CN109214030B - Micro-nano satellite test matrix design method - Google Patents
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Abstract
The invention discloses a kind of micro-nano satellite test matrix design methods, this method first determines micro-nano satellite project characteristic and design characteristics element, reselection micro-nano satellite verification experimental verification strategy, then according to the subjects of micro-nano satellite, in conjunction with micro-nano satellite project characteristic and design characteristics element and whole-satellite experiment baseline, the test matrix of corresponding system grade and component level product is designed.Compared with prior art, method of the invention at most can effectively save test period, 80% or more funds of test for a micro-nano satellite.
Description
Technical field
The invention belongs to satellite engineering design fields, it particularly relates to which a kind of consider under a variety of constraint conditions
Micro-nano satellite test matrix design method.
Background technique
Micro-nano satellite be satellite and spacecraft technology of new generation development fast-developing in recent years important directions it
One, it is with a wide range of applications, has shown that good in fields such as earth observation, communication, new technology verifying, scientific experimentations
Technology, economy and military value.Micro-nano satellite refers to whole star quality between 100kg~1kg, using open architecture and
Standard interface specifications widely apply innovation design ideas and the technological development such as COTS device, industrial technology and microminaturization product
A kind of satellite.
Micro-nano satellite have functional density is high, intelligent, low in cost, the lead time is short, can mass production test etc.
Feature has maneuverability transmitting, group of stars autonomous operation, extensive equipment, group of stars synergistic application, can flexibly reconstruct and system is good for
Strong property waits more by force application advantages.As conventional satellite, micro-nano satellite will face complex environment and effect in life cycle management
Test, therefore also need to combine task feature and satellite technology state, targetedly carry out effective test.Tradition is defended
For the development of star, long-life and highly reliable requirement in order to ensure satellite, need to put into a large amount of funds and time, wherein
Including high test expense.If micro-nano satellite still uses conventional satellite test model, will be handed over its low cost and quickly
The target paid mismatches.
Test is to guarantee one of the important means of micro-nano satellite mission reliability.Several statistical data show (Gregory F
D,Jean F C,Joseph H S.Statistical reliability analysis of satellites by mass
Category:Does spacecraft size matter? [J] Acta Astronautica, 2010 (67): 584-595),
Micro-nano satellite has higher crash rate at initial stage of entering the orbit compared with large-scale/medium-sized satellite of tradition, and a big chunk reason is that
Verification experimental verification (i.e. last quality control) is not carried out, and the mission reliability of the verification experimental verification guarantee product of specification, system is lacked.
Although micro-nano satellite largely uses COTS product, but this does not imply that micro-nano satellite in-orbit life-span not can guarantee, in fact very
More micro-nano satellites but being capable of 5 years in orbit or longer time.The design or manufacturing defect of micro-nano satellite can before transmission
It is showed in the form of initial failure during verification experimental verification, therefore initial failure can effectively be prevented by verification experimental verification.
Once long-term in-orbit probability will be significantly greatly increased in the passing of satelline initial failure stage, utility COTS product is built micro-
Nano satellite meets mission requirements.
As the pioneer of global micro-nano satellite technical field, Sa Rui company has transmitted more than 40 satellites so far, closely
10 years Mission Success rates are 100%.By analysis Sa Rui development of company track it can be found why it can so succeed from not
Lasting technological innovation and the control of efficient quality are opened, including guaranteeing satellite reliability with the high-performance of COTS product；Actively open
Exhibit-trader's technology space ground validation ensures product quality by efficiently testing, examining；It is selected for key technology or product
Machine carries out (the Sweeting M.N.pushing the capabilities of small such as in-orbit flight test
satellites[R].Nano-satellite Symposium Nagoya,Japan,11October,2012)。
Test matrix design is overall one of the important process project of micro-nano satellite test.The development of micro-nano satellite is used and is opened
Formula architecture and standard interface specifications are put, COTS technology is widely applied, with low in cost, the lead time is short, can mass
The features such as production test, can be emitted, extensive equipment, Cheng Xingqun synergistic application with maneuverability.But higher enter the orbit initial stage
Crash rate limits giving full play to for micro-nano satellite application value.If reasonably design micro-nano satellite test matrix, is guaranteeing
The advantage also possessing low cost under the premise of micro-nano satellite mission reliability, quickly testing becomes and carries out micro-nano satellite test square
The a big difficulty of battle array design work.Test matrix once it is determined that, just determine whole systems that a micro-nano satellite must carry out
Irrespective of size, component level pilot project, corresponding bulk testing funds and period also substantially determine that importance is self-evident therewith.
