CN107686883A - A kind of method for space camera structure stabilization - Google Patents

A kind of method for space camera structure stabilization Download PDF

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Publication number
CN107686883A
CN107686883A CN201710633672.XA CN201710633672A CN107686883A CN 107686883 A CN107686883 A CN 107686883A CN 201710633672 A CN201710633672 A CN 201710633672A CN 107686883 A CN107686883 A CN 107686883A
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gauge block
benchmark gauge
mrow
summit
benchmark
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CN107686883B (en
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罗世魁
曹东晶
李明
兰丽艳
任海培
高超
陈芳
唐璐
罗廷云
史姣红
孙海洋
张宁
宗肖颖
杜建祥
张建国
王聪
潘宁贤
岳聪
张志飞
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Beijing Institute of Space Research Mechanical and Electricity
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Beijing Institute of Space Research Mechanical and Electricity
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Studio Devices (AREA)

Abstract

The present invention relates to a kind of method for space camera structure stabilization, camera structure component is connected by this method with stabilizing test tool, reference for installation gauge block, carries out three-dimensional coordinates measurement, record benchmark gauge block position；Then small magnitude stress-removal experiment is carried out, component sensitive part change in location is judged by three-dimensional coordinates measurement benchmark gauge block change in location after experiment.If variable quantity exceeds required value, small magnitude stress-removal experiment is carried out again, if variable quantity is less than required value, continues stability test.Location variation is judged after experiment, if variable quantity exceeds required value, repeatedly for aforesaid operations until variable quantity is less than required value, structure reaches stable；If variable quantity is less than required value, continue thermal cycling test.Location variation is judged after experiment, if variable quantity exceeds required value, carries out thermal cycling test again, until variable quantity is less than required value, structure reaches stable；If variable quantity is less than required value, off-test, modular construction reaches stable.

Description

A kind of method for space camera structure stabilization
Technical field
The present invention relates to a kind of method for space camera structure stabilization, particularly one kind to be used for space remote sensor pair Size or the higher modular construction of position accuracy demand reach stable method, belong to space camera structure integration techno logy field.
Background technology
For space camera structure during adjustment is processed, inside configuration may produce following stress：Metal material is being cast Make, weld and cutting process in, inside parts can produce residual stress；In each part process formed dimensional tolerance, Shaped position tolerance can produce erection stress；Flexible structure deformation can produce residual stress in component internal；Carbon fiber composite For material after being glued and assembling, inside produces residual stress etc..The stress of component internal can cause the dimensional stability of camera structure Decline with mechanical performance.
Oscillating aging, heat aging and natrual ageing can reduce the residual stress of structure, but the time required to natrual ageing It is longer, efficiency is low, therefore majority using oscillating aging and heat aging reduces machining stress in part processing.By Zhao Changxi In the 3rd phase in 2008《Aerospace manufacturing technology》On " application study of vibratory stress reliefing technology " described in the text for delivering：Vibration It is exactly that periodic active force is applied to hardware.In vibration processes, be applied to the active force of hardware each several part with Internal residual stress is superimposed, and when superposition amplitude is more than the yield limit of hardware, the sliding of these point lattices, is produced small Plastic deformation, reach the purpose of release residual stress.Heat aging be by below workpiece heat to phase transition temperature come accelerate should Power discharges, and its cycle shortens dramatically compared with natrual ageing, is widely used.
In general oscillating aging and heat aging are generally used in part processing, can eliminate larger machining stress, but right In the camera structure component that assembling is completed, the especially component containing sensible parts such as optical elements, in general oscillating aging and heat Aging process can not be implemented.And for space camera, to ensure image quality, it is necessary to stability by some optical modules Control can not be realized in a μm level, general method for removing stress.Therefore component characteristic need to be directed to, to stress-removal vibration condition and thermal vacuum Condition is strictly controlled.
The content of the invention
The technology of the present invention solves problem：Overcome the deficiencies in the prior art, there is provided one kind is used for space camera structure Stabilized method, this method promote precision components structure to be rapidly reached stabilization by mechanics, thermal cycling test.
