CN107860513A - The method for determining spacecraft mass characteristic - Google Patents
The method for determining spacecraft mass characteristic Download PDFInfo
- Publication number
- CN107860513A CN107860513A CN201711031544.4A CN201711031544A CN107860513A CN 107860513 A CN107860513 A CN 107860513A CN 201711031544 A CN201711031544 A CN 201711031544A CN 107860513 A CN107860513 A CN 107860513A
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- CN
- China
- Prior art keywords
- spacecraft
- mass
- threedimensional model
- mass property
- bay section
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Classifications
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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
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
- G01M1/125—Determining position of centre of gravity of aircraft
-
- 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
- G01M1/10—Determining the moment of inertia
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/30—Circuit design
- G06F30/36—Circuit design at the analogue level
- G06F30/367—Design verification, e.g. using simulation, simulation program with integrated circuit emphasis [SPICE], direct methods or relaxation methods
Abstract
The present invention relates to the method for determining spacecraft mass characteristic, comprise the following steps：Establish the threedimensional model of spacecraft bay section and equipment；The mass property initial value after spacecraft bay section and spacecraft loading station goods is calculated using threedimensional model；The actual measurement mass property of the spacecraft after above-mentioned spacecraft bay section and loading station goods is measured using matter measurement equipment；The mass property for measuring to obtain in 1.3 is compared with gained mass property initial value in 1.2, when comparative result exceeds preset range, corrects the threedimensional model, and return to 1.2；When comparative result is within preset range, into step 1.5；The mass property of spacecraft in a fully loaded state is calculated using the threedimensional model obtained in 1.4.The method according to the invention, the mass property of large-scale or ultra-large type spacecraft or satellite etc. is precisely determined using the method can of threedimensional model and part actual measurement.
Description
Technical field
The present invention relates to the determination method of spacecraft mass characteristic, more particularly to determine that the spacecraft for loading goods is (fully loaded
Under state) mass property determine method.
Background technology
Mass property is a kind of characteristic of spacecraft itself, is boat mainly including quality, centroid position and rotary inertia etc.
The basic parameter of its device kinetic model.
Cargo ship comes and goes Material Transportation platform as the space station world, has and loads big car loading and size itself and again
Measure the characteristics of big.Its length is more than 10 meters, and more than 3 meters, the weight of full load condition is more than diameter more than 13000kg, rotary inertia
28000kg.m2.Therefore, the measuring apparatus that size is sufficiently large, range is enough must be had by measuring the mass property of cargo ship, and
Existing measuring apparatus bearing capacity is less than 8 tons, and rotary inertia maximum range is less than 15000kg.m2, it is impossible to meet this kind of large-scale
Spacecraft mass characteristic test needs.
,, also will be to quilt in actual measurement process even if there is the measuring apparatus that size and range all meet requirement in practice
Survey thing and a series of operation such as lifted, transported, overturn, when thus needing the longer measurement of substantial amounts of human input, needs
Between, need corresponding measured object of transporting for long-distance.Especially large-scale satellite, Large Spacecraft etc., this measurement method are needed very
Long time of measuring and a large amount of inputs of financial resource and material resource manpower.
In practice, the mass property of object is also obtained using simulation means.But obtain accurate measurement result, it is desirable to
Simulation model is as small as possible with actual determinand error.But in space industry, when spacecraft is fully loaded with cargo, by being filled
Carry or the goods the reason for being distributed inside spacecraft transported and goods or equipment shape in itself, distribution of weight etc. are many
The influence of factor so that distribution of weight is complicated in fully loaded with cargo spacecraft, the accuracy of model need to test confirmation and
Amendment improves.In addition, with the continuous progress of space technology, because future space station, Large-scale satellite etc. are large-scale and super
The requirement of Large Spacecraft, to precisely determining that large-scale and super-large space capsule mass property proposes more harsh requirement.Cause
This, establishes and revision and analysis model and to reach specified accuracy be very important.
The content of the invention
It is an object of the invention to provide a kind of method of the accurate mass property for obtaining spacecraft.