Risk class, micro-nano satellite deployment way, micro-nano satellite radiation pattern, the micro-nano satellite for comprehensively considering micro-nano satellite receiving are general
Technical characterstic, micro-nano satellite contractor technical strength, environmental test and reliability test efficiency, test funds and period etc. are a variety of
Constraint condition, creativeness propose a kind of more restriction conditions under micro-nano test matrix design method, can be used for micro-nano satellite totality
Unit carries out the work of micro-nano experimental design, formulates bulk testing authentication policy, determines system-level, component level pilot project, formulates
Strategy etc. is cut out in test.
Summary of the invention
It is defended for this purpose, the present invention has comprehensively considered micro-nano satellite project receiving risk class, micro-nano satellite deployment way, micro-nano
Star radiation pattern, micro-nano satellite general technology feature, micro-nano satellite contractor technical strength, environmental test and reliability test are imitated
Can, test a variety of constraint conditions such as funds and period, propose micro-nano test matrix design method under a kind of more restriction conditions, give
Micro-nano satellite universal test matrix is used out, is suitably cut out in the experimental basis, and it is inexpensive, fast that micro-nano satellite may be implemented
The balance between satellite task reliability three is tested and ensured to speed.
In order to solve the above technical problems, The technical solution adopted by the invention is as follows:
Micro-nano satellite test matrix design method, comprising the following steps:
1) micro-nano satellite project characteristic and design characteristics element are determined
Determine the micro-nano project characteristic element of micro-nano satellite, micro-nano project characteristic element mainly include satellite mass/volume,
Track, project funds, delivery time, system update time are i.e. to the time of next-generation satellite launch, development square gauge mould, development side
Infrastructure, component procurement, manufacturing process and material, external coordination can power, test, emission security and risk control, defend
The safety of star disposition and risk, from being delivered to time of transmitting, radiation pattern, operation duration, the method for operation；
Determine that the micro-nano Project design characteirstic element of micro-nano satellite, Project design characteirstic element mainly include interface, design
Service life, Calculation of Reliability, satellite continue working ability, Mission Success requirement, Single Point of Faliure, failure slow down, from being emitted to operation
Time, parts information model, radiation scheme surplus, electronic component installation, number of parts, outlet limitation, contamination control, material choosing
It selects, the processing of debris mitigation, cable, power-supply control unit, solar battery array, battery, instruction and data, telemetry rate, task
Data transfer rate, antenna, expansion, structure, separating mechanism, separating switch, thermal characteristics, gesture stability, micro-vibration, pushes away wireless transmitter
Into, EMC；
2) micro-nano satellite verification experimental verification strategy is selected
According to micro-nano satellite type, micro-nano satellite verification experimental verification strategy is selected, micro-nano satellite type is single satellite, a system
Column satellite or a constellation satellite, for single satellite, Yao Jingli QT+AT (qualification test+acceptance test) or PFT (quasi- identification
Test)；For a series of satellites, the QT of some QT, especially component level will be skipped；For the satellite of the mutually same constellation,
First satellite will be by after QT, remaining satellite will just emit after only undergoing AT；
3) micro-nano satellite test matrix is designed
According to the subjects of micro-nano satellite, in conjunction with micro-nano satellite project characteristic and design characteristics element and test base
Line designs the test matrix of corresponding product；Wherein, subjects mainly include whole star and component level product.
