CN201017038Y - Heat insulation shielding cover used on satellite magnetic field popple analyzer three-component sensor - Google Patents
Heat insulation shielding cover used on satellite magnetic field popple analyzer three-component sensor Download PDFInfo
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- CN201017038Y CN201017038Y CNU2007201037899U CN200720103789U CN201017038Y CN 201017038 Y CN201017038 Y CN 201017038Y CN U2007201037899 U CNU2007201037899 U CN U2007201037899U CN 200720103789 U CN200720103789 U CN 200720103789U CN 201017038 Y CN201017038 Y CN 201017038Y
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- adiabatic
- diaphragm
- radome
- ground wire
- heat
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Abstract
The utility model discloses a heat-insulating shielding cover used on a three-componnet sensor of a satellite magnetic field fluctuation analyzer, and comprises a heat-insulating membrane, a ground wire and a ground wire connector. The heat-insulating shielding cover consists of a plurality of layers of heat-insulating membranes butting-connected and stitched up along the neighboring edges and is provided with 33 planes. Each plane is covered by a heat-insulating membrane, or neighboring planes of different shapes are covered by a larger whole heat-insulating membrane. An electric-insulating interlayer rubber strip is inserted between edges of neighboring heat-insulating membranes, at which the membranes are connected in a butting way and stitched up. The heat-insulating membrane consists of 10 layers of heat-insulating membranes dedicated to space satellites and isolating nets between the heat-insulating membrane layers, and the heat-insulating layers and the nets are overlapped and tailored. The ground wire is connected with the heat-insulating membrane. The ground wire connector connects the ground wire of each heat-insulating membrane to a ground bolt of the sensor in sequence. Each heat-insulating membrane connected with the ground wire connector cannot form an electrically-closed loop to the whole sensor structure or any component of the sensor.
Description
Technical field
The utility model relates to satellite magnetic field fluction analysis instrument three-component sensor, particularly is used for the adiabatic radome on this three-component sensor.
Background technology
Because satellite magnetic field fluction analysis instrument possesses higher detection sensitivity, the three-component sensor need be away from various interference sources, particularly Aerospace Satellite is in the interference of the temperature variation in sunshine and shadow region etc., and therefore, satellite magnetic field fluction analysis instrument three-component sensor must be away from the satellite celestial body.This three-component sensor is installed in the top that stretches out in a long boom outside the satellite equipment storehouse usually, and sensor is in outside the satellite equipment storehouse, does not have the satellite temperature control device to regulate the electrostatic influence that temperature also can be subjected to space charged particle.If without any thermoshield equipment, magnetic field fluction analysis instrument sensor antenna etc. similarly the star external equipment space sunshine district and the shadow region in or all have from the following low temperature of negative more than 100 degree between sunside and back of the body day face and flow the temperature fluctuation that high temperature are spent in positive more than 100 of irradiation generation to the reception solar energy, not only influence the instrument operate as normal, increase signal noise and disturb, also quickened the aging of sensor construction material even caused structural failure.And the scope of application of sensor and arrangement works temperature thereof is much smaller than the temperature variation of space environment, therefore sensor can be worked steadily in the long term in the abominable space environment of low temperature, intense radiation (photograph), many electrostatic interference, just must the adiabatic radome of sensor installation.
Summary of the invention
The purpose of this utility model provides a kind of structure and is fit to the adiabatic radome that satellite-loaded magnetic field fluction analysis instrument three-component wave sensor is installed, to satisfy the space flight requirement.
