CN108414257B - A kind of precision of equipment installation measurement method for spacecraft - Google Patents
A kind of precision of equipment installation measurement method for spacecraft Download PDFInfo
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- CN108414257B CN108414257B CN201810176025.5A CN201810176025A CN108414257B CN 108414257 B CN108414257 B CN 108414257B CN 201810176025 A CN201810176025 A CN 201810176025A CN 108414257 B CN108414257 B CN 108414257B
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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
- G01M99/00—Subject matter not provided for in other groups of this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
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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
- G01M13/00—Testing of machine parts
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Measuring Fluid Pressure (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to a kind of precision of equipment installation measurement methods for spacecraft, comprising: S1. is filled with gas into the cabin of spacecraft and the pressure in the cabin is kept to stablize；S2. in the state that the pressure in the cabin is stablized, first time precision measure is carried out to the installation site for the equipment being located in the cabin, obtains the first measurement result, after completing measurement, the gas in the cabin is discharged.The space pressure environment of spacecraft is imitated during ground survey, gas is filled in cabin, make to be maintained at a standard atmospheric pressure inside and outside the cabin of spacecraft, cabin to which spacecraft be effectively ensured and state consistency when real space flight, precision measure is carried out by the installation site for the equipment installed in vitro to spacecraft module, avoid because pressure environment factor difference caused by measurement accuracy deviation, guarantee cabin on installation accuracy of the equipment at ground and it is in-orbit when installation accuracy consistency.
Description
Technical field
The present invention relates to a kind of precision of equipment installation measurement methods more particularly to a kind of equipment for spacecraft to install essence
Spend measurement method.
Background technique
It in the in-orbit flight course of spacecraft, needs to complete inter-related task by multiple sensors, such as spacecrafts rendezvous, in-orbit
Maintenance etc..In order to ensure being precisely accomplished task, various sensors must satisfy installation accuracy requirement when spacecraft carries out general assembly,
This can be realized by ground general assembly accurate measurement, but the pressure environment and in-orbit ring inside and outside bay section are sealed during general assembly accurate measurement
Border is not identical, causes sealed compartment piece housing structure partial to deform, the installation accuracy of equipment is caused to change.Ground accurate measurement
When meet index request equipment installation accuracy, once be influenced by the above factor and have exceeded installation accuracy and refer to after entering the orbit
Target range, may cause serious consequence.
Summary of the invention
The purpose of the present invention is to provide a kind of precision of equipment installation measurement methods for spacecraft, solve spacecraft
In cabin the installation accuracy of equipment ground and it is in-orbit when inconsistent problem.
For achieving the above object, the present invention provides a kind of precision of equipment installation measurement method for spacecraft, packet
It includes:
S1. it is filled with gas into the cabin of spacecraft and the pressure in the cabin is kept to stablize；
S2. in the state that pressure in the cabin is stablized, to the installation site of the equipment being located in the cabin into
Row first time precision measure obtains the first measurement result, and after completing measurement, the gas in the cabin is discharged.
According to an aspect of the present invention, further includes:
S3. after the gas in the cabin drains, the cabin is stood with first time interval；
S4. second of precision measure is carried out to the installation site of the equipment in the cabin, obtains the second measurement result, than
Measurement result more twice obtains offset direction and the deviant of the installation site of the equipment on the outside of the cabin.
According to an aspect of the present invention, include: in step S1
S11. nitrogen oxygen atmosphere is filled with into the cabin；
S12. so that the pressure difference inside and outside the cabin is reached preset pressure and pressure stabilizing is carried out with the second time interval.
According to an aspect of the present invention, in step S12, the preset pressure is an atmospheric pressure；
Second time interval is greater than or equal to 6 hours.
According to an aspect of the present invention, in step S12, if the intracorporal pressure in the cabin is stablized, S2 is thened follow the steps, it is no
Then, tonifying Qi and bleed air operation are carried out to the cabin, and with third time interval standing, until the intracorporal pressure in the cabin is steady
Step S2 is executed after fixed.