Further, radiation pattern includes lift-launch or small rockets launch.
Further, gesture stability mode is active or passive mode.
Method of the invention, compared with prior art, a micro-nano satellite at most can effectively save test periods, test warp
Take 80% or more.
Detailed description of the invention
Fig. 1 is micro-nano satellite test matrix design flow diagram of the invention.
Fig. 2 is simplified homocentric sphere thermal model.
Fig. 3 is that normal pressure and true temp compare.
Fig. 4 is thermal vacuum and temperature difference caused by thermal cycle under different characteristic length.
Fig. 5 is to test caused temperature difference (300K) for two kinds under different shell radiuses.
Fig. 6 is that thermal vacuum and two kinds of test temperatures caused by thermal cycle are poor.
Fig. 7 is influence of the heat transfer to two kinds of test temperature differences.
Fig. 8 is influence of the characteristic length to two kinds of test temperature differences.
Fig. 9 is that characteristic dimension halves influence to two kinds of test temperature differences respectively.
Characteristic length compares the influence of two kinds of test temperature differences when Figure 10 is 300K.
Characteristic length compares the influence of two kinds of test temperature differences when Figure 11 is 273K.
Characteristic length compares the influence of two kinds of test temperature differences when Figure 12 is 253K.
Specific embodiment
A kind of 1 pair of micro-nano satellite test matrix design method of the invention is described in detail referring to the drawings, but should
It describes merely illustrative, it is no intended to which any restrictions are carried out to protection scope of the present invention.
1) micro-nano satellite project characteristic and the selection of design characteristics element
Present embodiment is in need of consideration micro- when carrying out micro-nano satellite verification experimental verification policy selection, pilot project selection
Project characteristic element of receiving mainly includes (arriving down satellite mass/volume, track, project funds, delivery time, system update time
The time of generation satellite launch), develop square gauge mould, the infrastructure of development side, component procurement, manufacturing process and material, external coordination
Can power, test, emission security and risk control, satellite disposition safety and risk, from be delivered to transmitting when
Between, radiation pattern (lift-launch), radiation pattern (special small rocket launching), operation duration, the method for operation etc. 18.
Carry out micro-nano satellite verification experimental verification policy selection, pilot project selection is that micro-nano Project design in need of consideration is special
Property element mainly include interface, projected life, Calculation of Reliability, satellite continue working ability, Mission Success requirement, single-point therefore
Barrier, failure slow down, from being emitted to time of operation, parts information model, radiation scheme surplus, electronic component installation, number of parts, out
Gas limitation, contamination control, material selection, debris mitigation, cable, power-supply control unit, solar battery array, battery, instruction sum number
According to processing, telemetry rate, task data rate, wireless transmitter, antenna, expansion, structure, separating mechanism, separating switch, Re Te
Property, gesture stability (actively or passively), micro-vibration, propulsion, EMC etc. 34.
2) verification experimental verification policy selection
The selection of verification experimental verification strategy is to carry out the first step of micro-nano satellite test matrix design.Micro-nano satellite test strategy
Depending on satellite project characteristic, such as single satellite, an a series of or constellation.Newly-designed single satellite is likely to require experience
QT+AT (qualification test+acceptance test) or PFT (quasi- qualification test).For a series of follow-on satellites of design, one will be skipped
The QT of a little QT, especially component level.For the constellation of same satellite, after first satellite is by QT, remaining satellite exists
Only will just it emit after experience AT.
For single satellite project, even if QT+AT strategy has been determined, since the uncertainty of quality management will cause AT mould
Type and QT model are not exactly the same.Even if positive sample has passed through AT, lost if increasing surplus identical with QT and also resulting in test
It loses.PFT has a margin advantage compared with positive sample is tested, this can also can bring other advantages, such as does not need to purchase compared to QT model
It buys hardware and reduces purchase cost, shorten test progress and reduce experimentation cost etc..It leaves however, PFT is but increased to positive sample
The potential degradation risk of product.If the items selection of single satellite only carries out AT, and such test strategy holds in order to reduce cost
The risk for ignoring design defect is easily led to, and these defects are then possible to more assembling level product testing or product development later period
In show.In short, cutting both ways for single satellite project in 3 kinds of strategies of table 1.That test strategy is chosen depending on micro-
Nano satellite project characteristic and design characteristics.
