CN109141472A - For assessing the sight star test device and method of star sensor thermal stability - Google Patents
For assessing the sight star test device and method of star sensor thermal stability Download PDFInfo
- Publication number
- CN109141472A CN109141472A CN201810916247.6A CN201810916247A CN109141472A CN 109141472 A CN109141472 A CN 109141472A CN 201810916247 A CN201810916247 A CN 201810916247A CN 109141472 A CN109141472 A CN 109141472A
- Authority
- CN
- China
- Prior art keywords
- star sensor
- star
- thermal stability
- temperature
- mounting surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
- Radiation Pyrometers (AREA)
Abstract
The present invention relates to it is a kind of assess star sensor thermal stability sight star test device, include: integrated bracket, axially symmetric structure, thereon multiple mounting surfaces two-by-two between normal angle it is equal, identical star sensor is correspondingly arranged on each mounting surface；Precise temperature control instrument includes electric heating sheets and thermistor, is pasted onto the lateral surface and bottom surface mounting surface of each star sensor hood, carries out temperature acquisition and closed-loop control；Windproof protective cover is located at the outside for being equipped with the integrated bracket of multiple star sensors, and is mounted on outfield and sees on satellite experiment platform；Industrial personal computer is tested, is arranged with integrated bracket interval, passes through cable connection with each star sensor.The present invention also provides a kind of sight star test methods for assessing star sensor thermal stability.The present invention provides the quantitative estimation method of accurately and effectively star sensor thermal stability using the consistent feature of the thermal stability property of identical star sensor by technological means such as total reference for installation, active temperature control, heat-insulated radix saposhnikoviaes.
Description
Technical field
The present invention relates to a kind of device and method for assessing star sensor thermal stability, in particular to one kind for assessing star
The sight star test device and method of sensor thermal stability belong to the ground experiment technical field of space photoelectric sensor.
Background technique
Star sensor is a kind of high-precision spacecraft attitude measurement single machine, is detection target with fixed star, through interior lights
System, electronic packages and software processing, export three-axis attitude information.Due to the shadow by Orbital heat flux and deep cooling space background
It rings, the fluctuation of orbital period is generally presented in the temperature field of star sensor, and because thermal deformation generates the low frequency aberration of orbital period.One
As using the mounting surface temperature of star sensor as reference temperature, to measure temperature with the variable quantity of mounting surface temperature, it is quick to assess star
The thermal stability of sensor.Simultaneously, it is contemplated that the temperature fluctuation range of star sensor hood is larger, also needs in addition to examine star sensitive
The thermal stability of device is influenced situation by hood temperature.
In the prior art, it to the research of star sensor thermal stability, lays particular emphasis on from temperature control, that is, uses a series of thermal controls
Means realize the inhibition of thermal deformation to reduce the fluctuation range of temperature.But thermal stability is directly assessed
Study the thermal stability measuring system less, the country also there is no maturation to apply at present.
Currently, can be there are two types of thermal stability evaluation methods for reference: one is by other optical gauges, such as from
Collimator, prism square etc. measure the deformation of the structure under varying temperature environment.The disadvantages of the method are as follows the deformation of structure is not
It can be equivalent with the variation of the measurement result of optical gauge.Another kind is using the in-orbit data of star sensor, to the orbital period
Interior low frequency aberration is analyzed, but in the process, it still can not remove satellite platform stability and other mounting structures
The influence of thermal deformation.Therefore, both the above method directly can not effectively assess the thermal stability of star sensor.
Based on above-mentioned, the present invention proposes a kind of sight star test device and method for assessing star sensor thermal stability, thus
Solve disadvantage existing in the prior art and limitation.
Summary of the invention
The object of the present invention is to provide a kind of for assessing the sight star test device and method of star sensor thermal stability, leads to
The technological means such as reference for installation, active temperature control, heat-insulated radix saposhnikoviae altogether are crossed, the consistent spy of the thermal stability property of identical star sensor is utilized
Point provides a kind of method of accurately and effectively star sensor thermal stability quantitative evaluation.
