CN109141751A - Satellite rotary part Low-vacuum dynamic test method - Google Patents
Satellite rotary part Low-vacuum dynamic test method Download PDFInfo
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- CN109141751A CN109141751A CN201810850150.XA CN201810850150A CN109141751A CN 109141751 A CN109141751 A CN 109141751A CN 201810850150 A CN201810850150 A CN 201810850150A CN 109141751 A CN109141751 A CN 109141751A
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- 238000010998 test method Methods 0.000 title claims abstract description 25
- 238000005259 measurement Methods 0.000 claims abstract description 32
- 238000012360 testing method Methods 0.000 claims abstract description 25
- 238000009434 installation Methods 0.000 claims abstract description 14
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 7
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- GNFTZDOKVXKIBK-UHFFFAOYSA-N 3-(2-methoxyethoxy)benzohydrazide Chemical compound COCCOC1=CC=CC(C(=O)NN)=C1 GNFTZDOKVXKIBK-UHFFFAOYSA-N 0.000 claims description 3
- FGUUSXIOTUKUDN-IBGZPJMESA-N C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 Chemical compound C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 FGUUSXIOTUKUDN-IBGZPJMESA-N 0.000 claims description 3
- 230000000994 depressogenic effect Effects 0.000 claims description 3
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- 238000001514 detection method Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 12
- 238000013461 design Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
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- 238000010586 diagram Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 241000222712 Kinetoplastida Species 0.000 description 1
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- 238000003384 imaging method Methods 0.000 description 1
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- 238000009987 spinning Methods 0.000 description 1
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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
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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Abstract
The present invention provides a kind of satellite rotary part Low-vacuum dynamic test methods, carry out successively including that a. equipment is adjusted by using low vacuum tank (1) and high-precision slow-speed of revolution dynamic balancing machine (2)；B. installation calibration tooling；C. precision calibration；D., test product is installed；E. movable part is unfolded；F. normal pressure state dynamic balancing measurement；G. the test of low-pressure state dynamic balancing measurement, it can be avoided the influences of the factors to the measuring accuracy of rotary part dynamic balance running on star such as windage, air flowing, solve the problems, such as the high-precision dynamic balancing Detection & Controling of large-scale flexible expansion movement load rotor assembly, ensure remote sensing image quality, it can overcome the problems, such as that satellite rotary part dynamic balance running precision is insufficient under existing ground environment, the dynamic balancing measurement precision of satellite rotary part is effectively improved, and then improves its operation on orbit performance.
Description
Technical field
The present invention relates to a kind of satellite rotary part Low-vacuum dynamic test methods.
Background technique
Satellite in orbit under state, realize by the movements such as solar array orientation, the acquisition of sweep mechanism data, imager imaging
And Function, the precision and reliability of in-house facility are depended not only upon, also requires satellite that there is stable posture.And in work
Make under state, the operation of satellite borne equipment can generate variable amount of disturbance, and the excessive disturbance torque of magnitude will affect satellite platform appearance
The stability and remote sensing precision of state, and then the normal work of load observation and other systems is influenced, or even will affect satellite
Safety.Therefore, there is great meaning to the control of satellite borne equipment disturbance quantity.Rotation imbalance problem is the important of generation disturbance
One of factor.Spinning stability and remote sensing satellite, meteorological satellite etc., often with large-scale, slowly run component, due to material,
Various reasons such as processing, assembly, bring the problems such as rotatable parts Mass Distribution is uneven, there are undesirable fit-up gaps,
Cause satellite rotation imbalance.Therefore, the high-precision dynamic balancing measurement of large-sized low-speed rotatable parts is become to improve with control and is defended
The key technology of star remote sensing capability.
Summary of the invention
The purpose of the present invention is to provide a kind of satellite rotary part Low-vacuum dynamic test methods.
The present invention provides a kind of satellite rotary part Low-vacuum dynamic test method, comprising:
It carries out successively including that a. equipment is adjusted using low vacuum tank (1) and high-precision slow-speed of revolution dynamic balancing machine (2)；B. it installs
Demarcate tooling；C. precision calibration；D., test product is installed；E. movable part is unfolded；F. normal pressure state dynamic balancing measurement；G. low pressure
The test of state dynamic balancing measurement.
Further, in the above-mentioned methods, a. equipment adjustment, comprising:
By high-precision slow-speed of revolution dynamic balancing machine (2) bottom level regulating device, by high-precision slow-speed of revolution dynamic balancing machine (2)
Workpiece mounting surface (21) leveling to two orthogonal direction levelness be better than 0.02mm/m.