To achieve these goals, the utility model provides a kind of adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field, be used for the three-component wave sensor under the extreme environment of space thermal insulation shielding and to the shielding of static discharge phenomenon; Described adiabatic radome comprises adiabatic diaphragm, ground wire 44 and ground link 45; Described adiabatic radome is sewed up along the neighboring edge butt joint by difform multilayer heat insulation diaphragm and is formed, the shared geometric volume of described adiabatic radome can be divided into by 6 six square stage bodies 2,3,4,5,6,7 and 1 regular hexahedron 10 in the middle part of being positioned at is formed, and has 33 planes; Each plane can be by one adiabatic membrane covered, or difform adjacent plane is by whole a covering of the adiabatic diaphragm of bigger monoblock; Adjacent adiabatic diaphragm inserts electrical isolation interlayer adhesive tape between the edge that butt joint is sewed up; Described adiabatic diaphragm is formed by the overlapping cutting of separation net of special-purpose adiabatic membrane of 10 layers of space satellite and adiabatic membrane interlayer, and at the place, top of described six square stage bodies, the number of plies of adiabatic diaphragm reduces to below 5 layers; The outside surface of described adiabatic membrane is a conductive layer; Described ground wire 44 is connected on the described adiabatic diaphragm, should connect all retes of described adiabatic diaphragm when connecting, and described ground wire 44 is positioned at the inside of described radome; Described ground connection connects 45 ground wires 44 with each adiabatic diaphragm and is linked in sequence on the earth stud 8 of sensor, each adiabatic diaphragm that ground link 45 is linked can not form the electric closed circuit to whole sensor structure or arbitrary component, is promptly begun should form so-called tree to the ground wire 44 of ground link and each adiabatic diaphragm by earth stud.
In the technique scheme, described difform a plurality of adjacent planes can be by the bigger adiabatic membrane covered of a monoblock, and the adiabatic diaphragm of a monoblock can cover 4 difform adjacent planes at the most; Describedly belonged to together angle should be greater than 90 degree between the common adjacent plane that covers of an adiabatic diaphragm.
In the technique scheme, the voltage breakdown of described electrical isolation interlayer adhesive tape is greater than 0.5 kilovolt.
In the technique scheme, described adiabatic diaphragm is taken up an official post what any resistance to earth less than 10 kilohms.
In the technique scheme, when described ground wire 44 is connected on the described adiabatic diaphragm, be positioned at the medium position of described adiabatic diaphragm geometric surface, 10 millimeters to 20 millimeters places, contiguous adiabatic diaphragm edge.
In the technique scheme, the resistivity of ground wire 44 is not more than 20 kilohms/meter, 2 amperes of maximum loaded currents.
In the technique scheme, described ground link 45 should satisfy the following order of connection when connecting described ground wire 44:
Each ground wire 44 all can not form closed loop, or the adiabatic diaphragm of part can not form local closed loop, and connecting line 44 need satisfy shortest path and promptly must all be connected to minimum and the shortest connecting line, all adiabatic diaphragms, and total way of separate connection line is minimum.
In the technique scheme, be provided with the cushion of resilient material between each protuberance of described adiabatic radome and described sensor.
Advantage of the present utility model is:
1, ground link connection and reasonable arrangement, electromagnetic interference (EMI) is little, and is antistatic strong; ,
2, the Rational structure of adiabatic radome can be born by boom and is amplified to emission vibration more than the 40g.
Description of drawings
Fig. 1 is that the volume of the adiabatic radome parcel of satellite magnetic field fluction analysis instrument three-component sensor is divided into each surperficial 3-D view on seven unitary part;
Fig. 2 comprises each surface three dimension view of 5,7,10 3 parts that A links each adiabatic diaphragm of path in the adiabatic radome of satellite magnetic field fluction analysis instrument three-component sensor;
Fig. 3 comprises each surface three dimension view of 4,5,6,7,10 5 parts that B links each adiabatic diaphragm of path in the adiabatic radome of satellite magnetic field fluction analysis instrument three-component sensor;
Fig. 4 comprises each surface three dimension view of 2,3,7,10 4 parts that C links each adiabatic diaphragm of path in the adiabatic radome of satellite magnetic field fluction analysis instrument three-component sensor;
Fig. 5 comprises each surface three dimension view of 3,4,6,10 4 parts that D links each adiabatic diaphragm of path in the adiabatic radome of satellite magnetic field fluction analysis instrument three-component sensor;
Fig. 6 is three adjacent adiabatic diaphragms 31,32,37 and the ground wire 44 in the radome and the 3-D view of ground link 45 that shows the adiabatic radome of satellite magnetic field fluction analysis instrument three-component sensor.