To achieve the above object, the present invention provides a kind of for assessing the sight star test device of star sensor thermal stability,
Include: integrated bracket is axially symmetric structure, is provided with multiple mounting surfaces, and the normal angle of mounting surface between any two
It is equal, multiple identical star sensors are correspondingly arranged on each mounting surface；Precise temperature control instrument includes multiple electric heating sheets and more
A thermistor pastes the lateral surface and bottom surface mounting surface that the hood of each star sensor is arranged in, and carries out to star sensor
Temperature acquisition and closed-loop control；Windproof protective cover is located at the outside for being equipped with the integrated bracket of multiple star sensors, and pacifies
It is seen on satellite experiment platform mounted in outfield；Industrial personal computer is tested, is set with the integrated bracket spacing distance for being equipped with multiple star sensors
It sets, and passes through cable connection with each star sensor.
Preferably, the normal angle of the mounting surface on the integrated bracket between any two is 0~60 °.
Preferably, the integrated bracket is made of invar, and linear expansion coefficient is less than 1 × 10-7/℃。
Preferably, preformed groove is provided on each mounting surface on the integrated bracket.
Preferably, the precise temperature control instrument also includes: temperature controller host, with the integral type for being equipped with multiple star sensors
Spacer support frame distance setting；Multiple electric heating sheets are respectively adhered on lateral surface and the bottom of the hood of each star sensor
Face mounting surface, each electric heating sheets pass through cable connection with temperature controller host；Multiple thermistors are pasted respectively to be set
The lateral surface and bottom surface mounting surface in the hood of each star sensor are set, and is located at the side of each electric heating sheets, each
Thermistor passes through cable connection with temperature controller host.
Preferably, the electric heating sheets being pasted on the lateral surface of the hood of each star sensor, bonding area do not surpass
Cross the 1/2 of circumferential area；Also, on the lateral surface of hood of the electric heating sheets and thermistor in each star sensor
The resistance value deviations of the identical and co-located each electric heating sheets of paste position be not more than 1%.
Preferably, by the way that the electric heating sheets being pasted on the mounting surface of each star sensor bottom surface are correspondingly arranged at integral type
In the preformed groove of bracket, each star sensor is correspondingly arranged on each mounting surface of integrated bracket.
Preferably, it on the lateral surface of the hood for each star sensor for being pasted with multiple electric heating sheets, is respectively coated by
Heat-insulated multilayer module is set.
The windproof protective cover is made of transparent organic glass；The top surface of the radix saposhnikoviae protective cover is according to star sensor
Visual field size is preset with observation hole.
The present invention also provides a kind of for assessing the sight star test method of star sensor thermal stability, using above-mentioned sight star
Test device realization, comprising the following steps:
After S1, sight star test device and star sensor to be measured are installed, star sensor is powered on until entering tenacious tracking
State exports attitude quaternion data based on true starry sky；
S2, be arranged star sensor bottom surface mounting surface first object temperature；
S3, after reaching first object temperature by the temperature of each star sensor of precise temperature control instrument closed-loop control and stablize,
The attitude quaternion data that industrial personal computer acquisition is no less than each star sensor output of 10min are tested, and it is sensitive to calculate star two-by-two
Optical axis between device is directed toward angle；
The second target temperature of the bottom surface mounting surface of star sensor is arranged in S4, adjustment, repeats S3, is directed toward with optical axis
The ratio of the temperature variation of angle variable quantity and bottom surface mounting surface, assesses the thermal stability of star sensor；
S5, keep star sensor bottom surface mounting surface the second target temperature, the difference of the hood of star sensor is set
Target temperature reaches the target temperature of corresponding hood and steady by the temperature of each star sensor of precise temperature control instrument closed-loop control
After fixed, test industrial personal computer acquisition is no less than the attitude quaternion data of each star sensor output of 10min, and calculates corresponding mesh
Optical axis between star sensor two-by-two at a temperature of mark is directed toward angle；The temperature of the angle variable quantity and hood that are directed toward with optical axis
The ratio of variable quantity assesses influence of the hood temperature change to the thermal stability of star sensor.