According to an aspect of the present invention, the third time interval is greater than or equal to 20 minutes.
According to an aspect of the present invention, step S2 includes:
S21. in the state that the pressure in the cabin is stablized, the structure coordinate system of the cabin is established；
S22., accurate measurement prism square is installed in the cabin, and establishes the structure base of the cabin with the accurate measurement prism square
It is quasi-；
S23. first time precision measure is carried out with installation site of the structure benchmark to the equipment in the cabin, and
The installation site of equipment is adjusted；
S24. after completing measurement, the gas in the cabin is discharged.
According to an aspect of the present invention, in step S22, the structure that the position of accurate measurement prism square is installed in the cabin is rigid
Degree be greater than or equal to other positions the rigidity of structure.
According to an aspect of the present invention, right in every 24 hours during carrying out first time precision measure in step S2
Pressure difference inside and outside the cabin at least monitors once, and the pressure difference variation range in 24 hours inside and outside the cabin meet ±
1Kpa。
According to an aspect of the present invention, before being filled with gas into the cabin, by the cabin to presser sensor
Equipment Removal or change its working condition.
A kind of scheme according to the present invention imitates the space pressure environment of spacecraft, in cabin during ground survey
In be filled with gas, make to be maintained at a standard atmospheric pressure inside and outside the cabin of spacecraft, so that the cabin of spacecraft be effectively ensured
With state consistency when real space flight, carried out by installation site of the above-mentioned setting to the equipment that spacecraft module is installed in vitro
Precision measure avoids the deviation because of measurement accuracy caused by the difference of pressure environment factor, guarantees that equipment is on ground in cabin
Installation accuracy when face and it is in-orbit when installation accuracy consistency, so that spacecraft, which has been effectively ensured, executes accurately having for task
Effect.
A kind of scheme according to the present invention, the pressure difference inside and outside cabin by guaranteeing spacecraft carry out precision survey after stablizing
Amount further ensures equipment after ground survey result is entered the orbit with spacecraft to ensure that the effective and accurate of measurement result
Actual installation precision it is consistent.Cabin inside and outside differential pressure is monitored every 24 hours in measurement process, to ensure that
During ground test with when in-orbit actual flight state state it is consistent, further ensure ground survey result and spacecraft
The actual installation precision of equipment is consistent after entering the orbit.
A kind of scheme according to the present invention carries out second of precision measure after deflating by the cabin to spacecraft, and leads to
Measurement of comparison is crossed as a result, the intensity for respectively installing the mounting structure of equipment in the cabin of spacecraft can be found in time, thus according to
Comparing result, the mounting structure low to structural strength are accordingly reinforced, the installation of equipment after entering the orbit so as to avoid spacecraft
Precision is further ensured after ground survey result is entered the orbit with spacecraft and is set since mounting structure deformation leads to problem not up to standard
Standby actual installation precision it is consistent.
Detailed description of the invention
Fig. 1 schematically shows a kind of step block diagram of embodiment precision of equipment installation measurement method according to the present invention；
Fig. 2 schematically shows a kind of flow chart element of the precision of equipment installation measurement method of embodiment according to the present invention
Figure.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
As shown in Figure 1, a kind of embodiment according to the present invention, a kind of equipment for spacecraft of the invention installs essence
Spend measurement method, comprising:
S1. it is filled with gas into the cabin of spacecraft and the pressure in cabin is kept to stablize；
S2. in the state that the pressure in cabin is stablized, the installation site for the equipment being located in cabin is carried out for the first time
Precision measure obtains the first measurement result, and after completing measurement, the gas in cabin is discharged.
S3. after the gas in cabin drains, cabin is stood with first time interval；
S4. second of precision measure is carried out to the installation site of the equipment in cabin, obtains the second measurement result, compares two
Secondary measurement result obtains offset direction and the deviant of the installation site of the equipment on the outside of cabin.