The present invention technical solution be：
A kind of method for space camera structure stabilization, step are as follows：
(1) construction package to be stabilized in space camera is fixedly installed to the surface of frock；
(2) benchmark gauge block is fixedly mounted on the position to be tested of construction package and frock, obtains assembly；
(3) assembly obtained to step (2) carries out three-dimensional coordinates measurement, records the positional value W1 of benchmark gauge block；
(4) assembly for obtaining step (3) carries out the small magnitude stress-removal vibration in tri- directions of X, Y, Z on a vibration table Experiment；
(5) assembly that is obtained to step (4) carries out three-dimensional coordinates measurement, records the positional value W2 of benchmark gauge block, and with step Suddenly the positional value W1 that (3) obtain is compared, and obtains location variation δ 1, repeats to walk if location variation δ 1 is more than required value Suddenly (4) carry out the small magnitude stress-removal vibration test in tri- directions of X, Y, Z again, if location variation δ 1 is less than or equal to required value Then carry out step (6)；
(6) the stability vibration test in tri- directions of X, Y, Z is carried out on a vibration table to the assembly that step (5) obtains；
(7) assembly that is obtained to step (6) carries out three-dimensional coordinates measurement, records the positional value W3 of benchmark gauge block, and with step Suddenly the positional value W2 that (5) obtain is compared, and obtains location variation δ 2, repeats to walk if location variation δ 2 is more than required value Suddenly (4-6), step (8) is carried out if location variation δ 2 is less than or equal to required value；
(8) assembly obtained to step (7) carries out thermal cycling test；
(9) assembly that is obtained to step (8) carries out three-dimensional coordinates measurement, records the positional value W4 of benchmark gauge block, and with step Suddenly the positional value W3 that (7) obtain is compared, and obtains location variation δ 3, repeats to walk if location variation δ 3 is more than required value Suddenly (8), the off-test if location variation is less than or equal to required value.
The present invention compared with prior art the advantages of be：
(1) the inventive method is combined by mechanical test with thermal cycling test, is eliminated the machining stress in component, is assembled Stress etc., structure can be made to be rapidly reached stabilization；
(2) the inventive method is using small magnitude, the method for test of many times, it is ensured that the security of camera structure；
(3) the inventive method is by the way that camera structure component is connected with frock, and high accuracy is installed in frock and component Benchmark gauge block, the deformation of construction package is replaced with the change in location of benchmark gauge block, simplify measuring method, save time of measuring；
(4) the inventive method by establish two coordinate systems, repeatedly measure, take 3 points calculate position of centre of gravitys change sides Method, ensure the accuracy of measurement data；
(5) a kind of method for space camera structure stabilization, camera structure component is connected with stabilizing test tool Connect, reference for installation gauge block, carry out three-dimensional coordinates measurement, record benchmark gauge block position；Then small magnitude stress-removal experiment, experiment are carried out Component sensitive part change in location is judged by three-dimensional coordinates measurement benchmark gauge block change in location afterwards.If variable quantity exceeds required value, Small magnitude stress-removal experiment is then carried out again, if variable quantity is less than required value, continues stability test.Judge after experiment Location variation, if variable quantity exceeds required value, repeatedly for aforesaid operations until variable quantity is less than required value, structure reaches steady It is fixed；If variable quantity is less than required value, continue thermal cycling test.Location variation is judged after experiment, if variable quantity exceeds Required value, then thermal cycling test is carried out again, until variable quantity is less than required value, structure reaches stable；Will if variable quantity is less than Evaluation, then off-test, modular construction have reached stabilisation.The inventive method is tested by multiple power, heat aging, can be made to chi Very little or higher position accuracy demand modular construction reaches stable.
Brief description of the drawings
Fig. 1 is the FB(flow block) of test method of the present invention；
Fig. 2 is the composition schematic diagram of assembly in test method of the present invention；
Fig. 3 is that rectangular coordinate system O1X1Y1Z1 establishes figure in method of the invention；
Fig. 4 is that rectangular coordinate system O2X2Y2Z2 establishes figure in method of the invention.