The pros and cons of the single satellite project test strategy of table 1 are analyzed
3) whole-satellite experiment matrix design
In view of the general technology feature of micro-nano satellite, micro-nano satellite subjects mainly include that whole star and component level produce
Product.The whole star test of micro-nano satellite is referred to the whole-satellite experiment baseline that table 2 provides, in conjunction with micro-nano satellite project characteristic and design
Specificity analysis can be designed that the test matrix of corresponding system-level (i.e. whole star) product.
2 whole-satellite experiment baseline of table
4) component level product testing matrix design
Satellite Experiment authentication policy (QT, PFT, AT) is selected according to table 1, refers again to the component level that table 3, table 4, table 5 provide
Qualification test, acceptance test and the quasi- qualification test baseline of product, can in conjunction with micro-nano satellite project characteristic and design characteristics analysis
To design the test matrix of all components grade product.
3 component level of table tests baseline (QT)
4 component level of table tests baseline (AT)
5 component of table and test baseline (PFT)
5) micro-nano satellite heat test items selection criterion
In micro-nano satellite test matrix, thermal vacuum test is test period longest, the highest pilot project of testing expenses.
By total funding, development time and guarantee the constraints such as Mission Success, when carrying out the design of micro-nano satellite test matrix, avoids as far as possible
Prolonged thermal vacuum test is carried out in thermal vacuum chamber as large satellite, in the case where meeting certain condition, thermal vacuum is tried
Testing with vacuum test+thermal cycling test+cold heat starting test substitution is a kind of new efficient solution route.
It is true by being carried out in the vacuum tank of a very little (there is no the satellites of 1:2 and container characteristics size than limiting)
The ability to work of empty function test (containing electric performance test) verifying system under vacuum, and verify the work energy of system at high temperature
Power.By thermal cycle (testing with hot circulation function two parts containing thermal cycle is durable), test screens out product early defect, and verifies
Working performance of the system under high and low temperature.Start starting ability of the verification experimental verification system under high/low temperature by cold heat.
By carrying out Temperature calculating analysis of the different characteristic scale micro-nano satellite product under vacuum and convection environment, give
Vacuum test+thermal cycling test+cold heat starting test substitution thermal vacuum test criterion is gone out can use: when product works
The heat flow density of period is no more than 50W/m2When, it can use vacuum test+thermal cycling test+cold heat starting test substitution heat
Otherwise vacuum test must carry out thermal vacuum test.
About criterion threshold value 50W/m2Foundation, analyzed as follows using concentric sphere volume model.
Usage criteria number mode carries out mould to the temperature during micro-nano satellite product thermal vacuum, thermal cycling test, hot-fluid
It is quasi-, in order to avoid product different surfaces Nu number is different, it is used herein concentric sphere volume model and compares and analyzes, with reference to Fig. 2:
Wherein internal structure represents single machine heat source, characteristic length 100mm, slin emissivity 0.9, and external structure represents large size
Mechanism outboard structure directly participates in exchanging heat in test, slin emissivity 0.9, it is assumed that its shell in thermal vacuum, thermal cycling test
Temperature is 300K, then according to thermal conduction study fundamental formular, in thermal vacuum test, and heat flow density are as follows:
In thermal cycling test, exchange heat heat flow density are as follows:
Wherein, Nu is nusselt number, are as follows:
Since Prandtl number Pr varies with temperature smaller, above formula can simplify are as follows:
Nu≈2+50(ΔT)1/4D3/4 (4)
I.e. for the timing of surfaces externally and internally temperature one, thermal vacuum, thermal cycling test heat flow density respectively indicate are as follows:
As seen in formula (6), when the parameters such as temperature, geometry uniquely determine, heat flow density is determined by internal case temperature,
When test specimen internal heat flows density to timing, can solve nonlinear equation obtain two states inner test piece temperature difference, as Fig. 3 be
Skin temperature is 300K, when outer radius 0.06 (characteristic length 0.12m), carries out internal heat resource when thermal cycle/thermal vacuum test
Temperature curve:
A) shell size influences
Curve, such as Fig. 4 are drawn when being respectively 0.06,0.1,0.25 to R2 by x-axis of heat flow density.