A kind of embodiment according to the present invention, in step S1, comprising:
S11. nitrogen oxygen atmosphere is filled with into cabin；
S12. so that the pressure difference inside and outside cabin is reached preset pressure and pressure stabilizing is carried out with the second time interval.
In the present embodiment, precision of equipment installation measurement method of the invention is the spacecraft in imitative space pressure environment
It is carried out in accurate measurement environment.In the present embodiment, spacecraft is required to be parked on reliable bracket according to accurate measurement, bracket should have
Enough rigidity guarantees the stabilization of the spacecraft during accurate measurement.In order to imitate space environment, need when measuring and starting to boat
The cabin of its device is filled with gas, makes 2 standard atmospheric pressures of gas pressure intensity in spacecraft, and to navigate using ground installation
There are pressure differences with ambient enviroment in its device cabin, and pressure difference existing for the intracorporal pressure difference in cabin and extravehicular environment is made to reach default pressure
Difference, i.e. preset pressure in spacecraft outside the cabin of pressure and spacecraft are the pressure difference of an atmospheric pressure.In the present embodiment,
The gas being filled with into spacecraft is nitrogen oxygen atmosphere.
In the present embodiment, when the intracorporal inflation in cabin of completion spacecraft, and reach the cabin of spacecraft with the external world
To after preset pressure, spacecraft is made to carry out pressure stabilizing with the second time interval.And the second time interval is greater than or equal to 6 small
When.If the intracorporal pressure in the cabin of spacecraft is stablized, S2 is thened follow the steps, to the installation site of the equipment in the cabin of spacecraft
Carry out accurate measurement.If the intracorporal pressure in the cabin of spacecraft is unstable, need to carry out tonifying Qi to the cabin of spacecraft and the behaviour that deflates
Make, then spacecraft is stood with third time interval, recycle the above process, after the pressure in the cabin of spacecraft is stablized
Step S2 is executed, accurate measurement is carried out to the installation site of the equipment in the cabin of spacecraft.In the present embodiment, between the third time
Every more than or equal to 20 minutes.
A kind of embodiment according to the present invention, also needs before being inflated in the cabin to spacecraft in cabin
Pressure-sensitive equipment Removal changes to the working condition of pressure-sensitive equipment.
The embodiment of one kind according to the present invention, step S2 include:
S21. in the state that the pressure in cabin is stablized, the structure coordinate system of cabin is established；
S22., accurate measurement prism square is installed in cabin, and establishes the structure benchmark of cabin with accurate measurement prism square；In this implementation
In mode, in cabin install accurate measurement prism square position the rigidity of structure be greater than or equal to other positions the rigidity of structure, i.e.,
The position that the rigidity of structure is good in cabin is installed by prism square.Install the structure base for just establishing cabin after prism square with prism square
It is quasi-.
S23. first time precision measure is carried out to the installation site of the equipment in the cabin with structure benchmark, and to setting
Standby installation site is adjusted.In the present embodiment, essence is carried out by installation site of the measuring device to equipment in cabin
Degree measurement, while also needing to be adjusted the installation site of equipment, until meeting the requirements the installation accuracy of equipment.In this reality
It applies in mode, during the installation site to the equipment in cabin carries out precision measure, the cabin of spacecraft will keep only
It is vertical, avoid personnel or external object from touching cabin, to eliminate extraneous factor to the measurement result of the cabin of spacecraft
It influences, to ensure that the accurate of precision of equipment installation in cabin.
S24. after completing measurement, the gas in cabin is discharged.In the present embodiment, the peace to equipment in cabin is completed
It after the precision measure of holding position, deflates to cabin, the rate of deflation is controlled according to the design requirement of equipment in spacecraft
System, that is, the rate deflated cannot have an impact the equipment performance in cabin.It, will be in abovementioned steps after completing to the deflation of cabin
The equipment of dismounting installs back original position, or adjustment equipment working condition to original state.
A kind of embodiment according to the present invention, during carrying out first time precision measure, to cabin in every 24 hours
Inside and outside pressure difference at least monitors once, and the pressure difference variation range satisfaction ± 1Kpa 24 hours inside cabin inside and outsides.If cabin
The pressure difference of inside and outside is unsatisfactory for above-mentioned requirements, carries out in cabin after needing to carry out cabin to be readjusted to pressure stable state
The measurement of the installation site of equipment.
A kind of embodiment according to the present invention still ensures that space flight after completing step S3 to the discharge of gas in cabin
The cabin of device stands a period of time, i.e. first time interval.Step S4 is then executed, second of essence is carried out to the cabin of spacecraft
Degree measurement.It is consistent when the structure benchmark used during second precision measure is with first time precision measure, i.e. precision twice
Measurement process uses the same prism square.The process of second of precision measure and the process of first time precision measure are consistent,
And record the second measurement result.In the present embodiment, by the first measurement result of comparison and the second measurement result, to obtain
The offset direction of the installation site of equipment in cabin and deviant.If the offset direction and deviant that obtain do not meet space flight
The design requirement of the cabin of device is then reinforced for installing the mounting structure of equipment in the cabin of spacecraft.
According to the method for the present invention, the space pressure environment that spacecraft is imitated during ground survey, fills in cabin
Enter gas, make to be maintained at a standard atmospheric pressure inside and outside the cabin of spacecraft, so that the cabin and reality of spacecraft be effectively ensured
The state consistency when space flight of border carries out precision by installation site of the above-mentioned setting to the equipment that spacecraft module is installed in vitro
Measurement avoids the deviation because of measurement accuracy caused by the difference of pressure environment factor, guarantees that equipment is at ground in cabin
Installation accuracy and it is in-orbit when installation accuracy consistency, thus be effectively ensured spacecraft execute task it is accurate effectively.
According to the method for the present invention, the pressure difference inside and outside the cabin by guaranteeing spacecraft carries out precision measure after stablizing, from
And ensure that the effective and accurate of measurement result, further ensure the reality of equipment after ground survey result is entered the orbit with spacecraft
Installation accuracy it is consistent.Cabin inside and outside differential pressure is monitored every 24 hours in measurement process, to ensure that ground is surveyed
During examination with when in-orbit actual flight state state it is consistent, further ensure ground survey result and after spacecraft enters the orbit
The actual installation precision of equipment it is consistent.
According to the method for the present invention, carry out second of precision measure after deflating by cabin to spacecraft, and by pair
Than measurement result, the intensity that the mounting structure of equipment is respectively installed in the cabin of spacecraft can be found in time, thus according to comparison
As a result, the mounting structure low to structural strength is accordingly reinforced, the installation accuracy of equipment after entering the orbit so as to avoid spacecraft
Since mounting structure deformation leads to problem not up to standard, equipment after ground survey result is entered the orbit with spacecraft is further ensured
Actual installation precision it is consistent.
Above content is only enumerating for concrete scheme of the invention, for the equipment and structure of wherein not detailed description, is answered
When being interpreted as that the existing common apparatus in this field and universal method is taken to be practiced.
The foregoing is merely a schemes of the invention, are not intended to restrict the invention, for the technology of this field
For personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (9)
1. a kind of precision of equipment installation measurement method for spacecraft, comprising:
S1. it is filled with gas into the cabin of spacecraft and the pressure in the cabin is kept to stablize；
S2. in the state that pressure in the cabin is stablized, the is carried out to the installation site for the equipment being located in the cabin
Precision measure obtains the first measurement result, and after completing measurement, the gas in the cabin is discharged；
S3. after the gas in the cabin drains, the cabin is stood with first time interval；
S4. second of precision measure is carried out to the installation site of the equipment in the cabin, obtains the second measurement result, compares two
Secondary measurement result obtains offset direction and the deviant of the installation site of the equipment on the outside of the cabin.
