), and the other end passes through power transmission machine
Structure is connect with tension sensor (20)；Described five degree of freedom release component one end is connect with tension sensor (20), the other end
It is connect with optics load (7), the tension sensor (20) is used to measure gravity unloading device (6) internal pressure and drawing
Power.
3. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 2, feature
It is, the five degree of freedom release component includes the ball bearing assembly connecting with optics load (7), thrust shaft module, institute
The ball bearing assembly one end stated is connected with unloading attachment base (10), and the other end is connected with thrust shaft module.
4. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 3, feature
It is, the ball bearing assembly includes ball bearing (11), ball bearing housing (12), ball bearing pressing plate (13), the ball bearing
(11) it is mounted in ball bearing housing (12), the ball bearing pressing plate (13) provides precompression.
5. a kind of floating support arrangement for the unloading of space optics load ground gravity as claimed in claim 3, feature exist
In, the thrust shaft module include thrust ring (15), steel ball (16), retainer (17), thrust shaft block (18), it is described
Thrust ring (15) is fixedly connected with ball bearing housing (12), and annular is arranged between the retainer (17) and thrust shaft block (18)
Gap.
6. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 2, feature
It is, the vertical freedom degree release component includes lift connection plate (22) and running block component (27), the liter
Drop connecting plate (22) is fixed at the bottom end of force transmission mechanism, the two sides of lift connection plate (22) respectively with running block component
(27) it is fixedly connected.
7. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 6, feature
It is, further includes quiet pulley blocks component, the quiet pulley blocks component is fixed at gravity unloading by quiet pulley bearings seat
On the column of package base (26) two sides, the running block component (27) and the cooperation of quiet pulley blocks component (28) realize one
The winding of wirerope multiple groups.
8. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 7, feature
It is, further includes trim case bulb connection component (23), trim case (24), the wirerope in the running block component (27)
Both ends are connect by trim case bulb connection component (23) with trim case (24) flexural pivot, and trim case bulb connection component (23) can be released
Put the three-dimensional rotation freedom degree between wirerope and trim case (24).
9. a kind of floating support device for the unloading of space optics load ground gravity as claimed in claim 8, feature
It is, gravity unloading package base stiffening plate (25) is fixedly installed in the gravity unloading package base (26).
10. a kind of floating support device for the unloading of space optics load ground gravity as described in claim 1, feature
It is, the gravity unloading device (6) is four groups, and the fixed support device (9) is three groups.
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| CN110634372A (en) * | 2019-09-29 | 2019-12-31 | 中国科学院长春光学精密机械与物理研究所 | Optical system installation and adjustment strategy verification system |
| CN110823433A (en) * | 2019-10-18 | 2020-02-21 | 中国直升机设计研究所 | Five-freedom-degree device for rotor load measurement |
| CN112255868A (en) * | 2020-10-30 | 2021-01-22 | 长光卫星技术有限公司 | Gravity unloading device for large off-axis three-mirror space camera |
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| CN117704245B (en) * | 2024-02-06 | 2024-04-09 | 长春国宇光学科技有限公司 | Gravity unloading device for large-caliber space camera |
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