To achieve the above object, the present invention provides the method for determining spacecraft mass characteristic, comprises the following steps：
1.1 establish the threedimensional model of spacecraft bay section and equipment；
1.2 calculate the mass property initial value after spacecraft bay section and spacecraft loading station goods using threedimensional model；
The actual measurement quality of 1.3 spacecrafts for measuring above-mentioned spacecraft bay section and loading station goods using matter measurement equipment is special
Property；
1.4 compare the mass property for measuring to obtain in 1.3 with gained mass property initial value in 1.2, are tied when comparing
When fruit exceeds preset range, the threedimensional model is corrected, and return to 1.2；When comparative result is within preset range, into step
Rapid 1.5；
1.5 utilize the threedimensional model obtained in 1.4 to calculate the mass property under spacecraft full load condition.
According to an aspect of the present invention, in step 1.1, the threedimensional model is established based on Pro/E.
According to an aspect of the present invention, in step 1.2, using described in the interface facility export developed based on Pro/E
The mass property initial value of the spacecraft of spacecraft bay section and loading station goods, form spacecraft bay section and loading station goods
Spacecraft mass property initial value summary sheet.
According to an aspect of the present invention, in step 1.3, the measuring apparatus is for measuring spacecraft bay section and dress
Carry the spacecraft weight of partial cargo and the barycenter platform of barycenter and for measuring spacecraft bay section and the contained goods of part spacecraft
Rotary inertia rocks platform.
According to an aspect of the present invention, the measuring apparatus is matter scaffold tower and rocks platform, and the maximum of the matter scaffold tower is held
Loading capability is less than 7 tons, and the maximum load-carrying capacity for rocking platform is less than 8 tons, and maximum range is less than 15000kg.m2。
According to an aspect of the present invention, in step 1.4, the mass property based on actual measurement, it is three-dimensional to correct the Pro/E
Model.
The method according to the invention, using existing barycenter platform and platform is rocked to spacecraft bay section and loading station goods
Spacecraft bay section carries out the actual measurement of mass property, draws the quality after accurate spacecraft bay section and its loading station goods
Characteristic information.Then, with thus obtained accurately mass property information, the threedimensional model established based on Pro/E is corrected.Utilize
This method, threedimensional model can be precisely corrected, make the mass property that is obtained based on threedimensional model very accurate.This method
Particularly with it is complex-shaped, be not easy to calculate spacecraft components or contained goods for be very effective.For this
The parts or goods of sample, using barycenter platform and rock platform and can obtain accurately mass property information, based on it is this accurately
Quality information, correct threedimensional model, can it is very simple, quickly and accurately correct threedimensional model, improve and calculated by threedimensional model
The precision of the data obtained.
The method according to the invention, first with simulation means ----especially with Pro/E, to spacecraft bay section and
Spacecraft bay section mass property parameter after loading station goods is calculated.Then using existing barycenter platform and rocking platform pair
Spacecraft bay section mass property after spacecraft bay section and loading station goods carries out actual measurement.It can so make full use of
Existing barycenter platform and rock platform, avoid using the huge barycenter platform of size and range and rock platform to complete spacecraft and its
All goods loaded measure.This will greatly reduce a series of operations such as lifting to nacelle, transport, upset, letter
The time required to changing measurement, efficiency is improved.Especially, using barycenter platform and rock that platform is relatively small to size, shape is relatively multiple
Miscellaneous spacecraft component and goods is surveyed, and is then corrected computation model with measured value, is dropped significantly in terms of size and range
The low requirement to rocking platform and barycenter platform, so as to avoid reorganization and expansion barycenter platform and rock platform, reduce development cost.
The method according to the invention, based on existing matter measurement equipment to spacecraft zero load bay section and its loading station goods after
Mass property carries out actual measurement, then according to measured data amendment Simulation Calculation, so as to improve the precision of computation model.
Thereafter, mass property calculation is carried out to the spacecraft of full load condition using thus obtained simulation model, you can obtain accurate
Mass property information or data.This method is being manufactured into for future space station, Large-scale satellite, super-large space capsule
Sheet, manufacturing time, the accuracy of manufacture etc. everyway are of great advantage.
