CN109018455A - Spacecraft heat distortion test method - Google Patents
Spacecraft heat distortion test method Download PDFInfo
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- CN109018455A CN109018455A CN201810637276.9A CN201810637276A CN109018455A CN 109018455 A CN109018455 A CN 109018455A CN 201810637276 A CN201810637276 A CN 201810637276A CN 109018455 A CN109018455 A CN 109018455A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The present invention provides a kind of spacecraft heat distortion test method, includes the following steps: S1, on the basis of multi-boundary Condition thermal deformation analysis, and the in-orbit boundary condition of Simulated Spacecraft establishes spacecraft heat distortion test state；S2, different temperatures load is applied to spacecraft structure, obtains accurate temperature field and thermal change graphic data under typical test conditions, carries out the verifying of spacecraft structure thermal stability design rationality；S3, the amendment of thermal deformation simulation model is carried out by Comparability test data and emulation data, and then indicates in-orbit deformation.This invention ensures that test data is reliable, accurate, it can be designed for spacecraft structure thermal stability and design objective verifying provides foundation.
Description
Technical field
The present invention relates to spacecraft fields, and in particular to a kind of spacecraft heat distortion test method.
Background technique
In recent years, spatial resolution, temporal resolution and positioning accuracy of the high-resolution earth observation demand to spacecraft
Deng more stringent requirements are proposed.Spacecraft in orbit during, payload or platform caused by extreme rail temperature environment
One of an important factor for structure thermal deformation is influence spacecraft earth observation resolution ratio and positioning accuracy, it is necessary to spacecraft knot
Structure carries out THERMAL STABILITY and Control Thermal Deformation, to meet the growth requirement of high-resolution, high position precision.
Heat distortion test technology is the basis of spacecraft structure THERMAL STABILITY and in-orbit Deformation Prediction, is developed on ground
Stage needs reliable design, effective heat distortion test method to verify spacecraft structure thermostabilization design, by temperature
The accurate simulation of environment and the precise measurement of malformation are spent, realizes that spacecraft structure thermal deformation Modifying model and in-orbit deformation are pre-
Show, the on-orbit performance of spacecraft payload is assessed.
Summary of the invention
The present invention is directed to spacecraft structure thermostabilization research and Control Thermal Deformation demand, provides a kind of spacecraft structure heat
Deformation test method ensure that the reliable, accurate of test data, can be the design of spacecraft structure thermal stability and design objective
Verifying provides foundation.
Spacecraft heat distortion test method provided by the invention includes the following steps:
S1, on the basis of multi-boundary Condition thermal deformation analysis, the in-orbit boundary condition of Simulated Spacecraft establishes spacecraft thermal change
Shape trystate；In state of weightlessness and without restrained condition when the trystate is spacecraft operation on orbit；
S2, different temperatures load is applied to spacecraft structure, obtains accurately temperature field and thermal change under typical test conditions
Graphic data carries out the verifying of spacecraft structure thermal stability design rationality；
S3, the amendment of thermal deformation simulation model is carried out by Comparability test data and emulation data, and then indicates in-orbit deformation
Situation.
The spacecraft heat distortion test state is on the basis of multi-boundary Condition thermal deformation analysis, in ground experiment ring
The in-orbit boundary condition of Simulated Spacecraft under the conditions of border, and the feasibility and validity that guarantee test is implemented.
The typical test conditions are to consider spacecraft structure temperature gradient and thermal deformation sensible factor, to spacecraft
Structure applies different temperatures load, and obtains corresponding temperature field and thermal change graphic data.
The thermal deformation simulation model amendment is to consider structure lines expansion according to heat distortion test data and emulation data
Coefficient, rigidity, connection relationship and boundary condition etc. carry out the amendment of spacecraft structure thermal deformation model, and by spacecraft structure
Thermal deformation simulation model after the in-orbit Temperature Distribution Introduced Malaria of product main portions, the in-orbit deformation for obtaining infrastructure product are pre-
Show as a result, verifying the reasonability of spacecraft structure product thermal stability design.
