CN104691790A - High-accuracy micro deformation star sensor mounting bracket - Google Patents
High-accuracy micro deformation star sensor mounting bracket Download PDFInfo
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- CN104691790A CN104691790A CN201510080467.6A CN201510080467A CN104691790A CN 104691790 A CN104691790 A CN 104691790A CN 201510080467 A CN201510080467 A CN 201510080467A CN 104691790 A CN104691790 A CN 104691790A
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Abstract
The invention discloses a high-accuracy micro deformation star sensor mounting bracket. A star sensor mounting plate is connected to the outer surface of a thin-wall shell structure; a heat pipe is positioned inside the thin-wall shell structure; one end of the heat pipe is connected to the star sensor mounting plate; the other end of the heat pipe is connected with a heat collecting plate; the heat collecting plate is connected to the inner side of the top of the thin-wall shell structure and partially extends out of the top of the thin-wall shell structure; a first insulation mat is mounted between the heat collecting plate and the thin-wall shell structure; a rear cover board is connected to the back of the thin-wall shell structure so as to form a mounting bracket head; one end of a strut assembly is connected with the mounting bracket head; the other end of the strut assembly is used for mounting a spacecraft optical imaging effective load structure body. The high-accuracy micro deformation star sensor mounting bracket solves the technical difficult problem of harsh thermal deformation of a high-orbit spacecraft star sensor mounting bracket so as to meet the requirements on high-accuracy attitude determination of a spacecraft and image navigation registration, and meanwhile, has the advantages of novel structural form, light weight and the like.
Description
Technical field
What the present invention relates to is the device in Design of spacecraft structure field, is specially a kind of high precision Light deformation star sensor mounting bracket.
Background technology
Spacecraft star sensor is installed one and is not directly installed on spacecraft body construction, often needs Special mounting structure to transfer, mounting structure provides apparatus installation face and the attachment face with spacecraft structure body.Conventional one requirement of mounting structure has lightweight, high rigidity, good conducting and heat transfer characteristic, has enough intensity simultaneously, therefore often adopts light aluminum alloy or magnesium alloy materials integrated machine to process.Spacecraft in orbit time, these mounting structures are in repeatedly in the harsh environment of alternation, mounting structure will cause thermal deformation very big due to the high coefficient of thermal expansion of metallic material, appearance control instrument points to great changes will take place, spacecraft accuracy of attitude determination will be caused so poor, photographic images is fuzzy, and spacecraft function greatly reduces, and even loses.
Along with China is to the demand of spacecraft high precision, high-resolution imaging, particularly high rail spacecraft to star sensor mounting structure in-orbit thermal deformation propose rigors, design form traditional at present may meet high rail spacecraft high-precision attitude hardly and determine and the requirement of image-guidance registration.
Summary of the invention
The present invention is directed to and adopt the star sensor mounting structure of traditional design can not meet high orbit spacecraft high-precision attitude to determine and image-guidance registration requires deficiency, propose a kind of high precision Light deformation star sensor mounting bracket, the quick adapter plate of its culminant star passes through heat pipe heat radiation, be connected by flexible apparatus with heat pipe simultaneously, make it take into account to have two kinds of characteristics that the good and thermal deformation of heat conductivility is isolated, thin walled cavity structure and rod member assembly adopt carbon fiber composite material to ensure that this device had both had larger rigidity, very light weight again simultaneously.
The present invention is achieved by the following technical solutions.
A kind of high precision Light deformation star sensor mounting bracket, comprise: the quick adapter plate of thin-wall case structure, back shroud, star, heat collection plate, the first heat insulating mattress, heat pipe and strut bar assembly, wherein, the quick adapter plate of described star is connected on outside thin-wall case structure, for installing star sensor; Described heat pipe is positioned at the inside of thin-wall case structure, and one end of heat pipe is connected on the quick adapter plate of star, and the other end of heat pipe is connected with heat collection plate; Described heat collection plate is connected to the inside top of thin-wall case structure, and stretches out the top of thin-wall case structure at least partly; Described first heat insulating mattress is arranged between heat collection plate and thin-wall case structure; Described back shroud is connected to the back side of thin-wall case structure, thus forms mounting bracket head; One end of described strut bar assembly is connected with mounting bracket head, and the other end of strut bar assembly is for installing spacecraft optical imagery capacity weight structural body.