Embodiment
A kind of method for space camera structure stabilization, step are as follows：
(1) construction package 2 to be stabilized in space camera is fixedly installed to the surface of frock 1；Described frock 1 is used In the switching of construction package 2 and shake table, i.e., after construction package 2 is installed in frock 1, frock 1 is pacified together with construction package 2 It is attached on shake table, for carrying out vibration test；The interface of benchmark gauge block is also provided in frock 1；
(2) three benchmark gauge blocks 5 are uniformly fixedly mounted at the position to be tested of construction package 2, three benchmark gauge blocks 5 are distinguished On the basis of gauge block C1, benchmark gauge block C2 and benchmark gauge block C3；
Uniformly be fixedly mounted three benchmark gauge blocks 4 first in frock 1, three benchmark gauge blocks 4 be respectively benchmark gauge block B1, Benchmark gauge block B2 and benchmark gauge block B3；Benchmark gauge block B1 and construction package 2 line of centres are designated as L1, benchmark gauge block B2 and structure The line of centres of component 2 is designated as L2, and benchmark gauge block B3 and construction package 2 line of centres are designated as L3, angle between L1 and L2, The angle between angle, L1 and L3 between L2 and L3 is 120 °；On by benchmark gauge block B1 and the straight line vertical with L1 Two benchmark gauge block A2 and benchmark gauge block A3, benchmark gauge block A2 is also distributed with and benchmark gauge block A3 is located at benchmark gauge block B1 both sides And benchmark gauge block A2 to benchmark gauge block B1 distance is equal with benchmark gauge block A3 to benchmark gauge block B1 distance；By datum quantity Two benchmark gauge block A4 and benchmark gauge block A5, benchmark gauge block A4 and benchmark gauge block are also distributed with block B2 and the straight line vertical with L2 A5 is located at benchmark gauge block B2 both sides and benchmark gauge block A4 to benchmark gauge block B2 distance and benchmark gauge block A5 to benchmark gauge block B2 Distance it is equal；Two benchmark gauge block A1 and benchmark gauge block is also distributed with by benchmark gauge block B3 and the straight line vertical with L3 A6, benchmark gauge block A1 and benchmark gauge block A6 be located at benchmark gauge block B3 both sides and benchmark gauge block A1 to benchmark gauge block B3 distance with Benchmark gauge block A6 to benchmark gauge block B3 distance are equal, obtain assembly；
During three-dimensional coordinates measurement, above-mentioned benchmark gauge block A1, benchmark gauge block A2, benchmark gauge block A3, benchmark gauge block A4, Benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark gauge block C1, benchmark gauge block C2 And benchmark gauge block C3 five non-mounting surface can be measured to；
(3) assembly for obtaining step (2) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W1；
(4) assembly that step (2) obtains is fixedly installed on shake table, carries out the small magnitude in tri- directions of X, Y, Z Stress-removal vibration test；
(5) assembly obtained to step (4) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W2, and compared with the positional value W1 that step (3) obtains, Location variation is obtained, the repeat step (4) if location variation is more than required value, if location variation is less than or equal to required value Then carry out step (6)；
(6) assembly obtained to step (4) is fixedly installed on shake table, carries out the stability in tri- directions of X, Y, Z Vibration test；
(7) assembly obtained to step (6) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W3, and compared with the positional value W2 that step (5) obtains, Location variation is obtained, the repeat step (4-6) if location variation is more than required value, if location variation is less than or equal to require Value then carries out step (8)；
(8) assembly obtained to step (7) carries out thermal cycling test；
(9) assembly obtained to step (8) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W4, and compared with the positional value W3 that step (7) obtains, Location variation is obtained, the repeat step (8) if location variation is more than required value, if location variation is less than or equal to required value Then off-test.
In described step (1), frock 1 is generally circular in cross section or square, and size is bigger than construction package 2, there is provided installation knot The interface of structure component 2 and benchmark gauge block, fundamental frequency are more than 5 times of the fundamental frequency of construction package 2；
The stainless steel cube that benchmark gauge block in described step (2) is 20mm × 20mm × 20mm, centre punching are used In being fixed in frock 1；The planarity requirements in remaining 5 face are 0.002mm in addition to mounting surface, and angle requirement is 90 ° ± 40″；
In described step (4), small magnitude stress-removal vibration test condition will be less than stability vibration test, be stability 3/4ths of vibration test condition；
In described step (6), the condition of stability vibration test is a given value, and the given value is generally a song Line, it is the vibration test condition that construction package 2 to be stabilized is decomposed from space camera subsystem；
In described step (8), thermal cycling test condition is generally：Vacuum is better than 1.3X10-3Pa；Rate of temperature change is not More than 3 DEG C/1h；Temperature cycles：Room temperature is incubated 4h to 45 DEG C, then cools to 20 DEG C, is incubated 4h；Cycle-index：2 times；