As seen in Figure 4, smaller for inner heat source heat flow density, structure gets over not compact structure, carries out thermal cycling test
When, internal temperature differs smaller with thermal vacuum test.
Drawing 0.06~0.5 waits 8 kinds of shell radiuses in 300K, and two kinds of internal temperature differences for testing may cause are bent
Line, as shown in Figure 5:
C) influence of internal emission rate
Above-mentioned all calculate is based on the case where micro-nano satellite internal emission rate is 0.9, can consider when emissivity reduces
Internal radiation heat exchange surface thermal resistance increases, and causes convection current percentage to increase, and then cause thermal vacuum, the thermal cycling test temperature difference
Become larger, difference curve when being characterized length 1.2m such as Fig. 6, when inner surface of outer cover emissivity is respectively 0.9,0.8,0.7.
As seen in Figure 6, as slin emissivity is lower, vacuum test, the temperature difference of normal pressure test will also become larger.
D) thermally conductive influence
Since stand-alone device is generally mounted in deck board, it may have it is thermally conductive, when consider equipment wherein one side (20% area)
When participating in thermally conductive, it is dry contact, thermal contact resistance 50w/m that it, which is arranged, with bulkhead2, then vacuum, normal pressure heat flow density respectively can be with tables
It is shown as:
In formula, j is contact heat transfer coefficient, draws curve and sees Fig. 7 (skin temperature 250K):
As shown in fig. 7, the temperature difference of vacuum, normal pressure test can be reduced since conduction exists.For under different characteristic scale
The influence of conduction, as shown in Figure 8:
As seen in Figure 8, conduction to system heat exchange be affected, when test specimen with shell directly contact dependence it is thermally conductive based on carry out
When heat dissipation, criterion threshold value described previously can be suitably decontroled.
E) inner casing size influences
Adjustment inner casing is 0.025m, when cover characteristics size is respectively 0.03m, 0.05m, 0.125m, i.e. inner casing and shell
The relationship of heat flow density and two kinds of test temperature differences is shown in Fig. 9 when characteristic size halves.
As shown in figure 9, causing internal heat transfer free convection space to halve, but its is right although inside and outside shell characteristic size halves
Heat transfer free convection influence is smaller, can ignore when estimating heat output.So the result of Fig. 9 and Fig. 4 is relatively.It therefore can
Consider R2/R1 as criterion numeral, it can existing result is applied to the product of other sizes.
F) characteristic length is than influencing
In the case where different characteristic length ratio (R2/R1), consider when not considering thermally conductive, draw thermal cycling test/heat
Vacuum test difference curve, wherein the temperature difference less than 10 DEG C when be designated as grey (i.e. can be used thermal cycling test substitution thermal vacuum test
Range).Curve, which is drawn, for different skin temperatures sees Figure 10-Figure 12 respectively.