Preferably, described thin-wall case structure is provided with multiple outside, the quick adapter plate of described star is three pieces, be respectively the quick adapter plate of the first star, the quick adapter plate of second star and the quick adapter plate of Samsung, three pieces of quick adapter plates of star are connected on three outsides in the multiple outside of thin-wall case structure, described heat pipe comprises the first heat pipe and the second heat pipe, wherein, one end of first heat pipe is connected with the quick adapter plate of the first star and the quick adapter plate of the second star respectively, one end of second heat pipe is connected with the quick adapter plate of Samsung, described first heat pipe is all connected with heat collection plate with the other end of the second heat pipe.
Preferably, the quick adapter plate of described star adopts aluminum alloy materials; The outside face corner of the quick adapter plate of star is respectively equipped with the first boss, and described first boss is for installing star sensor; The inside face of the quick adapter plate of star is provided with the second boss, and described second boss is positioned at the position of center line of the quick adapter plate of star, for providing heat pipe joint face.
Preferably, the both sides of described second boss are provided with inside and outside through spron, and described inside and outside through spron is that star quick adapter plate line of centers is symmetrical.
The inner ring of the point of connection position of the point of connection position between the quick adapter plate of described star and thin-wall case structure between the quick adapter plate of star and star sensor.
Connection between described heat pipe and the quick adapter plate of star and between heat pipe and heat collection plate all selects flexible connecting device to connect, and described flexible connecting device adopts disc spring.
Described heat collection plate adopts high-thermal-conductivity low-expansibility aluminum-base silicon carbide material, and the installation screw thread on heat collection plate uses titanium alloy lining.
Described thin-wall case structure adopts carbon fiber composite material, and adopts integral structure.
Described strut bar assembly comprises rod member and the second heat insulating mattress, and one end of described rod member is provided with the joint for being connected on mounting bracket head, and the other end of rod member is connected in spacecraft optical imagery capacity weight structural body by the second heat insulating mattress.
Described rod member adopts carbon fiber composite material, and the laying angle of carbon fiber composite material be that the zero thermal expansion of [± 35 °/0 °/90 °] designs, and with joint integrated molding; Described second heat insulating mattress adopts titanium alloy material, and is hollow structure.
When the present invention works, star sensor is arranged on the quick adapter plate of star, heat is produced when star sensor works, heat is delivered on heat collection plate by the heat pipe be connected with the quick adapter plate of star by these heats, and on heat collection plate, heat is delivered to spacecraft heat delivery surface by the outside heat pipe of spacecraft by heat again.Due to the rational layout of whole device and structure, connection design and Material selec-tion, this device is made to have enough heat stabilitys and intensity, rigidity, and lighter weight.
Relative with prior art, the present invention has following effectively effect: spacecraft in orbit time, this device is in repeatedly in the harsh thermal environment of alternation, and particularly heat collection plate is due to the impact by spacecraft heat delivery surface low temperature environment, and thermal environment is very severe, extreme low temperature reaches-30 DEG C, and cyclical variation, and the quick attachment face of star must ensure 20 DEG C ± 0.5 DEG C, the present invention adopts as above summary of the invention, this device is made to have enough heat stabilitys and intensity, rigidity, and lighter weight.During spacecraft operation on orbit, the absolute thermal deformation of the quick attachment face of this device star (namely the quick attachment face of star is relative to strut bar root) is less than 15 "; between three quick attachment faces of star, relative thermal deformation is less than 5 ", relative conventional design reduces by 1 order of magnitude, meets high rail spacecraft high-precision attitude and determines and the requirement of image-guidance registration.This device have employed many innovative designs, has good reference to similar structures Control Thermal Deformation, be in particular in following some:
1) adopt heat pipe to carry out the technical scheme of conducting heat, solve the efficient heat transfer problem of star sensor;
2) what heat pipe and the quick adapter plate of star, heat pipe and heat collection plate adopted disc spring flexibly connects design form, reduces the tension-torsion effect to the quick adapter plate of star;