Accurate temperature under typical test conditions is carried out by temperature control system and measuring system for thermal deformation in the step S2
The acquisition of field and thermal change graphic data, the temperature control system are made of temperature loading system and temperature measurement system；The thermal deformation measurement
System is made of deformation measuring system and data analysis process system；Deformation measuring system includes that angle measurement system and displacement are surveyed
Amount system, angle measurement system is directed toward variation for measuring star sensor, star sensor is directed toward with respect to other load and changes；Displacement
Measuring system is used to measure flatness/surface precision variation of payload under typical test conditions；Data Analysis Services system
For realizing data acquisition, storage, format conversion；Realize specified name, filtering, the matching fitting of test measurement data,
And corresponding thermal deformation index evaluation is completed according to test documentation technical requirements；Has the output of test data analyzer result, figure
Display function.
This invention ensures that test data is reliable, accurate, it can be designed for spacecraft structure thermal stability and design refers to
Mark verifying provides foundation.
Detailed description of the invention
Fig. 1 is whole star heat distortion test satellite and the rocket parting surface restrained condition schematic diagram in the embodiment of the present invention；
In figure: (a) vertical state, (b) horizontality.
Fig. 2 is subsystem grade and parts grade heat distortion test restrained condition schematic diagram in the embodiment of the present invention.
Fig. 3 is spacecraft of embodiment of the present invention heat distortion test flow diagram.
Fig. 4 is the schematic diagram of spacecraft of embodiment of the present invention heat distortion test method.
Specific embodiment
Elaborate below to implementation of the invention, implement specific steps based on the technical solution of the present invention under into
Row, provides detailed embodiment and specific operating process here.
As shown in figure 4, including the following steps: the embodiment of the invention provides a kind of spacecraft heat distortion test method
S1, establish spacecraft structure heat distortion test state, confirmation participate in the experiment Product Status and testing equipment, tooling it is mating
Deng.
After S2, trystate have, temperature control system power-off carries out base operation condition measurement, first to determine thermal deformation initial shape
State.
S3, temperature control system work carry out temperature field load to spacecraft structure according to target temperature.
After S4, equalized temperature (temperature point variation is no more than 0.5 DEG C/h), temperature is carried out using measuring system for thermal deformation
Working condition measurement is spent, the temperature field data and thermal deformation situation of spacecraft structure under representative temperature operating condition are obtained.
S5, it is transferred to base operation condition after rising again, carries out next round thermal deformation test.
S6, the state of product of participating in the experiment, test tool, measuring device should be checked after the test.
S7, experimental data processing convert test data to the technical indicator of correlation test technical requirements.
S8, thermal deformation Modifying model and in-orbit deformation indication, the reasonability of verifying infrastructure product thermal stability design.
1. trystate
In state of weightlessness and without restrained condition when spacecraft operation on orbit.To guarantee the validity of ground experiment and feasible
Property, the thermal deformation analysis of operation on orbit state and the thermal deformation analysis of a variety of boundary conditions need to be compared, confirm and establish
Spacecraft heat distortion test state.
(1) environmental condition
Under normal circumstances, relative humidity: 30%~60%；Cleanliness: it is not less than 100,000 grades, concrete foundation spacecraft structure
And loading demands；
(2) restrained condition
Whole star heat distortion test generally uses satellite and the rocket parting surface to constrain, and the state according to test load is different, can be used
Vertical state, can also be turned over by two-axis platcform makes antenna array normal direction and ground level, to adapt to heat when heat distortion test
Control is implemented and thermal deformation measurement, restrained condition schematic diagram are shown in Fig. 1.
Under normal circumstances, subsystem grade and parts grade heat distortion test select high rigidity, high stability rigid support, adopt
With the clamped mode simulating boundary restrained condition of load mounting surface；It, should be in vibration-isolating platform when product of participating in the experiment has high-acruracy survey demand
On establish trystate, restrained condition schematic diagram is shown in Fig. 2.