Further, in the above-mentioned methods, the b. installation calibration tooling, comprising:
The workpiece installation that motor (41) are fixed on the high-precision slow-speed of revolution dynamic balancing machine (2) will be demarcated with pressing plate and screw
On face (21), calibration rotor (42) is connect with calibration motor (41) with screw, and adjust its concentricity better than 0.02m, wherein
The calibration rotor (42) there are two plane, upper alignment surface (43) and lower alignment surface (44) is matched, each with plane have 12 it is equal
Calibration counterweight (45) mounting hole of cloth.
Further, in the above-mentioned methods, the c. precision calibration, comprising:
Take a calibration counterweight (45), the amount of unbalance of calibration counterweight (45) is 10Umar, wherein the Umar is
High-precision slow-speed of revolution dynamic balancing machine (2) detectable minimum amount of unbalance under workpiece spin mode；
Calibration counterweight (45) is sequentially arranged on 12 mounting holes of the upper alignment surface (43), in each position
The calibration motor (41) is measured at load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42),
Obtain 12 points of static-unbalance average value e1；
Calibration counterweight is sequentially arranged on 12 mounting holes of lower alignment surface (44), is demarcated described in each position finding
Motor (41) is at load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42), obtains 12 points quiet
Amount of unbalance average value e2；
As (e1-10Umar)/10Umar < ± 12% and (e2-10Umar)/10Umar < ± 12%, it is determined as qualification,
Otherwise it needs to readjust dynamic balancing machine and demarcates tooling and repeat to demarcate until qualified；
Calibration motor (41), calibration rotor (42) and calibration counterweight (45) and its connector are removed after calibration.
Further, in the above-mentioned methods, the d. installs test product, comprising:
Above the spin load (3) lifting to the high-precision slow-speed of revolution dynamic balancing machine (2), pass through counter flange
(33) mounting screw fastens.
Further, in the above-mentioned methods, the e. movable part expansion, comprising:
After the spin load (3) is fixed, movable part (32) are unlocked and are unfolded；Starting spin motor (31)
And debug, check whether spin load (3) work is normal, and the spin motor (31) is closed after debugging.
Further, in the above-mentioned methods, the f. normal pressure state dynamic balancing measurement, comprising:
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes
Close spin motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), meter
Counterweight azimuth angle theta 1, the θ 2 in two counterweight faces are calculated, and matches weight m1, m2；
According to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, the second counterweight
2 direction of azimuth angle theta in face (35), radius r2 Weight m2；
Starting spin motor (31), quiet, the couple-unbalance of repetition measurement movable part (32) at working speed r are such as discontented
Sufficient operation on orbit requirement, then carry out repetition measurement until meeting the requirements by step f..
Further, in the above-mentioned methods, the g. low-pressure state dynamic balancing adjustment, comprising:
The cover (11) of low vacuum tank (1) is covered, after pedestal (12) sealing, starting vacuum evacuation device makes low vacuum tank
(1) vacuum degree is reduced to 5Pa or less in tank；
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes
Close spin motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), meter
Counterweight azimuth angle theta 1, the θ 2 in two counterweight faces are calculated, and matches weight m1, m2；Low vacuum tank (1) is depressed into normal pressure state again, is opened
Cover (11), according to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, second matches
2 direction of azimuth angle theta of weight face (35), radius r2 Weight m2；
The cover (11) of low vacuum tank (1) is covered again, after pedestal (12) sealing, starting vacuum evacuation device makes low true
In slack tank (1) tank vacuum degree be reduced to installation test product hereinafter, repetition measurement at working speed r movable part (32) it is quiet, even
Amount of unbalance is such as unsatisfactory for operation on orbit requirement, then carries out repetition measurement until meeting the requirements by step g..
Further, in the above-mentioned methods, the high-precision slow-speed of revolution dynamic balancing machine (2) has workpiece spin Working mould
Formula, i.e. dynamic balancing machine do not rotate, the mode of measured workpiece rotation.
Compared with prior art, beneficial effects of the present invention are as follows:
1. base has been established in the application for dynamic balance running technology under space environment present invention can apply to whole star component test
Plinth provides technical support for the design of spacecraft structure loss of weight.
Turn 2. the present invention solves the flexible expansion movement load of large size that FY-3 series of satellites Microwave Imager is representative
The high-precision dynamic balancing Detection & Controling problem of kinetoplast assembly, it is ensured that remote sensing image quality.