In described step (3), (5) and (7), during three-dimensional coordinates measurement, if a benchmark gauge block A1 summit is summit A1, A benchmark gauge block A2 summit is summit A2, and a benchmark gauge block A3 summit is summit A3, and one of benchmark gauge block A4 pushes up Point is summit A4, and a benchmark gauge block A5 summit is summit A5, and a benchmark gauge block A6 summit is summit A6, benchmark gauge block A B1 summit is summit B1, and a benchmark gauge block B2 summit is summit B2, and a benchmark gauge block B3 summit is summit B3, benchmark gauge block C1 a summit are summit C1, and a benchmark gauge block C2 summit is summit C2, one of benchmark gauge block C3 Summit is summit C3；
Benchmark gauge block A1 summit A1 acquisition methods are：Obtained by the intersection point for measuring three adjacent planes；Other The acquisition methods on summit are the same as summit A1；
Rectangular coordinate system O1X1Y1Z1 is defined as：Origin O1 is summit A3 to summit A1 and the intersection point of summit A5 line； Origin O1 to summit A5 line is X1 axles；Origin O1 to summit A3 line is Y1 axles；Z1 axles determine according to the right-hand rule；
Rectangular coordinate system O2X2Y2Z2 is defined as：Origin O2 is summit A6 to summit A2 and the intersection point of summit A4 line； Origin O2 to summit A2 line is X2 axles；Origin O2 to summit A6 line is Y2 axles；Z2 axles determine according to the right-hand rule；
In described step (3), (5) and (7) during three-dimensional coordinates measurement, respectively in coordinate system O1X1Y1Z1 and O2X2Y2Z2 Measure summit A1-A6, B1-B3, C1-C3 coordinate；Duplicate measurements twice, records such as table 1；
Table 1 summit A1-A6, B1-B3, C1-C3 coordinate value
In described step (3), (5) and (7) during three-dimensional coordinates measurement, point on the basis of the A1-A6 of summit, correspondence point is tested Subtract each other change to should be less than being equal to 3 μm；Summit B1-B3 change in location value is replaced by B1-B3 position of centre of gravity B change, is divided into Level change and vertical change, two changes of direction are respectively less than 3 μm；Summit C1-C3 judgement and computational methods and B1-B3 phases Together；Calculated respectively under OX1Y1Z1 and OX2Y2Z2 coordinate systems, detailed computational methods are as follows：
Summit B1-B3 change in location value is replaced by B1-B3 position of centre of gravity B change, summit B1-B3 position of centre of gravity B horizontal become turns to：
Summit B1-B3 position of centre of gravity B vertical change is：
It is the FB(flow block) of test method of the present invention as shown in Figure 1, Fig. 2 is the structure of experimental rig used in the inventive method Composition figure.Wherein 1 is needs to carry out the camera structure component for stabilizing experiment, and 2 be test tool, and component need to be designed with frock and connect Mouth connection.3,4,5 in Fig. 2 be benchmark gauge block, is respectively labeled as A, B, C, and each benchmark gauge block is cube, design interface It is connected with frock, and is fixed in the glue of surrounding point 502.The coordinate system as shown in Fig. 3,4, the summit of each gauge block is respectively defined as A1- A6、B1-B3、C1-C3。
Fig. 2 assembly is subjected to vibration test stress-removal and thermal cycling test stress-removal, wherein vibration test condition point Two kinds：Stability vibration test condition and small magnitude stress-removal vibration test condition.Stability vibration test condition generally from Camera subsystem decomposes the vibration test condition of component, and small magnitude stress-removal vibration test condition will be less than stability vibration examination Test, be recommended as 3/4ths of stability vibration test.Every time three-dimensional coordinates measurement, determinating reference gauge block top are carried out before and after vibration The changes in coordinates amount of point, judges whether modular construction is stablized with this.If unstable rule repetitive vibrations test stress-removal, if stable Carry out thermal cycling test stress-removal.Thermal cycling test stress-removal condition is generally：Vacuum is better than 1.3X10-3Pa；Temperature change Rate is not more than 3 DEG C/1h；Temperature cycles：Room temperature → 45 DEG C (insulation 4h) → 20 DEG C (insulation 4h)；Cycle-index：2 times.Thermal cycle Three-dimensional coordinates measurement is carried out before and after experiment, the changes in coordinates amount on determinating reference gauge block summit, judges whether modular construction is steady with this It is fixed.If unstable rule repeated thermal cycles test stress-removal, the off-test if stable.
In the three-dimensional coordinates measurement whether stablized of decision structure is carried out, Fig. 3 is coordinate system O1X1Y1Z1 foundation, foundation side Method is：O1 is A3 to straight line A1A5 intersection point, and using O1 as origin, using O1A5 as X1 axles, rectangular co-ordinate is established by Y1 axles of O1A3 It is O1X1Y1Z1.Fig. 4 is coordinate system O2X2Y2Z2 foundation, and method for building up is：O2 be A6 to straight line A2A4 intersection point using O2 as Origin, using O2A2 as X2 axles, rectangular coordinate system O2X2Y2Z2 is established by Y2 axles of O2A6.Respectively in coordinate system O1X1Y1Z1, Measurement point A1-A6, B1-B3, C1-C3 coordinate in O2X2Y2Z2.Duplicate measurements twice, records；Angle is calculated according to coordinate data Degrees of data.Point on the basis of A1-A6, experiment correspondence point subtract each other change and should be less than 3 μm；B1-B3 change in location by B1-B3 weight Heart position B change replaces, and is divided into horizontal change and vertical change, and two changes of direction is respectively less than 3 μm；C1-C3 judgement And computational methods are identical with B1-B3.