3) the quick adapter plate corner of star adopts boss design, ensure that the manufacturability that high precision is processed, and provide the installing space compensating heating plate, symmetrical spron design is adopted with the quick adapter plate of clock star, the quick adapter plate built-in thermal stress of star can be discharged, the temperature homogeneity of four boss can be ensured again, to reduce thermal deformation;
4) the quick adapter plate of star and thin-wall case structural attachment point position are positioned at the quick adapter plate of star and star quick point of connection position inner ring, the thermal deformation of outside four boss of the quick adapter plate of star can be discharged like this, ensure the matching of the quick adapter plate of star four boss and star sensor Housing Base thermal deformation;
5) heat collection plate uses high-thermal-conductivity low-expansibility material, makes it have good heat conduction, heat transfer characteristic, and self thermal deformation is less simultaneously, reduces the impact on other structure;
6) glass-felt plastic Design on thermal insulation is selected between heat collection plate and thin-wall case structure, reduce the thermoradiation efficiency of heat collection plate to thin-wall case structure, strut bar assembly takes the provision for thermal insulation of hollow titanium alloy structure, reduces optical imagery load to the heat transmission of strut bar;
7) strut bar adopts " zero " expansion Lay up design, reduces strut bar thermal deformation;
8) adopt the thin walled cavity structure of carbon fiber composite material, back shroud and strut bar assembly, make whole device have enough rigidity and heat stability, simultaneously structure lightened.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is Facad structure figure of the present invention;
Fig. 2 is inverse layer structure figure of the present invention;
Fig. 3 is cut-away view of the present invention;
Fig. 4 is heat pipe of the present invention and the quick adapter plate of star, heat collection plate connection diagram, and wherein, (a) is overall schematic, and (b) is partial enlarged drawing;
Fig. 5 is the quick adapter plate figure of star of the present invention, and wherein, (a) is front view, and (b) is lateral plan, and (c) is birds-eye view;
Fig. 6 is strut bar component drawings of the present invention;
Fig. 7 is heat collection plate figure of the present invention;
In figure: 1 is the quick adapter plate of the first star, 2 is the quick adapter plate of the second star, and 3 is heat collection plate, and 4 is thin-wall case structure, 5 is the quick adapter plate of Samsung, 6 is the first strut bar assembly, and 7 is the second strut bar assembly, and 8 is back shroud, 9 is the first heat insulating mattress, 10 is the first heat pipe, and 11 is the second heat pipe, and 12 is disc spring, 13 is screw, 14 is the second boss, and 15 is thin-wall case structural attachment point, and 16 is star sensor point of connection, 17 is inside and outside through spron, 18 is the first boss, and 19 is rod member, and 20 is the second heat insulating mattress.
Detailed description of the invention
Below embodiments of the invention are elaborated: the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.
Please refer to Fig. 1 to Fig. 7.
Present embodiments provide a kind of high precision Light deformation star sensor mounting bracket, comprise: the quick adapter plate of thin-wall case structure, back shroud, star, heat collection plate, heat insulating mattress, heat pipe and strut bar assembly, wherein, the quick adapter plate of described star is connected on outside thin-wall case structure, for installing star sensor; Described heat pipe is positioned at the inside of thin-wall case structure, and one end of heat pipe is connected on the quick adapter plate of star, and the other end of heat pipe is connected with heat collection plate; Described heat collection plate is connected to the inside top of thin-wall case structure, and stretches out the top of thin-wall case structure at least partly; Described first heat insulating mattress is arranged between heat collection plate and thin-wall case structure; Described back shroud is connected to the back side of thin-wall case structure, thus forms mounting bracket head; One end of described strut bar assembly is connected with mounting bracket head, and the other end of strut bar assembly is for installing spacecraft optical imagery capacity weight structural body.
Further; thin-wall case structure is provided with multiple outside; the quick adapter plate of star is three pieces; be respectively the quick adapter plate of the first star, the quick adapter plate of the second star and the quick adapter plate of Samsung; three pieces of quick adapter plates of star are connected on three outsides in the multiple outside of thin-wall case structure; heat pipe comprises the first heat pipe and the second heat pipe; wherein; one end of the first heat pipe is connected with the quick adapter plate of the first star and the quick adapter plate of the second star respectively; one end of the second heat pipe is connected with the quick adapter plate of Samsung, and the first heat pipe is all connected with heat collection plate with the other end of the second heat pipe.