2. pilot system
(1) temperature control system
Temperature control system is made of temperature loading system and temperature measurement system.
When heat distortion test, external dimensions is larger, the simple celestial body plate of structure, payload antenna array etc. are generally adopted
Temperature load is carried out with infrared heater (infrared lamp arrays, infrared cage etc.)；Product smaller for size, complicated, or not
Easy-operating part, internal component etc., can according to temperature load require the flexible contact electric heater of design size into
Trip temperature load.
Temperature measurement system generally comprises thermocouple, thermistor, platinum resistance, thermal imaging system etc..Using sensitivity analysis
Method screens temperature point, determines thermometric, temperature control key point.The principle of layouting of temperature point is and thermal deformation analysis mould
The calculate node position of type is as corresponding as possible；It is as far as possible to layout in conditions permit more.
(2) measuring system for thermal deformation
Measuring system for thermal deformation is made of deformation measuring system and data analysis process system.
Deformation measuring system generally comprises angle measurement and displacement measurement.Angle measurement system is mainly used to measure star sensitivity
Device is directed toward variation, star sensor and is directed toward variation etc. with respect to other load, and measuring device includes electronic theodolite, photoelectric auto-collimator
Deng.Displacement measurement system is mainly used to measure flatness/surface precision variation of payload under typical test conditions, and measurement is set
Standby includes laser displacement gauge, photogrammetric instrumentation, projection moire measuring device, laser tracker etc..
Data Analysis Services system should be able to realize data acquisition, storage, format conversion；Test measurement data can be carried out
The pretreatments such as specified name, filtering, matching fitting；Corresponding thermal deformation can be completed according to test documentation technical requirements to refer to
Mark assessment；Have the functions such as the output of test data analyzer result, graphical display.
(3) test tool
To reduce influence of the tooling deformation to thermal deformation measurement precision, test tool is set using low coefficient of thermal expansion materials
Meter, and spacecraft structure product is heat-insulated, vibration isolation is installed；Test tool should take certain temperature control measures (cystosepiment, multilayer package
Deng), temperature point is set, and is monitored to test tool deformation.
2. test procedure
(1) operating condition of test is arranged
Heat distortion test obtain spacecraft structure under different temperatures load relative to fiducial temperature when thermal deformation variation
Amount, operating condition of test are made of base operation condition and representative temperature operating condition two major classes.Operating condition of test should include following content: infrastructure product
The load target temperature at each position；Thermal deformation measurement amount under operating condition of test, pendulous frequency；Points for attention etc. when specific implementation
Deng.
(2) experiment process
After detailed process is shown in that Fig. 3, trystate have, temperature control system power-off first carries out base operation condition measurement, to determine heat
Deformed initial state；Consideration spacecraft structure temperature gradient and thermal deformation sensible factor, setting relevant temperature operating condition, and according to
The target temperature of operating condition setting carries out temperature load to corresponding region spacecraft structure；Spacecraft structure corresponding region is loaded into mesh
Mark temperature, and according to the temperature variations of temperature point determine equalized temperature stablize after, carry out temperature case test, obtain allusion quotation
The temperature field data and thermal deformation situation of spacecraft structure under type temperature case；After thermal deformation measurement, institute on product, tooling
There is temperature point to rise again to fiducial temperature, after product of participating in the experiment, test tool etc. are risen again completely, can just be transferred to base operation condition, carries out
Next round thermal deformation test.The state of product of participating in the experiment, test tool, measuring device should be checked after the test, and right
All test results are confirmed and are evaluated.
(3) experimental data processing
Firstly, measuring systematic uncertainty evaluation and test validity evaluation, judge that test data is complete, reliable.
Secondly, being analyzed and processed to test data, valid data are obtained, and according to thermal deformation index analysis calculation method, such as: effectively
Load is directed toward angle, Eulerian angles variation, and flatness (RMS value), flatness (peak-to-peak value), relative deformation etc. will test number
According to the technical indicator for being converted into correlation test technical requirements.