3. it is also possible to apply the invention to the analyses of Flexible Satellite Attitude control system and design, solar battery array structure and machine
The fields such as the optimization design of structure.
Detailed description of the invention
Fig. 1 is the product testing status diagram of one embodiment of the invention；
Fig. 2 is the precision calibration status diagram of one embodiment of the invention；
Wherein, low vacuum tank (1), cover (11), pedestal (12), high-precision slow-speed of revolution dynamic balancing machine (2), workpiece mounting surface
(21), spin load (3), spin motor (31), movable part (32), counter flange (33), the first counterweight face (34), second are matched
Weight face (35), calibration motor (41), calibration rotor (42), upper alignment surface (43), lower alignment surface (44), calibration counterweight (45).
Specific embodiment
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, with reference to the accompanying drawing and specific real
Applying mode, the present invention is described in further detail.
As shown in Figure 1, the present invention provides a kind of satellite rotary part Low-vacuum dynamic test method, comprising:
It carries out successively including that a. equipment is adjusted using low vacuum tank (1) and high-precision slow-speed of revolution dynamic balancing machine (2)；B. it installs
Demarcate tooling；C. precision calibration；D., test product is installed；E. movable part is unfolded；F. normal pressure state dynamic balancing measurement；G. low pressure
The test of state dynamic balancing measurement.
Here, utilizing Low-vacuum dynamic test device satellite under the in-orbit environment of ground simulation the present invention provides a kind of
The method of rotary part dynamic balance running, the test method can be avoided the factors such as windage, air flowing to rotary part on star
The influence of the measuring accuracy of dynamic balance running solves the high-precision dynamic balancing of large-scale flexible expansion movement load rotor assembly
Detection & Controling problem, it is ensured that remote sensing image quality can overcome satellite rotary part dynamic balancing under existing ground environment to try
The problem for testing precision deficiency, effectively improves the dynamic balancing measurement precision of satellite rotary part, and then improves its operation on orbit performance.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, a. equipment adjustment, comprising:
By high-precision slow-speed of revolution dynamic balancing machine (2) bottom level regulating device, by high-precision slow-speed of revolution dynamic balancing machine (2)
Workpiece mounting surface (21) leveling to two orthogonal direction levelness be better than 0.02mm/m.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the b. installation calibration tooling,
Include:
The workpiece installation that motor (41) are fixed on the high-precision slow-speed of revolution dynamic balancing machine (2) will be demarcated with pressing plate and screw
On face (21), calibration rotor (42) is connect with calibration motor (41) with screw, and adjust its concentricity better than 0.02m, wherein
The calibration rotor (42) there are two plane, upper alignment surface (43) and lower alignment surface (44) is matched, each with plane have 12 it is equal
Calibration counterweight (45) mounting hole of cloth.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the c. precision calibration, comprising:
Take a calibration counterweight (45), the amount of unbalance of calibration counterweight (45) is 10Umar, wherein the Umar is
High-precision slow-speed of revolution dynamic balancing machine (2) detectable minimum amount of unbalance under workpiece spin mode；
Calibration counterweight (45) is sequentially arranged on 12 mounting holes of the upper alignment surface (43), in each position
The calibration motor (41) is measured at load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42),
Obtain 12 points of static-unbalance average value e1；
Calibration counterweight is sequentially arranged on 12 mounting holes of lower alignment surface (44), is demarcated described in each position finding
Motor (41) is at load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42), obtains 12 points quiet
Amount of unbalance average value e2；
As (e1-10Umar)/10Umar < ± 12% and (e2-10Umar)/10Umar < ± 12%, it is determined as qualification,
Otherwise it needs to readjust dynamic balancing machine and demarcates tooling and repeat to demarcate until qualified；
Calibration motor (41), calibration rotor (42) and calibration counterweight (45) and its connector are removed after calibration.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the d. installs test product,
Include:
Above the spin load (3) lifting to the high-precision slow-speed of revolution dynamic balancing machine (2), pass through counter flange
(33) mounting screw fastens.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the e. movable part expansion,
Include:
After the spin load (3) is fixed, movable part (32) are unlocked and are unfolded；Starting spin motor (31)
And debug, check whether spin load (3) work is normal, and the spin motor (31) is closed after debugging.
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, f. normal pressure state dynamic balancing is surveyed
Examination, comprising:
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes
Close spin motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), meter
Counterweight azimuth angle theta 1, the θ 2 in two counterweight faces are calculated, and matches weight m1, m2；
According to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, the second counterweight
2 direction of azimuth angle theta in face (35), radius r2 Weight m2；
Starting spin motor (31), quiet, the couple-unbalance of repetition measurement movable part (32) at working speed r are such as discontented
Sufficient operation on orbit requirement, then carry out repetition measurement until meeting the requirements by step f..