Further, the quick adapter plate of star chooses aluminum alloy materials, and outside face corner adopts boss design, and inside face also adopts boss to design, and is positioned at adapter plate position of center line.Outside face four boss, provide star sensor four installation feet, boss exterior domain is used for the heating plate installing space that affords redress, and adopts boss design can improve the manufacturability of the quick attachment face high precision processing of star simultaneously; Inside face boss is for installing heat pipe.
Further, star quick adapter plate inside face boss both sides arrange inside and outside through spron, and in star, quick adapter plate line of centers is symmetrical.Spron can discharge the quick adapter plate thermal stress of star, and simultaneously symmetrical design form can ensure the homogeneity of the quick adapter plate of star four installation foot temperature, to reduce thermal deformation.
Further, the quick adapter plate of star and thin-wall case structural attachment point position are positioned at the quick adapter plate of star and star quick point of connection position inner ring.The thermal deformation of outside four boss of the quick adapter plate of star can be discharged like this, ensure the matching of the quick adapter plate of star four boss and star sensor Housing Base thermal deformation, prevent from not mating to cause due to distortion destroying star sensor internal optical component.
Further, heat pipe with the quick adapter plate of star, be connected between heat pipe with heat collection plate and all select flexible connection forms, simultaneously flexible apparatus selects disc spring.Flexibly connect and can reduce heat pipe and heat collection plate effect is pullled to the quick adapter plate of star, reduce thermal deformation.
Further, heat collection plate adopts high-thermal-conductivity low-expansibility aluminum-base silicon carbide material, installs screw thread and uses titanium alloy lining.Adopt high-thermal-conductivity low-expansibility material to make this structure have good heat conduction, heat transfer characteristic, self thermal deformation produced due to its severe thermal environment can be reduced again, reduce there is deformation effect to other structure.
Further, thin-wall case structure adopts carbon fiber composite material, is designed to integral structure.The carbon fiber composite structure of integration is adopted to have good heat stability and mechanical stability.
Further, strut bar assembly comprises rod member, heat insulating mattress, and this assembly one end is connected to mounting bracket head, and the other end is connected in spacecraft optical imagery capacity weight structural body.
Further, rod member adopts carbon fiber composite material, and " zero " expanded form that layering type is designed to [± 35 °/0 °/90 °], joint also adopts carbon fiber composite material, can reduce strut bar thermal deformation like this.
Further, strut bar assembly place heat insulating mattress adopts titanium alloy material, is designed to hollow structure form, reduces and spacecraft optical imagery capacity weight form touch area, thus reduces interchange of heat between strut bar assembly, reduces strut bar thermal deformation.
Below in conjunction with accompanying drawing, the present embodiment is further described.
As shown in Figure 1, 2, 3, the high precision Light deformation star sensor mounting bracket that the present embodiment provides, comprising: thin-wall case structure 4, back shroud 8, the quick adapter plate of star, heat collection plate 3, heat insulating mattress 9,20, heat pipe 10,11 and strut bar assembly 6,7.Wherein, the quick adapter plate 1 of first star, the quick adapter plate 2 of second star, the quick adapter plate 5 of Samsung, be connected on three outsides of thin-wall case structure 4 outside, first heat pipe 10, it is inner that second heat pipe 11 is positioned at thin-wall case structure 4, first its one end of heat pipe 10 is connected to the second boss of the quick adapter plate 1 of the first star, the second boss of the quick adapter plate 2 of the second star is connected in the middle part of first heat pipe 10, the other end of the first heat pipe 10 is connected to heat collection plate 3, second heat pipe 11 one end is connected to the second boss of the quick adapter plate 5 of Samsung, second heat pipe 11 other end is connected on heat collection plate 3.Heat collection plate 3 is connected to thin-wall case structure 4 inside top, and part is stretched out simultaneously, and the first heat insulating mattress 9 is arranged between heat collection plate 3 and thin-wall case structure 4, and back shroud 8 is connected to thin-wall case structure 4 back side, thus forms mounting bracket head; One end of first strut bar assembly 6, second strut bar assembly 7 is connected with mounting bracket head, and the other end is arranged in spacecraft optical imagery capacity weight structure.