Embodiment
According to one embodiment of the present invention, initially set up and load and/or transport for spacecraft bay section, by spacecraft
The Pro/E threedimensional models of the goods sent, for calculating and determining that the mass property after space flight bay section and its loading station goods is joined
Number.In this embodiment, selection is difficult to for complex-shaped, non-uniform mass or irregular, mass property as far as possible
The goods of calculating establishes Pro/E threedimensional models.In the present embodiment, now selected spacecraft bay section is empty bay section, is not had
Load any goods.With this, the mass property parameter of bay section in itself is determined.
According to the Pro/E threedimensional models established, the mass property after spacecraft bay section and its loading station goods is determined
Initial value, and the interface facility based on Pro/E exploitations is utilized by the quality after these spacecraft bay sections and its loading station goods
Characteristic initial value exports, after analyzing, arranging the data obtained and be aggregated into corresponding spacecraft bay section and its loading station goods
The mass property initial value summary sheet of (such as the equipment being loaded in spacecraft or equipment etc.).
In the present embodiment, the other parts of spacecraft can also be selected as the object for establishing threedimensional model, without
It is limited only to spacecraft loading bay section.
Platform is rocked to establishing the spacecraft bay section and its loading part of threedimensional model using existing 7 tons of barycenter platform and 8 tons
Mass property after distribution of goods thing carries out actual measurement, obtains corresponding accurately actual measurement mass property parameter.
When the longitudinal size of spacecraft in itself is larger, such as more than 10 meters；Maximum outside diameter is also relatively large, such as 3.4
During rice or so, the rotary inertia of fully loaded spacecraft is more than 28000kg.m2.If with an equipment to such fully loaded boat
Its device measure in the hope of obtain its accurately mass property parameter when, very high requirement will be proposed to equipment.
And in this case, according to the design of the present invention, entirely fully loaded spacecraft is broken the whole up into parts, divided and rule.
When using the method according to the invention, it is only necessary to a part of in whole spacecraft, the goods for loading or transporting to spacecraft
A part for thing carries out actual measurement, draws its mass property.In this way, substantially reduce the requirement to measuring apparatus.Meanwhile
Repeated multiple times handling, upset, transport etc. are carried out without counterweight and big object.
Thereafter, the actual gained quality characteristics data that measures is aggregated, forms actual measurement mass property summary sheet.Will actual measurement
Mass property parameter based on threedimensional model compared with calculating gained mass property.It is just right when comparative result is more than predictive error
Based on deviation size amendment threedimensional model.Then, using revised threedimensional model recalculate corresponding spacecraft bay section and
The mass property of goods.Acquired results will be calculated again compared with measured result.So repeatedly, constantly threedimensional model is corrected in check and correction,
Untill expected precision is reached.
So modification threedimensional model, in particular for labyrinth shape, the unequal thing for being not easy to calculate of Mass Distribution
Body is established and correction model, can make the model calculation progressively close to actual measured results.Thus, three-dimensional mould is improved
The precision of type.
When the result of calculation of the threedimensional model based on measured result amendment and the difference of measured result are less than predetermined value or divide
Cloth is when among predetermined value scope, it is meant that, gained model has met required precision.
Now, you can the object using above-mentioned gained threedimensional model to various sizes, shape and weight, it is especially fully loaded
, large-scale or super-large space capsule calculated, draw accurate mass property parameter.
Claims (6)
1. determine the method for spacecraft mass characteristic, it is characterised in that comprise the following steps：
1.1 establish the threedimensional model of spacecraft bay section and equipment；
1.2 calculate the mass property initial value after spacecraft bay section and spacecraft loading station goods using threedimensional model；
1.3 measure the actual measurement mass property of the spacecraft of above-mentioned spacecraft bay section and loading station goods using matter measurement equipment；
1.4 compare the mass property for measuring to obtain in 1.3 with gained mass property initial value in 1.2, when comparative result surpasses
When going out preset range, the threedimensional model is corrected, and return to 1.2；When comparative result is within preset range, into step
1.5；
1.5 utilize the threedimensional model obtained in 1.4 to calculate the mass property under spacecraft full load condition.