In conclusion it is provided by the present invention for assessing the sight star test device and method of star sensor thermal stability,
By the design of integrated bracket (low-grade fever deformation and altogether reference for installation), heat-insulated multilayer module, windproof protective cover, so that environment
The influence of temperature, wind load to measurement result is negligible；Each increment thermal stability property one of identical star sensor is utilized simultaneously
The characteristics of cause, is directed toward angle with the change of temperature in conjunction with optical axis by precise temperature control instrument to each star sensor active closed-loop temperature control
Change relationship, to accurately and effectively assess the thermal stability of star sensor.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the sight star test device for assessing star sensor thermal stability in the present invention；
Fig. 2 a and Fig. 2 b are the paste position schematic diagram of the electric heating sheets and thermistor in the present invention；
Fig. 3 is the structural schematic diagram of the integrated bracket in the present invention.
Specific embodiment
Below in conjunction with FIG. 1 to FIG. 3, by preferred embodiment to technology contents of the invention, construction feature, reached purpose
And effect is described in detail.
As shown in Figure 1, including for provided by the present invention for the sight star test device for assessing star sensor thermal stability:
Integrated bracket 1 is axially symmetric structure, is provided with multiple mounting surfaces, and the normal angle of mounting surface between any two is equal,
Multiple identical star sensors 6 are correspondingly arranged on each mounting surface；Precise temperature control instrument 2 includes multiple electric heating sheets 21 and more
A thermistor 22, paste be arranged in each star sensor 6 hood lateral surface and bottom surface mounting surface, to star sensor into
Trip temperature acquisition and closed-loop control；Windproof protective cover 4 is located at the outer of the integrated bracket 1 for being equipped with multiple star sensors 6
Portion, and be mounted on outfield and see on satellite experiment platform；Industrial personal computer is tested, with the integrated bracket 1 for being equipped with multiple star sensors 6
Be spaced a distance setting, and passes through cable connection with each star sensor 6.
The normal angle of mounting surface between any two on the integrated bracket 1 is 0~60 °.
The integrated bracket 1 is made of invar, and linear expansion coefficient is less than 1 × 10-7/ DEG C, than star sensor
Low two orders of magnitude of mechanical-optical setup material, therefore influence of the thermal deformation to test result of the integrated bracket 1 can be ignored.
As shown in figure 3, preformed groove 11 is provided on each mounting surface on the integrated bracket 1, for avoiding light
Learn the electric heater and thermistor pasted on probe mounting surface.
In a preferred embodiment of the invention, 3 mounting surfaces, mounting surface are provided on the integrated bracket 1
Normal angle between any two is 60 °.Preformed groove 11 is provided on each mounting surface, it is identical to respectively correspond installation 3
Star sensor 6.
As shown in Figure 2 a and 2 b, the precise temperature control instrument 2 also includes: temperature controller host, multiple stars are quick with being equipped with
The integrated bracket 1 of sensor 6 is spaced a distance setting；Multiple electric heating sheets 21 use film-type electric heating sheets, point
Be not pasted onto the lateral surface and bottom surface mounting surface of the hood of each star sensor 6, each electric heating sheets 21 with temperature controller master
Machine passes through cable connection；Multiple thermistors 22 paste the outside that the hood of each star sensor 6 is arranged in respectively
Face and bottom surface mounting surface, and it is located at the side of each electric heating sheets 21, each thermistor 22 passes through with temperature controller host
Cable connection.
Wherein, the electric heating sheets 21 being pasted on the lateral surface of the hood of each star sensor 6, bonding area does not surpass
Cross the 1/2 of circumferential area；Also, the electric heating sheets 21 and thermistor 22 each star sensor 6 hood it is outer
The resistance value deviation of the identical and co-located each electric heating sheets 21 of paste position on side is not more than 1%.
In a preferred embodiment of the invention, as shown in Figure 2 a, in the lateral surface of the hood of each star sensor 6
On same position at, be respectively set 3 electric heating sheets 21, and the bonding area of each electric heating sheets is no more than circumferential area
1/2, and the resistance value deviation being located between each electric heating sheets 21 on different star sensors 6 at same position is not more than
1%.Meanwhile in the side of each electric heating sheets 21, one thermistor 22 of setting is also pasted.As shown in Figure 2 b, in each star
1 electric heating sheets 21 is set on the bottom surface mounting surface of sensor 6, and in the side of the electric heating sheets 21, also pastes setting one
Thermistor 22.