As shown in Fig. 4 (a), (b), give the annexation of the first heat pipe 10, second heat pipe 11 with the quick adapter plate of heat collection plate 3, first star quick adapter plate 1, second star 2, the quick adapter plate 5 of Samsung, first heat pipe and the second heat pipe are provided with screw 13 mounting hole at wing plate, use disc spring 8 simultaneously, weaken coupling stiffness.
As shown in Fig. 5 (a), (b), (c), the quick adapter plate of first star quick adapter plate 1, second star 2, the quick adapter plate 5 of Samsung choose aluminum alloy materials, outside face corner adopts the first boss 18 to design, for installing star sensor, inside face also adopts the second boss 14 to design, be positioned at adapter plate position of center line, for providing heat pipe joint face.
The quick adapter plate of first star quick adapter plate 1, second star 2, Samsung quick adapter plate 5 inside face second boss both sides provide inside and outside through spron 17, and in star, quick adapter plate line of centers is symmetrical.
The quick adapter plate of first star quick adapter plate 1, second star 2, the quick adapter plate of Samsung 5 and thin-wall case structure 4 point of connection 15 are positioned at the quick adapter plate of the first star quick adapter plate 1, second star 2, the quick adapter plate 5 of Samsung and star sensor point of connection 16 inner ring.
As shown in Figure 6, the first strut bar assembly 6, second strut bar assembly 7 includes integrated rod member 19, second heat insulating mattress 20, and this assembly one end is connected to mounting bracket head, and the other end is connected in spacecraft optical imagery capacity weight structural body.
Described rod member 19 adopts carbon fiber composite material, and layering type is designed to ± " zero " expanded form of 35 °/0 °/90 °, joint also adopts carbon fiber composite material.
Second heat insulating mattress 20 adopts titanium alloy material, is designed to hollow structure form, reduces and spacecraft optical imagery capacity weight form touch area, thus reduces interchange of heat between strut bar assembly.
Heat collection plate 3 adopts high-thermal-conductivity low-expansibility aluminum-base silicon carbide material, installs screw thread and uses titanium alloy lining.
Thin-wall case structure 4 adopts carbon fiber composite material, is designed to integral structure.
During the present embodiment work, three star sensors are arranged on the quick adapter plate of the first star quick adapter plate 1, second star 2, the quick adapter plate 5 of Samsung respectively, heat is produced when star sensor works, on the quick adapter plate 2 of first star quick adapter plate 1, second star, heat is delivered on heat collection plate 3 by internal stent first heat pipe 10, and on the quick adapter plate 5 of Samsung, heat is delivered on heat collection plate 3 by the second heat pipe 11.On heat collection plate 3, heat is delivered to spacecraft heat delivery surface by the outside heat pipe of spacecraft by heat again.Due to the rational layout of whole device and structure, connection design and Material selec-tion, this device is made to have enough heat stabilitys and intensity, rigidity, and lighter weight.The relative conventional design of the present invention makes thermal deformation in-orbit reduce by 1 order of magnitude, meets high rail spacecraft high-precision attitude and determines and the requirement of image-guidance registration.
The present embodiment solves the thermal deformation technical barrier of high rail spacecraft star sensor mounting bracket harshness, thus meets spacecraft high-precision attitude and determine and the requirement of image-guidance registration to have new in structure, the advantages such as quality is light simultaneously.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. a high precision Light deformation star sensor mounting bracket, it is characterized in that: comprising: the quick adapter plate of thin-wall case structure, back shroud, star, heat collection plate, the first heat insulating mattress, heat pipe and strut bar assembly, wherein, the quick adapter plate of described star is connected to outside thin-wall case structure, for installing star sensor; Described heat pipe is positioned at the inside of thin-wall case structure, and one end of heat pipe is connected on the quick adapter plate of star, and the other end of heat pipe is connected with heat collection plate; Described heat collection plate is connected to the inside top of thin-wall case structure, and part stretches out the top of thin-wall case structure; Described first heat insulating mattress is arranged between heat collection plate and thin-wall case structure; Described back shroud is connected to the back side of thin-wall case structure, thus forms mounting bracket head; One end of described strut bar assembly is connected with mounting bracket head, and the other end of strut bar assembly is for installing spacecraft optical imagery capacity weight structural body.