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the g. low-pressure state dynamic balancing
Adjustment, comprising:
The cover (11) of low vacuum tank (1) is covered, after pedestal (12) sealing, starting vacuum evacuation device makes low vacuum tank
(1) vacuum degree is reduced to 5Pa or less in tank；
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes
Close spin motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), meter
Counterweight azimuth angle theta 1, the θ 2 in two counterweight faces are calculated, and matches weight m1, m2；Low vacuum tank (1) is depressed into normal pressure state again, is opened
Cover (11), according to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, second matches
2 direction of azimuth angle theta of weight face (35), radius r2 Weight m2；
The cover (11) of low vacuum tank (1) is covered again, after pedestal (12) sealing, starting vacuum evacuation device makes low true
In slack tank (1) tank vacuum degree be reduced to installation test product hereinafter, repetition measurement at working speed r movable part (32) it is quiet, even
Amount of unbalance is such as unsatisfactory for operation on orbit requirement, then carries out repetition measurement until meeting the requirements by step g..
In one embodiment of satellite rotary part Low-vacuum dynamic test method of the present invention, the high-precision slow-speed of revolution is dynamic
Balancing machine (2) have workpiece spin operating mode, i.e., dynamic balancing machine do not rotate, the mode of measured workpiece rotation.
The present invention is further illustrated below with reference to an application example:
Application example is tested using Low-vacuum dynamic test device, as shown in Figure 1, include low vacuum tank (1) and
High-precision slow-speed of revolution dynamic balancing machine (2).Wherein low vacuum tank (1) interior envelope is having a size of Φ 2600mm × 4000m, final vacuum
<5Pa.The specified carrying 300kg of high-precision slow-speed of revolution dynamic balancing machine (2), workpiece from rotary-die type remnants static-unbalance (Umar) <
0.8kg.mm, remaining couple-unbalance < 200kg.mm2.
Participation test products are certain satellite spin load, and major parameter is as follows:
Testing process is as follows: a. equipment adjustment → b. installation calibration tooling → c. precision calibration → d. installation test product →
E. movable part expansion → f. normal pressure state dynamic balancing measurement → g. low-pressure state dynamic balancing measurement.
A. equipment adjusts: by high-precision slow-speed of revolution dynamic balancing machine (2) bottom level regulating device by the high-precision slow-speed of revolution
Workpiece mounting surface (21) leveling of dynamic balancing machine (2) to two orthogonal direction levelness are better than 0.02mm/m.
B. tooling is demarcated in installation: will be demarcated motor (41) with pressing plate and screw and is fixed on high-precision slow-speed of revolution dynamic balancing machine
(2) in workpiece mounting surface (21).Calibration rotor (42) is connect with calibration motor (41) with screw, and it is excellent to adjust its concentricity
In 0.02m.The calibration rotor (42) each matches plane there are two plane, upper alignment surface (43) and lower alignment surface (44) is matched
There are 12 uniformly distributed calibration counterweight (45) mounting holes.
C. precision calibration: taking a calibration counterweight (45), 12 for demarcating counterweight and being sequentially arranged at upper alignment surface (43)
On mounting hole, in each position finding calibration motor (41) amount of unbalance at revolving speed 35.3rpm, as a result see the table below, it is quiet not
Aequum average value e1=8.09kg.mm, (e1-10Umar)/10Umar=1.1% < 12%.Calibration counterweight is sequentially arranged at
On 12 mounting holes of upper alignment surface (43), in imbalance of each position finding calibration motor (41) at revolving speed 35.3rpm
Amount, as a result see the table below, static-unbalance average value e2=8.09kg.mm, (e2-10Umar)/10Umar=1.1% < 12%.Mark
Fixed qualification.
Counterweight m=25g, upper alignment surface height ha=560mm are demarcated, lower alignment surface height Hb=300mm is upper and lower to calibrate
Radius surface ra=320mm,
D., test product is installed: above spin load (3) lifting to high-precision slow-speed of revolution dynamic balancing machine (2), being passed through
Cross the fastening of flange (33) mounting screw.
E. movable part is unfolded: movable part (32) being unlocked and be unfolded after spin load (3) is fixed.Starting spin
Motor (31) is simultaneously debugged, revolving speed 35.3rpm, and confirmation spin load (3) is working properly, closes spin motor (31).