As shown in Figure 1, by the way that the electric heating sheets 21 being pasted on each 6 bottom surface mounting surface of star sensor are correspondingly arranged
In the preformed groove 11 of integrated bracket 1, each star sensor 6 is correspondingly arranged to each mounting surface of integrated bracket 1
On.
Further, it on the lateral surface of the hood for each star sensor 6 for being pasted with multiple electric heating sheets 21, wraps respectively
It covers and sets heat-insulated multilayer module 3, reduce the heat exchange with external environment.
The windproof protective cover 4 is made of transparent organic glass, is that cuboid is box-packed；The side of the radix saposhnikoviae protective cover 4
Face is preset with cable threading hole, connect each star sensor 6 can by cable with test industrial personal computer, and make each electric heating
Piece 21, thermistor 22 can be connect by cable with temperature controller host；Top surface is preset with according to the visual field size of star sensor 6
Hole is observed, is blocked to will not be generated to the visual field of star sensor 6.In the present invention, the windproof protective cover 4 of setting can be avoided outer
Influence of the wind load to star sensor heat stability testing under the environment of field.
In conclusion in the present invention, each star sensor 6 to be measured, integrated bracket 1, electric heating sheets 21, temperature-sensitive electricity
Resistance 22, heat-insulated multilayer module 3 and windproof protective cover 4 are arranged in outfield and see on star platform；But test industrial personal computer and temperature control
Instrument host is then to keep suitably distance to be arranged with these above-mentioned components, and pass through cable connection.
The present invention also provides a kind of for assessing the sight star test method of star sensor thermal stability, using above-mentioned sight star
Test device is realized, is drawn partially by the way that temperature of the precise temperature control instrument 2 to each star sensor 6 is synchronous, is based on optical axis included angle method, assessment
The thermal stability of star sensor 6, comprising the following steps:
S1, see after star test device and star sensor to be measured 6 be installed, star sensor 6 power on until enter stablize with
Track state exports attitude quaternion data based on true starry sky；
S2, be arranged star sensor 6 bottom surface mounting surface first object temperature；
S3, first object temperature and stabilization are reached by the temperature of each star sensor 6 of 2 closed-loop control of precise temperature control instrument
Afterwards, the acquisition of test industrial personal computer is no less than the attitude quaternion data that each star sensor 6 of 10min (minute) exports, and calculates
The optical axis between star sensor 6 is directed toward angle two-by-two；
The second target temperature of the bottom surface mounting surface of star sensor 6 is arranged in S4, adjustment, repeats S3, is directed toward with optical axis
Angle variable quantity and bottom surface mounting surface temperature variation ratio, assess star sensor 6 thermal stability；
S5, keep star sensor 6 bottom surface mounting surface the second target temperature, be arranged star sensor 6 hood not
Same target temperature reaches corresponding target temperature and stabilization by the temperature of each star sensor 6 of 2 closed-loop control of precise temperature control instrument
Afterwards, the acquisition of test industrial personal computer is no less than the attitude quaternion data that each star sensor 6 of 10min exports, and calculates corresponding mesh
Optical axis between star sensor two-by-two 6 at a temperature of mark is directed toward angle；The temperature of the angle variable quantity and hood that are directed toward with optical axis
The ratio of variable quantity is spent, influence of the hood temperature change to the thermal stability of star sensor 6 is assessed.
Below in conjunction with FIG. 1 to FIG. 3, by a specific embodiment, what the present invention will be described in detail is used to assess star sensor
The sight star test device and method of thermal stability.
S1, carry out see star test device and star sensor to be measured 6 installation, star sensor 6 power on until enter stablize with
Track state exports attitude quaternion data based on true starry sky.