(4) thermal deformation Modifying model and in-orbit deformation indication
Firstly, the key factor for influencing thermal deformation is determined by the sensitivity analysis influenced on each position of spacecraft structure,
Finite element amendment Optimized model is established, single goal nonlinear restriction planning problem is solved；According to heat distortion test data and emulation
Data consider structure linear expansion coefficient, rigidity, connection relationship and boundary condition etc., carry out the amendment of structure thermal deformation model, really
Determine the modified confidence level of thermal deformation simulation model.
Then, the in-orbit Temperature Distribution for listing spacecraft structure product main portions is emulated using revised thermal deformation
Model obtains the in-orbit deformation indication of infrastructure product as a result, the reasonability that verifying infrastructure product thermal stability designs.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (6)
1. a kind of spacecraft heat distortion test method, characterized by the following steps:
S1, on the basis of multi-boundary Condition thermal deformation analysis, the in-orbit boundary condition of Simulated Spacecraft, establish spacecraft thermal deformation examination
Test state；
S2, different temperatures load is applied to spacecraft structure, obtains accurate temperature field and thermal change figurate number under typical test conditions
According to progress spacecraft structure thermal stability design rationality verifying；
S3, the amendment of thermal deformation simulation model is carried out by Comparability test data and emulation data, and then indicates in-orbit deformation.
2. spacecraft heat distortion test method according to claim 1, it is characterised in that: the spacecraft thermal deformation examination
The state of testing is on the basis of multi-boundary Condition thermal deformation analysis, in the in-orbit boundary shape of ground experiment environmental condition Imitating spacecraft
State, and the feasibility and validity that guarantee test is implemented.
3. spacecraft heat distortion test method according to claim 1, it is characterised in that: the typical test conditions are
Consider spacecraft structure temperature gradient and thermal deformation sensible factor, different temperatures load is applied to spacecraft structure, and obtain
Corresponding temperature field and thermal change graphic data.
4. spacecraft heat distortion test method according to claim 1, it is characterised in that: the thermal deformation simulation model
Amendment is to consider structure linear expansion coefficient, rigidity, connection relationship and perimeter strip according to heat distortion test data and emulation data
Part carries out the amendment of spacecraft structure thermal deformation model, and the in-orbit Temperature Distribution of spacecraft structure product main portions is defeated
Enter revised thermal deformation simulation model, obtains the in-orbit deformation indication of infrastructure product as a result, verifying spacecraft structure product heat
The reasonability of stability Design.
5. spacecraft heat distortion test method according to claim 1, it is characterised in that: the trystate is spacecraft
In state of weightlessness and without restrained condition when operation on orbit.
6. spacecraft heat distortion test method according to claim 1, it is characterised in that: pass through temperature control in the step S2
System and measuring system for thermal deformation carry out the accurately acquisition of temperature field and thermal change graphic data, the temperature control system under typical test conditions
System is made of temperature loading system and temperature measurement system；The measuring system for thermal deformation is by deformation measuring system and data analysis
Reason system composition；Deformation measuring system includes angle measurement system and displacement measurement system, and angle measurement system is for measuring star
Sensor is directed toward variation, star sensor is directed toward with respect to other load and changes；Displacement measurement system is for measuring typical test conditions
The flatness of lower payload/surface precision variation；Data Analysis Services system is acquired for realizing data, is stored, format turns
It changes；It realizes specified name, filtering, the matching fitting of test measurement data, and completes phase according to test documentation technical requirements
The thermal deformation index evaluation answered；Has the output of test data analyzer result, graphical display function.