For example, for the micro-nano satellite of 10 × 10 × 10cm, whole star quality about 1kg, 0.5~2W of whole star heat consumption or so, ginseng
Figure 12 is examined, to guarantee vacuum, atmospheric low-temperature test (- 40 DEG C) temperature difference at 10 DEG C or so, it is assumed that core heat consumption package surface product
For 150cm2It controls (5 × 5 × 10cm) and only relies on radiation heat transfer, then the maximum heat consumption allowed is 0.6W, corresponding maximum hot-fluid
Density is 40W/m2；If on the contrary contact with wall surface using heat loss through conduction, allow maximum heat consumption up to 4.5W, corresponding maximum hot-fluid
Density is 300W/m2。
In conclusion heat flow density is in 50W/m2Within, considering a variety of shell sizes, internal emission rate, thermally conductive, inner casing
In the case where size, characteristic length ratio, skin temperature, the temperature difference of thermal vacuum test and thermal cycling test can control substantially
Within 10 DEG C.Therefore, 50W/m2It can be used as criterion threshold value.
The beneficial effect of present embodiment is described as follows: it is provided in test baseline in table 2, table 3, table 4, table 5, it is nearly all
Environmental suitability test is that choosing is done (except the random vibration test in acceptance test), it is generally the case that all kinds of environment of satellite
Adaptability accounts for the largest percentage in entire test funds, test period.At the same time, device, material, portion are reduced to greatest extent
Part, component and system-level upper repeat pilot project, compression assembly grade product testing project, to pilot project to system-level, first device
Part/material grade transfer.Different micro-nano satellite research institutes can rationally set according to self-technique strength, product technology feature etc.
The test matrix of specific micro-nano satellite is counted, thus effectively save test test and test funds.Under optimal cases, a micro-nano is defended
Star can effectively save test period, 80% or more funds of test.System-level and must doing experiment for component level product is concentrated mainly on
Interface, functional performance proving test, these pilot projects are extremely critical for guaranteeing Mission Success.These pilot projects are set
Project must be done by being set to, extremely important to guarantee micro-nano satellite mission reliability.The test base provided using table 2, table 3, table 4, table 5
Line, it is ensured that the reasonability of micro-nano satellite test matrix design.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (3)
1. micro-nano satellite test matrix design method, comprising the following steps:
1) micro-nano satellite project characteristic and design characteristics element are determined
Determine that the micro-nano project characteristic element of micro-nano satellite, micro-nano project characteristic element mainly include satellite mass/volume, rail
Road, project funds, delivery time, system update time be to next-generation satellite launch time, develop square gauge mould, development side
Infrastructure, component procurement, manufacturing process and material, external coordination can power, test, emission security and risk control, satellite
The safety of disposition and risk, from time, radiation pattern, operation duration and the method for operation for being delivered to transmitting；
Determine the micro-nano Project design characteirstic element of micro-nano satellite, Project design characteirstic element mainly include interface, projected life,
Calculation of Reliability, satellite continue working ability, Mission Success requirement, Single Point of Faliure, failure slow down, from be emitted to operation when
Between, parts information model, radiation scheme surplus, electronic component installation, number of parts, outlet limitation, contamination control, material selection, it is broken
Piece slows down, cable, power-supply control unit, solar battery array, battery, instruction and data are handled, telemetry rate, task data
Rate, wireless transmitter, antenna, expansion, structure, separating mechanism, thermal characteristics, gesture stability, micro-vibration, propulsion and EMC；
2) micro-nano satellite verification experimental verification strategy is selected
According to micro-nano satellite type, micro-nano satellite verification experimental verification strategy is selected, micro-nano satellite type is single satellite, a series of defends
Star or a constellation satellite, for single satellite, Yao Jingli QT+AT(qualification test+acceptance test) or the identification examination of PFT(quasi-
It tests)；For a series of satellites, some QT will be skipped；For the satellite of the mutually same constellation, first satellite by QT it
Afterwards, remaining satellite will just emit after only undergoing AT；
3) micro-nano satellite test matrix is designed
According to the subjects of micro-nano satellite, in conjunction with micro-nano satellite project characteristic and design characteristics element and test baseline, if
Count out the test matrix of corresponding product；Wherein, subjects mainly include whole star and component level product.
2. the method for claim 1, wherein radiation pattern includes lift-launch or small rockets launch.
3. the method for claim 1, wherein gesture stability mode is active or passive mode.
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| CN109214030A (en) | 2019-01-15 |
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