Wherein, specific installation process are as follows: the thin-film electro heating sheet 21 of precise temperature control instrument 2 is pasted onto each star sensor
The lateral surface of same position on 6 hood, the area coverage of electric heating sheets 21 are not more than the 1/2 of circumferential area, and every
A thermistor 22 is pasted in the side of a electric heating sheets 21, coats heat-insulated multilayer module 3 in the outside of star sensor 6 later；
Electric heating sheets 21 and thermistor 22, electric heating sheets 21 and heat are pasted in the bottom surface mounting surface of each star sensor 6
The paste position of quick resistance 22 must not be beyond the region of the preformed groove 11 on integrated bracket 1；
3 increment A, the increment B and increment C of star sensor are corresponded into installation to integrated bracket 1, and are placed on outfield
See satellite experiment platform on, cover windproof protective cover 4, cable is pierced by through the cable threading hole of windproof 4 side of protective cover, respectively with
It is connected every the temperature controller host of a distance setting with test industrial personal computer.
S2, for 10 DEG C of environment temperature, be arranged star sensor 6 bottom surface mounting surface first object temperature be 15 DEG C.
S3, precise temperature control instrument 2 is opened, by controlling the heating of electric heating sheets 21, the temperature of each star sensor 6 of closed-loop control
Degree reaches 15 DEG C, is regarded as temperature less than 0.5 DEG C with the variation of each 22 temperature collections of thermistor in 1 hour and reaches stable,
It tests industrial personal computer acquisition and is no less than the attitude quaternion data that each star sensor 6 of 10min exports, and be based on attitude quaternion
The optical axis calculated between star sensor 6 two-by-two is directed toward angle.
Wherein, specific heating process are as follows: Current Temperatures are acquired by each thermistor 22 and are transmitted to temperature controller master
Machine, if target temperature has not yet been reached in Current Temperatures, temperature controller host, which continues to power to each electric heating sheets 21, to be heated,
Until after reaching target temperature, and then make temperature reach stable using same closed-loop control.
Wherein, the process that optical axis is directed toward angle is specifically calculated are as follows:
The quaternion algebra of each star sensor 6 is according to identical time reference is used, if testing period star sensor increment A's
The Quaternion Sequence of constant duration isThe four of the constant duration of star sensor increment B
First number sequence is classified asTime interval is the sampling period T of attitude measurement informationc.It is quick for star
Each time point t of sensor increment A and star sensor increment BiQuaternary numberWithIts optical axis vector vAAnd vBRespectively under
Formula indicates:
Therefore, the optical axis of star sensor increment A and star sensor increment B are directed toward angle and are shown below:
It further obtains: SAB={ (ti,αi), i=1,2 ..., N }, to acquire star sensor increment A and star sensor
The optical axis of increment B is directed toward the mean value of angle
According to above-mentioned, the optical axis that can similarly acquire star sensor increment A and star sensor increment C is directed toward the mean value of angleAnd the optical axis of star sensor increment B and star sensor increment C is directed toward the mean value of angle
The second target temperature that the bottom surface mounting surface of star sensor 6 is arranged in S4, adjustment is 25 DEG C, repeats the step of above-mentioned S3
Suddenly, that is, precise temperature control instrument 2 is opened, by controlling the heating of electric heating sheets 21, the temperature of each star sensor 6 of closed-loop control reaches
25 DEG C, temperature is regarded as less than 0.5 DEG C with the variation of each 22 temperature collections of thermistor in 1 hour and reaches stable, tests work
The acquisition of control machine is no less than the attitude quaternion data that each star sensor 6 of 10min exports, and calculates two based on attitude quaternion
Optical axis between two star sensors 6 is directed toward the mean value of angleWithThen, the angle variable quantity being directed toward with optical axis
With the ratio of the temperature variation of bottom surface mounting surface, the thermal stability TS of star sensor 6 is assessed:
Wherein, thermal stability TS refers to that unit temperature changes the angle variable quantity that caused optical axis is directed toward；In above-mentioned formula
Part before symbol "/" indicates to take the separate unit star sensor 6 obtained after mean value by the variable angle between star sensor two-by-two
Optical axis be directed toward variable quantity, unit is angle；25 DEG C -15 DEG C be target temperature variable quantity.
S5, the temperature for keeping the bottom surface mounting surface of star sensor 6 are 25 DEG C, and the difference of the hood of star sensor 6 is arranged
Target temperature assesses hood temperature change to the shadow of the thermal stability of star sensor 6 using the identical method of above-mentioned S3 and S4
It rings.Reach the target temperature and stabilization of corresponding hood by the temperature of each star sensor 6 of 2 closed-loop control of precise temperature control instrument
Afterwards, the acquisition of test industrial personal computer is no less than the attitude quaternion data that each star sensor 6 of 10min exports, and calculates corresponding mesh
Optical axis between star sensor two-by-two 6 at a temperature of mark is directed toward angle；The temperature of the angle variable quantity and hood that are directed toward with optical axis
The ratio of variable quantity is spent, influence of the hood temperature change to the thermal stability of star sensor 6 is assessed.