This test method can be combined by mechanical test with thermal cycling test, is eliminated the machining stress in component, is filled With stress etc., structure can be made to be rapidly reached stabilization, ensure that dimensional stability and position of the modular construction after final assembly are stable Property.It can be widely applied to the various structure types higher to dimensional stability and positional stability required precision.
Embodiment
The outer profile size of the construction package 2 of space camera is Φ 200mm × 100mm, the size of frock 1 be Φ 720mm × 70mm。
It is required that the frequency range of stability vibration test is 20~2000Hz, total root mean square is 4.87grms, the load time For 2 minutes.During mechanical test and thermal cycling test, determinating reference gauge block change in location required value is less than or equal to 3 μm.
The stabilized test method of construction package, process are as follows：
(1) construction package 2 to be stabilized in space camera is fixedly installed to the surface of frock 1；Described frock 1 is used In the switching of construction package 2 and shake table, i.e., after construction package 2 is installed in frock 1, frock 1 is pacified together with construction package 2 It is attached on shake table, for carrying out vibration test；The interface of benchmark gauge block is also provided in frock 1；
(2) the position to be tested of construction package 2 uniformly be fixedly mounted three benchmark gauge blocks, respectively benchmark gauge block C1, Benchmark gauge block C2 and benchmark gauge block C3；
Three benchmark gauge blocks, respectively benchmark gauge block B1, benchmark gauge block B2 and base is uniformly fixedly mounted first in frock 1 Quasi- gauge block B3；The line of centres of benchmark gauge block B1 and construction package 2 is designated as L1, and benchmark gauge block B2 and construction package 2 center connect Line is designated as L2, and benchmark gauge block B3 and construction package 2 line of centres are designated as L3, between the angle, L2 and L3 between L1 and L2 Angle between angle, L1 and L3 is 120 °, and L1, L2, L3 length are 220mm；Passing through benchmark gauge block B1 and hung down with L1 Two benchmark gauge block A2 and benchmark gauge block A3, benchmark gauge block A2 are also distributed with straight straight line and benchmark gauge block A3 is located at datum quantity Block B1 both sides and benchmark gauge block A2 to benchmark gauge block B1 distance is equal with benchmark gauge block A3 to benchmark gauge block B1 distance, For 225mm；Two benchmark gauge block A4 and benchmark gauge block A5 are also distributed with by benchmark gauge block B2 and the straight line vertical with L2, Benchmark gauge block A4 and benchmark gauge block A5 is located at benchmark gauge block B2 both sides and benchmark gauge block A4 to benchmark gauge block B2 distance and base Quasi- gauge block A5 to benchmark gauge block B2 distance are equal, are 225mm；On by benchmark gauge block B3 and the straight line vertical with L3 also Be distributed with two benchmark gauge block A1 and benchmark gauge block A6, benchmark gauge block A1 and benchmark gauge block A6 be located at benchmark gauge block B3 both sides and Benchmark gauge block A1 to benchmark gauge block B3 distance is equal with benchmark gauge block A6 to benchmark gauge block B3 distance, is 225mm, obtains Assembly；
(3) assembly for obtaining step (2) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W1；
(4) assembly that step (2) obtains is fixedly installed on shake table, carries out the small magnitude in tri- directions of X, Y, Z Stress-removal vibration test；
(5) assembly obtained to step (4) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W2, and compared with the positional value W1 that step (3) obtains, Location variation is obtained, the repeat step (4) if location variation is more than required value, if location variation is less than or equal to required value Then carry out step (6)；
(6) assembly obtained to step (4) is fixedly installed on shake table, carries out the stability in tri- directions of X, Y, Z Vibration test；
(7) assembly obtained to step (6) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W3, and compared with the positional value W2 that step (5) obtains, Location variation is obtained, the repeat step (4-6) if location variation is more than required value, if location variation is less than or equal to require Value then carries out step (8)；
(8) assembly obtained to step (7) carries out thermal cycling test；
(9) assembly obtained to step (8) carries out three-dimensional coordinates measurement, record benchmark gauge block A1, benchmark gauge block A2, benchmark Gauge block A3, benchmark gauge block A4, benchmark gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark Gauge block C1, benchmark gauge block C2 and benchmark gauge block C3 positional value W4, and compared with the positional value W3 that step (7) obtains, Location variation is obtained, the repeat step (8) if location variation is more than required value, if location variation is less than or equal to required value Then off-test.
It is as shown in table 2 to stabilize experiment procedural test data.It can be seen that according to data in table and tested by the stabilisation Method, the location variation of modular construction measurement point taper into, and the final requirement met less than or equal to 3 μm, component internal should Power discharges, and structure tends towards stability, and method is effective.
Table 2 stabilizes the test data during experiment
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.

Claims (10)

  1. A kind of 1. method for space camera structure stabilization, it is characterised in that step is as follows：
    (1) construction package to be stabilized in space camera is fixedly installed to the surface of frock；
    (2) benchmark gauge block is fixedly mounted on the position to be tested of construction package and frock, obtains assembly；
    (3) assembly obtained to step (2) carries out three-dimensional coordinates measurement, records the positional value W1 of benchmark gauge block；
    (4) assembly for obtaining step (3) carries out the small magnitude stress-removal vibration examination in tri- directions of X, Y, Z on a vibration table Test；
    (5) assembly that is obtained to step (4) carries out three-dimensional coordinates measurement, records the positional value W2 of benchmark gauge block, and with step (3) Obtained positional value W1 is compared, and obtains location variation δ 1, the repeat step (4) if location variation δ 1 is more than required value The small magnitude stress-removal vibration test in tri- directions of X, Y, Z is carried out again, is entered if location variation δ 1 is less than or equal to required value Row step (6)；
    (6) the stability vibration test in tri- directions of X, Y, Z is carried out on a vibration table to the assembly that step (5) obtains；
    (7) assembly that is obtained to step (6) carries out three-dimensional coordinates measurement, records the positional value W3 of benchmark gauge block, and with step (5) Obtained positional value W2 is compared, and obtains location variation δ 2, the repeat step (4- if location variation δ 2 is more than required value 6), step (8) is carried out if location variation δ 2 is less than or equal to required value；
    (8) assembly obtained to step (7) carries out thermal cycling test；
    (9) assembly that is obtained to step (8) carries out three-dimensional coordinates measurement, records the positional value W4 of benchmark gauge block, and with step (7) Obtained positional value W3 is compared, and obtains location variation δ 3, the repeat step if location variation δ 3 is more than required value (8), the off-test if location variation is less than or equal to required value.
  2. A kind of 2. method for space camera structure stabilization according to claim 1, it is characterised in that：Described step Suddenly in (1), frock is used for the switching of construction package and shake table, i.e., after construction package is installed in frock, frock is together with structure Component is co-mounted on shake table, for carrying out vibration test；The interface of benchmark gauge block is also provided in frock；The size of frock Bigger than construction package, fundamental frequency is more than 5 times of construction package fundamental frequency.
  3. A kind of 3. method for space camera structure stabilization according to claim 1, it is characterised in that：Described step Suddenly in (2), benchmark gauge block is 20mm × 20mm × 20mm stainless steel cube, and centre is punched for being fixed on frock；Base Quasi- gauge block planarity requirements in remaining 5 face in addition to mounting surface are 0.002mm, and angle requirement is 90 ° ± 40 ".
  4. A kind of 4. method for space camera structure stabilization according to claim 1, it is characterised in that：Described step Suddenly in (2), three benchmark gauge blocks are uniformly fixedly mounted in the position to be tested of construction package, and three benchmark gauge blocks are respectively datum quantity Block C1, benchmark gauge block C2 and benchmark gauge block C3；
    In frock uniformly be fixedly mounted three benchmark gauge blocks, three benchmark gauge blocks be respectively benchmark gauge block B1, benchmark gauge block B2 and Benchmark gauge block B3；
    The line of centres of benchmark gauge block B1 and construction package is designated as L1, and the line of centres of benchmark gauge block B2 and construction package is designated as The line of centres of L2, benchmark gauge block B3 and construction package is designated as L3；
    The angle between the angle between angle, L2 and L3, L1 and L3 between L1 and L2 is 120 °；
    Two benchmark gauge block A2 and benchmark gauge block A3, benchmark is also distributed with by benchmark gauge block B1 and the straight line vertical with L1 Gauge block A2 and benchmark gauge block A3 is located at benchmark gauge block B1 both sides and benchmark gauge block A2 to benchmark gauge block B1 distance and datum quantity Block A3 to benchmark gauge block B1 distance are equal；
    Two benchmark gauge block A4 and benchmark gauge block A5, benchmark is also distributed with by benchmark gauge block B2 and the straight line vertical with L2 Gauge block A4 and benchmark gauge block A5 is located at benchmark gauge block B2 both sides and benchmark gauge block A4 to benchmark gauge block B2 distance and datum quantity Block A5 to benchmark gauge block B2 distance are equal；
    Two benchmark gauge block A1 and benchmark gauge block A6, benchmark is also distributed with by benchmark gauge block B3 and the straight line vertical with L3 Gauge block A1 and benchmark gauge block A6 is located at benchmark gauge block B3 both sides and benchmark gauge block A1 to benchmark gauge block B3 distance and datum quantity Block A6 to benchmark gauge block B3 distance are equal；
    During three-dimensional coordinates measurement, above-mentioned benchmark gauge block A1, benchmark gauge block A2, benchmark gauge block A3, benchmark gauge block A4, benchmark Gauge block A5, benchmark gauge block A6, benchmark gauge block B1, benchmark gauge block B2, benchmark gauge block B3, benchmark gauge block C1, benchmark gauge block C2 and Benchmark gauge block C3 five non-mounting surface can be measured to.