The drawing explanation
1 radome 2 to 7 all is square stage body 8 earth studs 9 plug connectors of six
10 regular hexahedrons
11 to 13 is three surfaces that regular hexahedron 10 exposes
14 to 18 is five surfaces that six square stage bodies 3 expose
19 to 23 is five surfaces that six square stage bodies 6 expose
24 to 28 is five surfaces that six square stage bodies 4 expose
29 to 33 is five surfaces that six square stage bodies 5 expose
34 to 38 is five surfaces that six square stage bodies 7 expose
39 to 43 is five surfaces that six square stage bodies 2 expose
44 ground wires, 45 ground links
Specific embodiments
Below in conjunction with the drawings and specific embodiments the adiabatic radome on the three-component sensor of the present utility model is described.
Adiabatic radome of the present utility model is used for satellite magnetic field fluction analysis instrument three-component sensor, therefore, the shape and the three-component sensor of adiabatic radome have confidential relation, in the present embodiment, before adiabatic radome is described, at first the three-component sensor that is used on the fluction analysis instrument of satellite magnetic field is described.
The three-component sensor that is used for satellite magnetic field fluction analysis instrument has high sensitivity, but this sensor need stably be worked in low temperature, high vacuum, antistatic, intense radiation abominable space environment midium or long terms such as (photographs), also must bear when taking off such as rocket through the boom system and be amplified to judder more than the acceleration 40g.Therefore, described three-component sensor has specific structure, to adapt to the space requirements of one's work.
Adiabatic radome of the present utility model is wrapped on the described three-component sensor, is one and has the obturator that matches with the sensor construction profile, be made up of 33 quadrangular plan.This thermal insulation shielding covers on and may be partitioned into 6 six square stage bodies and 1 regular hexahedron that is positioned at the middle part on the geometric configuration.As shown in Figure 1, adiabatic radome 1 of the present utility model is divided into 6 six square stage bodies, represent with 2,3,4,5,6 and 7 respectively, 5 faces that six square stage bodies 2 expose are represented with 39-43 respectively, 5 faces that six square stage bodies 3 expose are represented with 14-18 respectively, 5 faces that six square stage bodies 4 expose are represented with 24-28 respectively, 5 faces that six square stage bodies 5 expose are represented with 29-33 respectively, 5 faces that six square stage bodies 6 expose represent with 19-23 respectively, and 5 faces that six square stage bodies 7 expose are represented with 34-38 respectively.The regular hexahedron at middle part represents that with 10 3 faces that regular hexahedron exposes are represented with 11-13.
On every adiabatic diaphragm, all include ground wire, the tie point of described ground wire and adiabatic diaphragm is usually at the middle part of adiabatic diaphragm, and 10 millimeters to 20 millimeters at the edge of contiguous adiabatic diaphragm.The resistivity of described ground wire should be not more than 20 kilohms/meter, and maximum loaded current is 2 amperes.Described every all retes that adiabatic diaphragm ground wire all runs through to be connected to this thermal insulation diaphragm, ground wire is positioned at adiabatic radome.As shown in Figure 6, after adiabatic diaphragm reduction finishes, with rivet ground wire 44 is riveted on the adiabatic diaphragm, ground wire 44 is positioned at adiabatic diaphragm on the inside surface of radome 1.