In conclusion it is provided by the present invention for assessing the sight star test device and method of star sensor thermal stability,
By the way that during star is seen in outfield, the temperature field of active control star sensor is steady using each increment heat of identical star sensor
Determine the almost the same feature of characteristic, using optical axis included angle method, can effectively assess the thermal stability of star sensor.
Compared with prior art, the present invention having the following advantages and beneficial effects:
1, it is set by integrated bracket (low-grade fever deformation and altogether reference for installation), heat-insulated multilayer module, windproof protective cover
Meter, so that the influence of environment temperature, wind load to measurement result is negligible；
2, the feature consistent using each increment thermal stability property of identical star sensor, it is quick to each star by precise temperature control instrument
Sensor active closed-loop temperature control is directed toward angle variation with temperature relationship in conjunction with optical axis, to accurately and effectively assess star sensor
Thermal stability.
It is discussed in detail although the contents of the present invention have passed through above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read above content, for of the invention
A variety of modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (10)
1. it is a kind of for assessing the sight star test device of star sensor thermal stability, characterized by comprising:
Integrated bracket is axially symmetric structure, is provided with multiple mounting surfaces, and the normal angle phase of mounting surface between any two
Deng being correspondingly arranged multiple identical star sensors on each mounting surface；
Precise temperature control instrument includes multiple electric heating sheets and multiple thermistors, pastes the hood that each star sensor is arranged in
Lateral surface and bottom surface mounting surface, temperature acquisition and closed-loop control are carried out to star sensor；
Windproof protective cover is located at the outside for being equipped with the integrated bracket of multiple star sensors, and is mounted on outfield and sees star examination
It tests on platform；
Test industrial personal computer, be equipped with multiple star sensors integrated bracket spacing distance be arranged, and with each star sensor
Pass through cable connection.
2. as described in claim 1 for assessing the sight star test device of star sensor thermal stability, which is characterized in that described
Integrated bracket on mounting surface normal angle between any two be 0~60 °.
3. as described in claim 1 for assessing the sight star test device of star sensor thermal stability, which is characterized in that described
Integrated bracket be made of invar, linear expansion coefficient is less than 1 × 10-7/℃。
4. as described in claim 1 for assessing the sight star test device of star sensor thermal stability, which is characterized in that described
Integrated bracket on each mounting surface on be provided with preformed groove.
5. as claimed in claim 4 for assessing the sight star test device of star sensor thermal stability, which is characterized in that described
Precise temperature control instrument also include: temperature controller host, be equipped with multiple star sensors integrated bracket spacing distance be arranged；
Multiple electric heating sheets are respectively adhered on the lateral surface and bottom surface mounting surface of the hood of each star sensor, each
Electric heating sheets pass through cable connection with temperature controller host；
Multiple thermistors paste the lateral surface and bottom surface mounting surface that the hood of each star sensor is arranged in respectively,
And it is located at the side of each electric heating sheets, each thermistor passes through cable connection with temperature controller host.
6. as claimed in claim 5 for assessing the sight star test device of star sensor thermal stability, which is characterized in that paste
Electric heating sheets on the lateral surface of the hood of each star sensor, bonding area are no more than the 1/2 of circumferential area；
The paste position of the electric heating sheets and thermistor on the lateral surface of the hood of each star sensor is identical, with
And the resistance value deviation of co-located each electric heating sheets is not more than 1%.
7. as claimed in claim 5 for assessing the sight star test device of star sensor thermal stability, which is characterized in that pass through
The electric heating sheets being pasted on the mounting surface of each star sensor bottom surface are correspondingly arranged in the preformed groove of integrated bracket, it will be each
A star sensor is correspondingly arranged on each mounting surface of integrated bracket.