  5. A kind of 5. method for space camera structure stabilization according to claim 1, it is characterised in that：Described step Suddenly in (4), small magnitude stress-removal vibration test condition is the stability vibration less than 3/4ths of stability vibration test condition Experimental condition is a given value, and the given value is to decompose shaking for construction package to be stabilized (2) from space camera subsystem Dynamic test condition.
  6. A kind of 6. method for space camera structure stabilization according to claim 1, it is characterised in that：Described step Suddenly in (8), thermal cycling test condition is：Vacuum is better than 1.3X10-3Pa；Rate of temperature change is not more than 3 DEG C/1h；Temperature cycles： Room temperature is incubated 4h to 45 DEG C, then cools to 20 DEG C, is incubated 4h；Cycle-index：2 times.
  7. A kind of 7. method for space camera structure stabilization according to claim 4, it is characterised in that：Described step Suddenly in (3), (5) and (7), during three-dimensional coordinates measurement, if a benchmark gauge block A1 summit is summit A1, one of benchmark gauge block A2 Summit is summit A2, and a benchmark gauge block A3 summit is summit A3, and a benchmark gauge block A4 summit is summit A4, datum quantity A block A5 summit is summit A5, and a benchmark gauge block A6 summit is summit A6, and a benchmark gauge block B1 summit is top Point B1, benchmark gauge block B2 a summit are summit B2, and a benchmark gauge block B3 summit is summit B3, the one of benchmark gauge block C1 Individual summit is summit C1, and a benchmark gauge block C2 summit is summit C2, and a benchmark gauge block C3 summit is summit C3；
    Benchmark gauge block A1 summit A1 acquisition methods are：Obtained by the intersection point for measuring three adjacent planes；Other summits Acquisition methods with summit A1；
    Rectangular coordinate system O1X1Y1Z1 is defined as：Origin O1 is summit A3 to summit A1 and the intersection point of summit A5 line；Origin O1 to summit A5 line is X1 axles；Origin O1 to summit A3 line is Y1 axles；Z1 axles determine according to the right-hand rule；
    Rectangular coordinate system O2X2Y2Z2 is defined as：Origin O2 is summit A6 to summit A2 and the intersection point of summit A4 line；Origin O2 to summit A2 line is X2 axles；Origin O2 to summit A6 line is Y2 axles；Z2 axles determine according to the right-hand rule；
    In described step (3), (5) and (7) during three-dimensional coordinates measurement, measured respectively in coordinate system O1X1Y1Z1 and O2X2Y2Z2 Summit A1-A6, B1-B3, C1-C3 coordinate；Duplicate measurements twice, records.
  8. A kind of 8. method for space camera structure stabilization according to claim 7, it is characterised in that：Summit A1- The result of A6, B1-B3, C1-C3 coordinate record is as shown in table 1：
    Table 1 summit A1-A6, B1-B3, C1-C3 coordinate value represent as follows：
  9. A kind of 9. method for space camera structure stabilization according to claim 7, it is characterised in that：Summit A1- The decision method of A6 change in location value is：Experiment correspondence point subtracts each other.