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Cited By (11)
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| CN110044319A (en) * | 2019-04-30 | 2019-07-23 | 北京航天发射技术研究所 | A kind of measurement method and measuring device of the deformation of Strapdown Inertial Navigation System damper |
| CN110654572A (en) * | 2019-11-01 | 2020-01-07 | 上海裕达实业有限公司 | Novel spacecraft vacuum thermal test measurement and control device and measurement and control method |
| CN111323210A (en) * | 2020-03-17 | 2020-06-23 | 北京控制工程研究所 | Device and method for testing optical axis thermal stability of optical lens |
| CN111929165A (en) * | 2020-08-25 | 2020-11-13 | 常州启赋安泰复合材料科技有限公司 | Method for checking hybrid connection strength of composite part and metal part |
| CN112629429A (en) * | 2020-12-04 | 2021-04-09 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| CN112668220A (en) * | 2020-12-23 | 2021-04-16 | 天津大学 | Method for measuring three-dimensional thermal deformation of aerospace device structure based on finite element analysis |
| CN112710699A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Test system and method for simulating thermal deformation of composite material rod piece in space environment |
| CN113901690A (en) * | 2021-10-13 | 2022-01-07 | 上海航天测控通信研究所 | Satellite-borne reflector antenna on-orbit thermal deformation performance evaluation method |
| CN114018170A (en) * | 2021-11-05 | 2022-02-08 | 中交一公局第七工程有限公司 | Prefabricated box girder monitoring method based on BIM |
| CN114492180A (en) * | 2022-01-17 | 2022-05-13 | 上海卫星工程研究所 | Remote sensing satellite on-orbit deformation prediction method and system |
| CN114818153A (en) * | 2022-07-01 | 2022-07-29 | 中国飞机强度研究所 | Test piece complex temperature field reconstruction method for aircraft component thermal test |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110044319A (en) * | 2019-04-30 | 2019-07-23 | 北京航天发射技术研究所 | A kind of measurement method and measuring device of the deformation of Strapdown Inertial Navigation System damper |
| CN110654572A (en) * | 2019-11-01 | 2020-01-07 | 上海裕达实业有限公司 | Novel spacecraft vacuum thermal test measurement and control device and measurement and control method |
| CN111323210A (en) * | 2020-03-17 | 2020-06-23 | 北京控制工程研究所 | Device and method for testing optical axis thermal stability of optical lens |
| CN111929165B (en) * | 2020-08-25 | 2021-06-08 | 常州启赋安泰复合材料科技有限公司 | Method for checking hybrid connection strength of composite part and metal part |
| CN111929165A (en) * | 2020-08-25 | 2020-11-13 | 常州启赋安泰复合材料科技有限公司 | Method for checking hybrid connection strength of composite part and metal part |
| CN112629429A (en) * | 2020-12-04 | 2021-04-09 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| CN112629429B (en) * | 2020-12-04 | 2023-02-07 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| CN112710699A (en) * | 2020-12-16 | 2021-04-27 | 中国科学院微小卫星创新研究院 | Test system and method for simulating thermal deformation of composite material rod piece in space environment |
| CN112668220A (en) * | 2020-12-23 | 2021-04-16 | 天津大学 | Method for measuring three-dimensional thermal deformation of aerospace device structure based on finite element analysis |
| CN113901690A (en) * | 2021-10-13 | 2022-01-07 | 上海航天测控通信研究所 | Satellite-borne reflector antenna on-orbit thermal deformation performance evaluation method |
| CN113901690B (en) * | 2021-10-13 | 2024-04-12 | 上海航天测控通信研究所 | On-orbit thermal deformation performance evaluation method for satellite-borne reflector antenna |
| CN114018170A (en) * | 2021-11-05 | 2022-02-08 | 中交一公局第七工程有限公司 | Prefabricated box girder monitoring method based on BIM |
| CN114492180A (en) * | 2022-01-17 | 2022-05-13 | 上海卫星工程研究所 | Remote sensing satellite on-orbit deformation prediction method and system |
| CN114818153A (en) * | 2022-07-01 | 2022-07-29 | 中国飞机强度研究所 | Test piece complex temperature field reconstruction method for aircraft component thermal test |
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Application publication date: 20181218 |