8. as claimed in claim 5 for assessing the sight star test device of star sensor thermal stability, which is characterized in that viscous
On the lateral surface for posting the hood of each star sensor of multiple electric heating sheets, it is respectively coated by the heat-insulated multilayer module of setting.
9. as described in claim 1 for assessing the sight star test device of star sensor thermal stability, which is characterized in that described
Windproof protective cover be made of transparent organic glass；The top surface of the radix saposhnikoviae protective cover is according to the visual field size of star sensor, in advance
Equipped with observation hole.
10. it is a kind of for assessing the sight star test method of star sensor thermal stability, using any one of such as claim 1~9
The sight star test device is realized, which is characterized in that is comprised the steps of:
After S1, sight star test device and star sensor to be measured are installed, star sensor is powered on up to entering tenacious tracking state,
Attitude quaternion data are exported based on true starry sky；
S2, be arranged star sensor bottom surface mounting surface first object temperature；
S3, it after reaching first object temperature by the temperature of each star sensor of precise temperature control instrument closed-loop control and stablize, tests
Industrial personal computer acquisition be no less than 10min each star sensor output attitude quaternion data, and calculate two-by-two star sensor it
Between optical axis be directed toward angle；
The second target temperature of the bottom surface mounting surface of star sensor is arranged in S4, adjustment, repeats S3, the angle being directed toward with optical axis
The ratio of the temperature variation of variable quantity and bottom surface mounting surface, assesses the thermal stability of star sensor；
S5, keep star sensor bottom surface mounting surface the second target temperature, the different target of the hood of star sensor is set
Temperature reaches the target temperature and stabilization of corresponding hood by the temperature of each star sensor of precise temperature control instrument closed-loop control
Afterwards, test industrial personal computer acquisition is no less than the attitude quaternion data of each star sensor output of 10min, and calculates corresponding target
At a temperature of star sensor two-by-two between optical axis be directed toward angle；The temperature of the angle variable quantity and hood that are directed toward with optical axis becomes
The ratio of change amount assesses influence of the hood temperature change to the thermal stability of star sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810916247.6A CN109141472B (en) | 2018-08-13 | 2018-08-13 | Star observation testing device and method for evaluating thermal stability of star sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810916247.6A CN109141472B (en) | 2018-08-13 | 2018-08-13 | Star observation testing device and method for evaluating thermal stability of star sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109141472A true CN109141472A (en) | 2019-01-04 |
| CN109141472B CN109141472B (en) | 2020-08-28 |
Family
ID=64792662
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810916247.6A Active CN109141472B (en) | 2018-08-13 | 2018-08-13 | Star observation testing device and method for evaluating thermal stability of star sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109141472B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111323052A (en) * | 2020-03-20 | 2020-06-23 | 上海航天控制技术研究所 | Navigation sensor heat balance test device used in complex thermal environment |
| CN111649765A (en) * | 2020-06-18 | 2020-09-11 | 西安中科微星光电科技有限公司 | Thermal vacuum test device for star sensor performance test |
| CN111811540A (en) * | 2020-07-17 | 2020-10-23 | 上海航天控制技术研究所 | Star sensor optical axis thermal stability test system and method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102564419A (en) * | 2011-12-29 | 2012-07-11 | 北京控制工程研究所 | Probe assembly for star sensor |
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
| CN205168943U (en) * | 2015-11-27 | 2016-04-20 | 上海卫星工程研究所 | Orbit transfer vehicle star sensor temperature on low side is heat accuse device independently |
| CN105675323A (en) * | 2016-01-15 | 2016-06-15 | 北京空间飞行器总体设计部 | Method for ground test of heat stability of satellite structure |
| CN106679695A (en) * | 2017-01-10 | 2017-05-17 | 上海航天控制技术研究所 | Method for testing thermal deformation of focal plane based on star sensor |