F. normal pressure state dynamic balancing measurement: starting spin motor (31), measurement movable part at working speed 35.3rpm
(32) quiet, couple-unbalance close spin motor (32).Dynamic balancing measurement see the table below with counterweight situation:
G. low-pressure state dynamic balancing adjustment: the cover (11) of low vacuum tank (1) is covered, and after pedestal (12) sealing, is opened
Dynamic vacuum evacuation device makes vacuum degree in low vacuum tank (1) tank be reduced to 10Pa or less.Starting spin motor (31), measurement are working
Quiet, the couple-unbalance of movable part (32) under revolving speed r close spin motor (32).Dynamic balancing measurement is seen below with counterweight situation
Table:
Dynamic balancing adjustment is met the requirements, and test passes through.
Beneficial effects of the present invention are as follows:
1. base has been established in the application for dynamic balance running technology under space environment present invention can apply to whole star component test
Plinth provides technical support for the design of spacecraft structure loss of weight.
2. the present invention solves the flexible expansion movement load rotor of large size that meteorological satellite Microwave Imager is representative
The high-precision dynamic balancing Detection & Controling problem of assembly, it is ensured that remote sensing image quality.
3. it is also possible to apply the invention to the analyses of Flexible Satellite Attitude control system and design, solar battery array structure and machine
The fields such as the optimization design of structure.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
Professional further appreciates that, unit described in conjunction with the examples disclosed in the embodiments of the present disclosure
And algorithm steps, can be realized with electronic hardware, computer software, or a combination of the two, in order to clearly demonstrate hardware and
The interchangeability of software generally describes each exemplary composition and step according to function in the above description.These
Function is implemented in hardware or software actually, the specific application and design constraint depending on technical solution.Profession
Technical staff can use different methods to achieve the described function each specific application, but this realization is not answered
Think beyond the scope of this invention.
Obviously, those skilled in the art can carry out various modification and variations without departing from spirit of the invention to invention
And range.If in this way, these modifications and changes of the present invention belong to the claims in the present invention and its equivalent technologies range it
Interior, then the invention is also intended to include including these modification and variations.
Claims (9)
1. a kind of satellite rotary part Low-vacuum dynamic test method characterized by comprising
It carries out successively including that a. equipment is adjusted using low vacuum tank (1) and high-precision slow-speed of revolution dynamic balancing machine (2)；B. installation calibration
Tooling；C. precision calibration；D., test product is installed；E. movable part is unfolded；F. normal pressure state dynamic balancing measurement；G. low-pressure state
The test of dynamic balancing measurement.
2. satellite rotary part Low-vacuum dynamic test method as described in claim 1, which is characterized in that a. equipment
Adjustment, comprising:
By high-precision slow-speed of revolution dynamic balancing machine (2) bottom level regulating device, by the work of high-precision slow-speed of revolution dynamic balancing machine (2)
Part mounting surface (21) leveling to two orthogonal direction levelness are better than 0.02mm/m.
3. satellite rotary part Low-vacuum dynamic test method as claimed in claim 2, which is characterized in that the b. installation
Demarcate tooling, comprising:
The workpiece mounting surface that motor (41) are fixed on the high-precision slow-speed of revolution dynamic balancing machine (2) will be demarcated with pressing plate and screw
(21) on, calibration rotor (42) is connect with calibration motor (41) with screw, and adjust its concentricity better than 0.02m, wherein institute
The calibration rotor (42) stated each has 12 to be evenly distributed with there are two plane, upper alignment surface (43) and lower alignment surface (44) is matched with plane
Calibration counterweight (45) mounting hole.
4. satellite rotary part Low-vacuum dynamic test method as claimed in claim 3, which is characterized in that the c. precision
Calibration, comprising:
A calibration counterweight (45) is taken, the amount of unbalance of calibration counterweight (45) is 10Umar, wherein the Umar is high-precision
Spend slow-speed of revolution dynamic balancing machine (2) detectable minimum amount of unbalance under workpiece spin mode；
Calibration counterweight (45) is sequentially arranged on 12 mounting holes of the upper alignment surface (43), in each position finding
At load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42) obtain the calibration motor (41)
12 points of static-unbalance average value e1；
Calibration counterweight is sequentially arranged on 12 mounting holes of lower alignment surface (44), demarcates motor described in each position finding
(41) at load (3) the working speed r that spins, quiet, the couple-unbalance of the calibration rotor (42) obtain 12 points of quiet injustice
Measure average value e2；
As (e1-10Umar)/10Umar < ± 12% and (e2-10Umar)/10Umar < ± 12%, it is determined as qualification, otherwise
Dynamic balancing machine and calibration tooling need to be readjusted and repeat to demarcate until qualified；
Calibration motor (41), calibration rotor (42) and calibration counterweight (45) and its connector are removed after calibration.