2. precision of equipment installation measurement method according to claim 1, which is characterized in that include: in step S1
S11. nitrogen oxygen atmosphere is filled with into the cabin；
S12. so that the pressure difference inside and outside the cabin is reached preset pressure and pressure stabilizing is carried out with the second time interval.
3. precision of equipment installation measurement method according to claim 2, which is characterized in that in step S12, the default pressure
Difference is an atmospheric pressure；
Second time interval is greater than or equal to 6 hours.
4. precision of equipment installation measurement method according to claim 2 or 3, which is characterized in that in step S12, if described
The intracorporal pressure in cabin is stablized, and S2 is thened follow the steps, and otherwise, carries out tonifying Qi and bleed air operation to the cabin, and when with third
Between be spaced and stand, until the intracorporal pressure in the cabin executes step S2 after stablizing.
5. precision of equipment installation measurement method according to claim 4, which is characterized in that the third time interval is greater than
Or it is equal to 20 minutes.
6. precision of equipment installation measurement method according to one of claims 1 to 5, which is characterized in that step S2 includes:
S21. in the state that the pressure in the cabin is stablized, the structure coordinate system of the cabin is established；
S22., accurate measurement prism square is installed in the cabin, and establishes the structure benchmark of the cabin with the accurate measurement prism square；
S23. first time precision measure is carried out to the installation site of the equipment in the cabin with the structure benchmark, and to setting
Standby installation site is adjusted；
S24. after completing measurement, the gas in the cabin is discharged.
7. precision of equipment installation measurement method according to claim 6, which is characterized in that in step S22, in the cabin
Install accurate measurement prism square position the rigidity of structure be greater than or equal to other positions the rigidity of structure.
8. precision of equipment installation measurement method according to claim 6, which is characterized in that in step S2, carrying out first
The pressure difference inside and outside the cabin is at least monitored during secondary precision measure, in every 24 hours once, and the institute in 24 hours
State the pressure difference variation range satisfaction ± 1Kpa inside and outside cabin.
9. according to claim 1 to precision of equipment installation measurement method described in one of 3, which is characterized in that into the cabin
It is filled with before gas, to pressure-sensitive equipment Removal or its working condition will be changed in the cabin.
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| CN109307492B (en) * | 2018-12-11 | 2020-04-17 | 中国科学院沈阳自动化研究所 | Space station science experiment cabinet assembly size detects frock |
| CN111562124B (en) * | 2020-05-07 | 2022-08-09 | 上海宇航系统工程研究所 | Precision measuring method for storage tank flat-laying configuration spacecraft |
| CN113103016B (en) * | 2021-03-19 | 2022-08-16 | 上海航天精密机械研究所 | Automatic production line and production method suitable for cabin body processing |
| CN113804429B (en) * | 2021-10-28 | 2023-11-10 | 北京卫星环境工程研究所 | Method for compensating equipment precision of spacecraft sealed cabin in rail pressure difference environment cabin |
| CN114234836B (en) * | 2021-11-16 | 2023-12-19 | 北京卫星制造厂有限公司 | Method for assembling large complex sealed cabin structure of space station in part |
| CN117268675A (en) * | 2023-09-20 | 2023-12-22 | 北京理工大学 | Spacecraft equipment installation precision deviation compensation method |
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| CN104535281B (en) * | 2015-01-15 | 2015-10-14 | 中国石油大学(华东) | Machine level ground closed pipeline system safety testing device based on pressure correlation method carries out the method for testing |
| CN106586032B (en) * | 2016-11-14 | 2018-08-21 | 北京卫星环境工程研究所 | Spacecraft closes the method for adjustment of cabin status devices installation accuracy |
| CN106596277B (en) * | 2016-11-28 | 2020-06-30 | 上海大学 | High-flux membrane material mechanical testing device and method |
| CN107664605A (en) * | 2017-09-13 | 2018-02-06 | 莱茵技术-商检（宁波）有限公司 | A kind of detection device of lithium battery pack shell |
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