After ground wire is riveted on each adiabatic diaphragm, sew up adiabatic diaphragm, when sewing up, at first insert wide about 8 millimeters electrical isolation interlayer adhesive tape between the edge that adjacent adiabatic diaphragm abutment joint is closed, then electrical isolation interlayer adhesive tape is docked stitching with the edge, form the edge electrical isolation between adjacent adiabatic diaphragm, to avoid the electrical coupling between adiabatic diaphragm.When sewing up, the suture line that is adopted is the insulated wire of space flight special use, and the pin hole of stitching is apart from about 5 millimeters.Before sewing up whole adiabatic diaphragms, the edge between reservation and face 15 and 16,13 and 22, the 29 and 33 corresponding adiabatic diaphragms is not sewed up earlier, becomes the opening shape.The voltage breakdown of described electrical isolation interlayer adhesive tape should be greater than 0.5 kilovolt.
As shown in Figure 3, to the annexation that is labeled as the ground wire on 9,13,31,32,33,36 and 37 the plane be:
As shown in Figure 4, to the annexation that is labeled as the ground wire on 9,22,23,25,26,27,28,29,30 and 38 the plane be:
As shown in Figure 5, to the annexation that is labeled as the ground wire on 9,14,17,34,35,39,41,42 and 43 the plane be:
As shown in Figure 6, to the annexation that is labeled as the ground wire on 9,11,12,15,16,18,19,20,21,24 and 40 the plane be:
The annexation of above-mentioned ground wire is also not exclusive, its cardinal rule is: each ground wire all can not form closed loop, or the adiabatic diaphragm of part can not form local closed loop, connecting line need satisfy shortest path promptly with minimum and the shortest connecting line, all adiabatic diaphragms must all be connected to, total way of separate connection line is minimum, be easy to make and the strict requirement for restriction that satisfies the sensor gross weight etc.
In connection procedure, ground wire 44 is done insulation with the tie point of ground link 45.After aforesaid operations is finished, the three-component sensor is put into adiabatic radome 1 of the present utility model from the aforementioned opening of reserving, sew up the opening of reserving again, form closed adiabatic radome 1.
Because near the antenna at satellite--the resonant frequency of boom system, the three-component sensor will bear the high vibration times over satellite accelerations and Oscillation Amplitude.Big like this acceleration and amplitude can damage parts such as the structure of sensor and surface heat dielectric film at the utmost point in the short time.Therefore, be provided with the cushion of resilient material between each protuberance of adiabatic radome 1 and sensor construction.
Claims (8)
1. adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field, be used for the three-component wave sensor under the extreme environment of space the thermal insulation shielding and to the shielding of static discharge phenomenon; Described adiabatic radome comprises adiabatic diaphragm, ground wire (44) and ground link (45); It is characterized in that, described adiabatic radome is sewed up along the neighboring edge butt joint by difform multilayer heat insulation diaphragm and is formed, the shared geometric volume of described adiabatic radome can be divided into by 6 six square stage bodies (2), (3), (4), (5), (6), (7) and 1 regular hexahedron (10) in the middle part of being positioned at is formed, and has 33 planes; Each plane can be by one adiabatic membrane covered, or difform adjacent plane is by whole a covering of the adiabatic diaphragm of bigger monoblock; Adjacent adiabatic diaphragm inserts electrical isolation interlayer adhesive tape between the edge that butt joint is sewed up; Described adiabatic diaphragm is formed by the overlapping cutting of separation net of special-purpose adiabatic membrane of 10 layers of space satellite and adiabatic membrane interlayer, and at the place, top of described six square stage bodies, the number of plies of adiabatic diaphragm reduces to below 5 layers; The outside surface of described adiabatic membrane is a conductive layer; Described ground wire (44) is connected on the described adiabatic diaphragm, should connect all retes of described adiabatic diaphragm when connecting, and described ground wire (44) is positioned at the inside of described radome; Described ground connection connects (45) ground wire (44) of each adiabatic diaphragm is linked in sequence on the earth stud (8) of sensor, each adiabatic diaphragm that ground link (45) is linked can not form the electric closed circuit to whole sensor structure or arbitrary component, is promptly begun should form so-called tree to the ground wire (44) of ground link and each adiabatic diaphragm by earth stud.
2. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1, it is characterized in that, described difform a plurality of adjacent planes can be by the bigger adiabatic membrane covered of a monoblock, and the adiabatic diaphragm of a monoblock can cover 4 difform adjacent planes at the most; Describedly belonged to together angle should be greater than 90 degree between the common adjacent plane that covers of an adiabatic diaphragm.
3. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1 is characterized in that the voltage breakdown of described electrical isolation interlayer adhesive tape is greater than 0.5 kilovolt.
4. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1 is characterized in that, described adiabatic diaphragm is taken up an official post what any resistance to earth less than 10 kilohms.
5. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1, it is characterized in that, when described ground wire (44) is connected on the described adiabatic diaphragm, be positioned at the medium position of described adiabatic diaphragm geometric surface, 10 millimeters to 20 millimeters places, contiguous adiabatic diaphragm edge.
6. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1 is characterized in that the resistivity of ground wire (44) is not more than 20 kilohms/meter, 2 amperes of maximum loaded currents.
7. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1 is characterized in that, described ground link (45) should satisfy the following order of connection when connecting described ground wire (44):
Each ground wire (44) all can not form closed loop, or the adiabatic diaphragm of part can not form local closed loop, connecting line (44) need satisfy shortest path and promptly must all be connected to minimum and the shortest connecting line, all adiabatic diaphragms, and total way of separate connection line is minimum.
8. the adiabatic radome that is used on the fluction analysis instrument three-component sensor of satellite magnetic field according to claim 1 is characterized in that, is provided with the cushion of resilient material between each protuberance of described adiabatic radome and described sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201037899U CN201017038Y (en) | 2007-03-12 | 2007-03-12 | Heat insulation shielding cover used on satellite magnetic field popple analyzer three-component sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201037899U CN201017038Y (en) | 2007-03-12 | 2007-03-12 | Heat insulation shielding cover used on satellite magnetic field popple analyzer three-component sensor |
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| Publication Number | Publication Date |
|---|---|
| CN201017038Y true CN201017038Y (en) | 2008-02-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201037899U Expired - Fee Related CN201017038Y (en) | 2007-03-12 | 2007-03-12 | Heat insulation shielding cover used on satellite magnetic field popple analyzer three-component sensor |
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| CN (1) | CN201017038Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102681016A (en) * | 2011-03-11 | 2012-09-19 | 中国科学院空间科学与应用研究中心 | Low-frequency magnetic fluctuation analyzer sensor |
| CN106158050A (en) * | 2016-06-29 | 2016-11-23 | 中国科学院国家天文台 | A kind of thermal protection structure for nearly sun observation equipment |
| CN107894574A (en) * | 2017-09-30 | 2018-04-10 | 航天东方红卫星有限公司 | A kind of method that coil magnetometer carries out heat-control multilayer cladding |
-
2007
- 2007-03-12 CN CNU2007201037899U patent/CN201017038Y/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102681016A (en) * | 2011-03-11 | 2012-09-19 | 中国科学院空间科学与应用研究中心 | Low-frequency magnetic fluctuation analyzer sensor |
| CN102681016B (en) * | 2011-03-11 | 2014-07-09 | 中国科学院空间科学与应用研究中心 | Low-frequency magnetic fluctuation analyzer sensor |
| CN106158050A (en) * | 2016-06-29 | 2016-11-23 | 中国科学院国家天文台 | A kind of thermal protection structure for nearly sun observation equipment |
| CN107894574A (en) * | 2017-09-30 | 2018-04-10 | 航天东方红卫星有限公司 | A kind of method that coil magnetometer carries out heat-control multilayer cladding |
| CN107894574B (en) * | 2017-09-30 | 2019-10-18 | 航天东方红卫星有限公司 | A kind of method that coil magnetometer carries out heat-control multilayer cladding |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080206 Termination date: 20130312 |