5. satellite rotary part Low-vacuum dynamic test method as claimed in claim 4, which is characterized in that the d. installation
Test product, comprising:
Above the spin load (3) lifting to the high-precision slow-speed of revolution dynamic balancing machine (2), pacified by counter flange (33)
Cartridge screw fastening.
6. satellite rotary part Low-vacuum dynamic test method as claimed in claim 5, which is characterized in that the e. activity
Component expansion, comprising:
After the spin load (3) is fixed, movable part (32) are unlocked and are unfolded；Starting spin motor (31) is simultaneously adjusted
Examination checks whether spin load (3) work is normal, and the spin motor (31) is closed after debugging.
7. satellite rotary part Low-vacuum dynamic test method as claimed in claim 6, which is characterized in that the f. normal pressure
State dynamic balancing measurement, comprising:
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes certainly
It revolves motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), two are calculated
The counterweight azimuth angle theta 1 in a counterweight face, θ 2, and match weight m1, m2；
According to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, the second counterweight face
(35) 2 direction of azimuth angle theta, radius r2 Weight m2；
Starting spin motor (31), quiet, the couple-unbalance of repetition measurement movable part (32) at working speed r are such as unsatisfactory for
Rail job requirement then carries out repetition measurement until meeting the requirements by step f..
8. satellite rotary part Low-vacuum dynamic test method as claimed in claim 7, which is characterized in that the g. low pressure
State dynamic balancing adjustment, comprising:
The cover (11) of low vacuum tank (1) is covered, after pedestal (12) sealing, starting vacuum evacuation device makes low vacuum tank (1)
Vacuum degree is reduced to 5Pa or less in tank；
Start the spin motor (31), measure quiet, the couple-unbalance of the movable part (32) at working speed r, closes certainly
It revolves motor (32)；
According to parameter h1, r1 and h2, the r2 in the first counterweight face (34) of spin load (3) and the second counterweight face (35), two are calculated
The counterweight azimuth angle theta 1 in a counterweight face, θ 2, and match weight m1, m2；Low vacuum tank (1) is depressed into normal pressure state again, opens cover
(11), according to calculated result, in 1 direction of azimuth angle theta in the first counterweight face (34), radius r1 Weight m1, the second counterweight face
(35) 2 direction of azimuth angle theta, radius r2 Weight m2；
The cover (11) of low vacuum tank (1) is covered again, after pedestal (12) sealing, starting vacuum evacuation device makes low vacuum tank
(1) vacuum degree is reduced to installation test product hereinafter, repetition measurement the quiet of movable part (32), idol at working speed r is uneven in tank
It measures, is such as unsatisfactory for operation on orbit requirement, then carry out repetition measurement until meeting the requirements by step g..
9. satellite rotary part Low-vacuum dynamic test method as claimed in any one of claims 1 to 8, which is characterized in that
The high-precision slow-speed of revolution dynamic balancing machine (2) have workpiece spin operating mode, i.e., dynamic balancing machine do not rotate, measured workpiece from
The mode turned.
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| CN201810850150.XA CN109141751A (en) | 2018-07-28 | 2018-07-28 | Satellite rotary part Low-vacuum dynamic test method |
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| CN201810850150.XA CN109141751A (en) | 2018-07-28 | 2018-07-28 | Satellite rotary part Low-vacuum dynamic test method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112414618A (en) * | 2020-10-13 | 2021-02-26 | 深圳航天科技创新研究院 | Weight removal system for momentum wheel and weight removal method for momentum wheel |
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| CN102650560A (en) * | 2012-04-24 | 2012-08-29 | 上海卫星工程研究所 | Large-scale rotary load high-precision dynamic balance measuring device for spacecraft |
| CN103674428A (en) * | 2013-11-29 | 2014-03-26 | 上海卫星装备研究所 | Low-vacuum dynamic test device |
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| CN102650560A (en) * | 2012-04-24 | 2012-08-29 | 上海卫星工程研究所 | Large-scale rotary load high-precision dynamic balance measuring device for spacecraft |
| CN103674428A (en) * | 2013-11-29 | 2014-03-26 | 上海卫星装备研究所 | Low-vacuum dynamic test device |
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