2. high precision Light deformation star sensor mounting bracket according to claim 1, it is characterized in that: described thin-wall case structure is provided with multiple outside, the quick adapter plate of described star is three pieces, be respectively the quick adapter plate of the first star, the quick adapter plate of second star and the quick adapter plate of Samsung, three pieces of quick adapter plates of star are connected on three outsides in the multiple outside of thin-wall case structure, described heat pipe comprises the first heat pipe and the second heat pipe, wherein, one end of first heat pipe is connected with the quick adapter plate of the first star and the quick adapter plate of the second star respectively, one end of second heat pipe is connected with the quick adapter plate of Samsung, described first heat pipe is all connected with heat collection plate with the other end of the second heat pipe.
3. high precision Light deformation star sensor mounting bracket according to claim 1, is characterized in that: the quick adapter plate of described star adopts aluminum alloy materials; The outside face corner of the quick adapter plate of star is respectively equipped with the first boss, and described first boss is for installing star sensor; The inside face of the quick adapter plate of star is provided with the second boss, and described second boss is positioned at the position of center line of the quick adapter plate of star, for providing heat pipe joint face.
4. high precision Light deformation star sensor mounting bracket according to claim 3, is characterized in that: the both sides of described second boss are provided with inside and outside through spron, and described inside and outside through spron is that star quick adapter plate line of centers is symmetrical.
5. high precision Light deformation star sensor mounting bracket according to claim 1, is characterized in that: the inner ring of the point of connection position of the point of connection position between the quick adapter plate of described star and thin-wall case structure between the quick adapter plate of star and star sensor.
6. high precision Light deformation star sensor mounting bracket according to claim 1, it is characterized in that: the connection between described heat pipe and the quick adapter plate of star and between heat pipe and heat collection plate all selects flexible connecting device to connect, described flexible connecting device adopts disc spring.
7. high precision Light deformation star sensor mounting bracket according to claim 1, is characterized in that: described heat collection plate adopts high-thermal-conductivity low-expansibility aluminum-base silicon carbide material, and the installation screw thread on heat collection plate uses titanium alloy lining.
8. high precision Light deformation star sensor mounting bracket according to claim 1, is characterized in that: described thin-wall case structure adopts carbon fiber composite material, and adopts integral structure.
9. high precision Light deformation star sensor mounting bracket according to claim 1, it is characterized in that: described strut bar assembly comprises rod member and the second heat insulating mattress, one end of described rod member is provided with the joint for being connected on mounting bracket head, and the other end of rod member is connected in spacecraft optical imagery capacity weight structural body by the second heat insulating mattress.
10. spacecraft high precision Light deformation appearance control instrument mounting structure according to claim 9, it is characterized in that: described rod member adopts carbon fiber composite material, the laying angle of carbon fiber composite material is the zero thermal expansion design of [± 35 °/0 °/90 °], and with joint integrated molding; Described second heat insulating mattress adopts titanium alloy material, and is hollow structure.
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| CN107792400B (en) * | 2017-09-19 | 2021-06-29 | 上海卫星工程研究所 | Satellite external-pasting heat pipe mounting structure with deformation isolation function |
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| CN107972889B (en) * | 2017-11-20 | 2019-06-18 | 中国运载火箭技术研究院 | A kind of used group mounting structure of high rigidity high-precision composite material |
| CN113998157A (en) * | 2021-10-11 | 2022-02-01 | 上海卫星装备研究所 | Spacecraft mechanical-thermal integrated multi-equipment mounting bracket and manufacturing method thereof |
| CN113998157B (en) * | 2021-10-11 | 2023-08-11 | 上海卫星装备研究所 | Spacecraft mechanical-thermal integrated multi-equipment mounting bracket and manufacturing method thereof |
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