  10. A kind of 10. method for space camera structure stabilization according to claim 7, it is characterised in that：Summit B1- The decision method of B3 change in location value is：
    Summit B1-B3 change in location value is replaced by B1-B3 position of centre of gravity B change, is divided into horizontal change and vertical change, Calculated respectively under OX1Y1Z1 and OX2Y2Z2 coordinate systems；The summit C1-C3 same B1-B3 of decision method；
    Summit B1-B3 change in location value is replaced by B1-B3 position of centre of gravity B change, summit B1-B3 position of centre of gravity B's Level, which becomes, to be turned to：
    <mfenced open = "" close = ""> <mtable> <mtr> <mtd> <mrow> <mi>B</mi> <mi>&amp;Delta;</mi> <mi>X</mi> <mi>Y</mi> <mo>=</mo> <mi>s</mi> <mi>q</mi> <mi>r</mi> <mi>t</mi> <mrow> <mo>(</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>X</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>X</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>X</mi> <mn>2</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>-</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>X</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>X</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>X</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>+</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Y</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>Y</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>Y</mi> <mn>2</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>-</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Y</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>Y</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>Y</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>)</mo> </mrow> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mo>=</mo> <mi>s</mi> <mi>q</mi> <mi>r</mi> <mi>t</mi> <mrow> <mo>(</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>X</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>1</mn> <mi>X</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>2</mn> <mi>X</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>2</mn> <mi>X</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>3</mn> <mi>X</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>3</mn> <mi>X</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>+</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Y</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>1</mn> <mi>Y</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>2</mn> <mi>Y</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>2</mn> <mi>Y</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>3</mn> <mi>Y</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>3</mn> <mi>Y</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>)</mo> </mrow> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mo>=</mo> <mi>s</mi> <mi>q</mi> <mi>r</mi> <mi>t</mi> <mrow> <mo>(</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mi>B</mi> <mn>1</mn> <mi>&amp;Delta;</mi> <mi>X</mi> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>&amp;Delta;</mi> <mi>X</mi> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>&amp;Delta;</mi> <mi>X</mi> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>+</mo> <msup> <mrow> <mo>&amp;lsqb;</mo> <mfrac> <mrow> <mi>B</mi> <mn>1</mn> <mi>&amp;Delta;</mi> <mi>Y</mi> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>&amp;Delta;</mi> <mi>Y</mi> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>&amp;Delta;</mi> <mi>Y</mi> </mrow> <mn>3</mn> </mfrac> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>)</mo> </mrow> </mrow> </mtd> </mtr> </mtable> </mfenced>
    Summit B1-B3 position of centre of gravity B vertical change is：
    <mrow> <mtable> <mtr> <mtd> <mrow> <mi>B</mi> <mi>&amp;Delta;</mi> <mi>Z</mi> <mo>=</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Z</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>Z</mi> <mn>2</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>Z</mi> <mn>2</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>-</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Z</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>Z</mi> <mn>1</mn> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>Z</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> <mo>=</mo> <mfrac> <mrow> <mo>(</mo> <mi>B</mi> <mn>1</mn> <mi>Z</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>1</mn> <mi>Z</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>2</mn> <mi>Z</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>2</mn> <mi>Z</mi> <mn>1</mn> <mo>)</mo> <mo>+</mo> <mo>(</mo> <mi>B</mi> <mn>3</mn> <mi>Z</mi> <mn>2</mn> <mo>-</mo> <mi>B</mi> <mn>3</mn> <mi>Z</mi> <mn>1</mn> <mo>)</mo> </mrow> <mn>3</mn> </mfrac> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <mo>=</mo> <mfrac> <mrow> <mi>B</mi> <mn>1</mn> <mi>&amp;Delta;</mi> <mi>Z</mi> <mo>+</mo> <mi>B</mi> <mn>2</mn> <mi>&amp;Delta;</mi> <mi>Z</mi> <mo>+</mo> <mi>B</mi> <mn>3</mn> <mi>&amp;Delta;</mi> <mi>Z</mi> </mrow> <mn>3</mn> </mfrac> </mrow> </mtd> </mtr> </mtable> <mo>.</mo> </mrow>
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US20020154379A1 (en) * 1997-04-02 2002-10-24 Tonar William L. Electrochromic rearview mirror assembly incorporating a display/signal light
CN102506807A (en) * 2011-10-24 2012-06-20 北京航天计量测试技术研究所 Method for measuring deformation amount of mechanical structure
CN106148863A (en) * 2015-04-17 2016-11-23 首都航天机械公司 Cast aluminium alloy gold circular thin-wall structural member stress relieving and dimensionally stable method

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020154379A1 (en) * 1997-04-02 2002-10-24 Tonar William L. Electrochromic rearview mirror assembly incorporating a display/signal light
CN102506807A (en) * 2011-10-24 2012-06-20 北京航天计量测试技术研究所 Method for measuring deformation amount of mechanical structure
CN106148863A (en) * 2015-04-17 2016-11-23 首都航天机械公司 Cast aluminium alloy gold circular thin-wall structural member stress relieving and dimensionally stable method

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