2. the method according to claim 1 for determining spacecraft mass characteristic, it is characterised in that in step 1.1, be based on
Pro/E establishes the threedimensional model.
3. the method according to claim 2 for determining spacecraft mass characteristic, it is characterised in that in step 1.2, utilize
The mass property for the spacecraft that interface facility based on Pro/E exploitations exports the spacecraft bay section and loading station goods is initial
Value, form the mass property initial value summary sheet of the spacecraft of spacecraft bay section and loading station goods.
4. the method according to claim 1 for determining spacecraft mass characteristic, it is characterised in that described in step 1.3
Measuring apparatus is for measuring the spacecraft weight of spacecraft bay section and loading station goods and the barycenter platform of barycenter and for surveying
The spacecraft rotary inertia of amount spacecraft bay section and loading station goods rocks platform.
5. the method according to claim 4 for determining spacecraft mass characteristic, it is characterised in that the measuring apparatus is matter
Scaffold tower is less than 7 tons with platform, the maximum load-carrying capacity of the matter scaffold tower is rocked, and the maximum load-carrying capacity for rocking platform is less than 8 tons,
Maximum range is less than 15000kg.m2。
6. the method according to claim 1 for determining spacecraft mass characteristic, it is characterised in that in step 1.4, be based on
Part mass characteristic measured result, corrects the threedimensional model.
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| CN201711031544.4A CN107860513A (en) | 2017-10-27 | 2017-10-27 | The method for determining spacecraft mass characteristic |
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| CN201711031544.4A CN107860513A (en) | 2017-10-27 | 2017-10-27 | The method for determining spacecraft mass characteristic |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116401793A (en) * | 2023-06-07 | 2023-07-07 | 济宁联威车轮制造有限公司 | Grinding tool three-dimensional model construction method based on grinding tool design |
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| CN103389183A (en) * | 2013-08-06 | 2013-11-13 | 北京卫星环境工程研究所 | Spacecraft quality characteristic comprehensive test board based on spherical air bearing |
| CN103136425B (en) * | 2013-02-26 | 2015-10-21 | 北京空间飞行器总体设计部 | A kind of spacecraft mass characteristic rapid analysis |
| CN106276155A (en) * | 2016-07-27 | 2017-01-04 | 赛摩电气股份有限公司 | A kind of Gravimetric Coal Feeders device and calibration steps thereof |
| CN106484929A (en) * | 2015-08-26 | 2017-03-08 | 上海宇航系统工程研究所 | A kind of moon exploration spacecraft multimode rotary inertia computational methods |
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2017
- 2017-10-27 CN CN201711031544.4A patent/CN107860513A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101655388A (en) * | 2009-09-18 | 2010-02-24 | 张德强 | On-line calibration primary-secondary belt balance and method |
| CN103033248A (en) * | 2012-10-29 | 2013-04-10 | 江苏鼎邦生物质能源机械有限公司 | Weight-equipped balance hopper |
| CN103136425B (en) * | 2013-02-26 | 2015-10-21 | 北京空间飞行器总体设计部 | A kind of spacecraft mass characteristic rapid analysis |
| CN103389183A (en) * | 2013-08-06 | 2013-11-13 | 北京卫星环境工程研究所 | Spacecraft quality characteristic comprehensive test board based on spherical air bearing |
| CN106484929A (en) * | 2015-08-26 | 2017-03-08 | 上海宇航系统工程研究所 | A kind of moon exploration spacecraft multimode rotary inertia computational methods |
| CN106276155A (en) * | 2016-07-27 | 2017-01-04 | 赛摩电气股份有限公司 | A kind of Gravimetric Coal Feeders device and calibration steps thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116401793A (en) * | 2023-06-07 | 2023-07-07 | 济宁联威车轮制造有限公司 | Grinding tool three-dimensional model construction method based on grinding tool design |
| CN116401793B (en) * | 2023-06-07 | 2023-08-22 | 济宁联威车轮制造有限公司 | Grinding tool three-dimensional model construction method based on grinding tool design |
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Application publication date: 20180330 |