| CN107560638A (en) * | 2017-09-05 | 2018-01-09 | 上海航天控制技术研究所 | A kind of acquisition methods of star sensor alternating temperature calibrating parameters |
| CN107807696A (en) * | 2017-09-22 | 2018-03-16 | 上海卫星工程研究所 | Star upper heater precision temperature control method |
-
2018
- 2018-08-13 CN CN201810916247.6A patent/CN109141472B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102564419A (en) * | 2011-12-29 | 2012-07-11 | 北京控制工程研究所 | Probe assembly for star sensor |
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
| CN205168943U (en) * | 2015-11-27 | 2016-04-20 | 上海卫星工程研究所 | Orbit transfer vehicle star sensor temperature on low side is heat accuse device independently |
| CN105675323A (en) * | 2016-01-15 | 2016-06-15 | 北京空间飞行器总体设计部 | Method for ground test of heat stability of satellite structure |
| CN106679695A (en) * | 2017-01-10 | 2017-05-17 | 上海航天控制技术研究所 | Method for testing thermal deformation of focal plane based on star sensor |
| CN107560638A (en) * | 2017-09-05 | 2018-01-09 | 上海航天控制技术研究所 | A kind of acquisition methods of star sensor alternating temperature calibrating parameters |
| CN107807696A (en) * | 2017-09-22 | 2018-03-16 | 上海卫星工程研究所 | Star upper heater precision temperature control method |
Non-Patent Citations (2)
| Title |
|---|
| 孙鹏等: "一体化星敏感器温度控制措施及试验验证", 《航天器工程》 * |
| 童叶龙等: "航天器精密控温技术研究现状", 《航天返回与遥感》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111323052A (en) * | 2020-03-20 | 2020-06-23 | 上海航天控制技术研究所 | Navigation sensor heat balance test device used in complex thermal environment |
| CN111649765A (en) * | 2020-06-18 | 2020-09-11 | 西安中科微星光电科技有限公司 | Thermal vacuum test device for star sensor performance test |
| CN111811540A (en) * | 2020-07-17 | 2020-10-23 | 上海航天控制技术研究所 | Star sensor optical axis thermal stability test system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109141472B (en) | 2020-08-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109141472A (en) | For assessing the sight star test device and method of star sensor thermal stability | |
| CN105675143B (en) | A kind of vacuum blackbody radiation source | |
| Tan et al. | Heat capacities and thermodynamic functions of p-chlorobenzoic acid | |
| CN102967623A (en) | Infrared lamp array heat-flow density calibration device and calibration method | |
| CN109000879A (en) | A kind of wind-tunnel balance temperature drift modification method | |
| CN106292771B (en) | A kind of star sensor temperature field measurement and control device and its method | |
| CN104006887A (en) | Object surface emissivity field calibration method | |
| CN106467174A (en) | Large Spacecraft mechanism normal pressure thermograde pilot system | |
| CN108120477B (en) | Hot wire wind speed and direction measuring system suitable for low-temperature and low-pressure environment | |
| CN108680284B (en) | Temperature calibration device and calibration method for fiber bragg grating temperature sensor in low-temperature environment | |
| CN109507229A (en) | Thin plate thin-film material heat conductivity measuring device and measurement method | |
| CN106197751A (en) | The thermometry in a kind of temperature field and device | |
| CN103868948A (en) | Method for correcting heat exchange power of heat conductivity tester through single-test piece guarded hot plate method | |
| Jovanovic et al. | Temperature measurement of photovoltaic modules using non-contact infrared system | |
| CN104215659A (en) | Infrared lamp single-lamp radiation characteristic test system under vacuum thermal environment | |
| CN107271076B (en) | Distributed fiber optic temperature automatic calibration system and method are used under high vacuum thermal environment | |
| CN106546440B (en) | A kind of test method of verification heat control system performance suitable for Gravity Satellite | |
| Hagart-Alexander | Temperature measurement | |
| CN108168857A (en) | Temprature control method in a kind of canopy fatigue test | |
| Diller et al. | Heat flux measurement | |
| CN116242878A (en) | Integrated test system and method for performance of thermal protection material | |
| CN205138659U (en) | A high temperature testing arrangement for scanning electron microscope vacuum environment | |
| Rizzo et al. | Calibration methodology for contact heat flux sensors with enhanced accuracy | |
| US6301775B1 (en) | Alumina encapsulated strain gage, not mechanically attached to the substrate, used to temperature compensate an active high temperature gage in a half-bridge configuration | |
| Dimitrov et al. | Thin film platinum resistance thermometers: calibration and mathematical description of T (R) function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |